Rocket launching system and auxiliary hardware

FIELD: transport.

SUBSTANCE: invention relates to systems for payload delivery to upper air and higher. Proposed system (1) comprises tubular rocket launching cart (2) with friction drives of cable-rope path (26) displacing below two-pin hinge (63) secured to ground and lifted to coaxial portable tube (124, 143) extending to three main fastened cables/ropes (27), their weight being equalized by balloons (164). Then, said cart displaces to connector station (166) retained above the ground in stratosphere by two secondary cables/rope (184) suspended from fastening frame (162) to tensioning of said balloons. Said cart is retained by end grip (196) of said cart directed in two secondary and two tertiary cables/rope (186) to be lifted by bottom lifter (198) guides by secondary cables. Said bottom lifter is retained by top lifter (168) suspended from fastening frame of tensioning balloons. Said cart hooked by lifting ring (183) guided by secondary cables/ropes upward revolves in necessary direction with release of rocket and, fact, recoilless ejection during free fall of said cart downward with engine ignition at safe distance.

EFFECT: safe, non-polluting reusable system.

50 cl, 67 dwg

 

Cross-reference to related applications

This application claims the benefit of priority interim patent application U.S. No. 61/337,645, filed February 11, 2010, in accordance with article 119(e) of Chapter 35 of the Code of laws of the United States, which is fully incorporated into the present description by reference.

Background of the INVENTION

Area of technology

The present invention relates to delivery systems of various types of payloads into the upper atmosphere and above, in particular the rocket launcher with high cyclic speed run starting from the top station. Self weight of the cables is compensated by the balloons. The cables are tensioned by one or more balloons and fastened pivotally fastened by a rope.

The level of technology

Exist or have been proposed in recent publications, many delivery methods useful materials, such as fuel gases for life support, etc. and products into the upper atmosphere and above.

Here primarily include rocket-powered chemical, nuclear or terrestrial laser or maser energy sources. Exist or have been proposed various ways to reduce the cost per unit mass delivery of useful materials and products into the upper atmosphere and above, which include missiles.

They included aircraft with cancer�time engines reusable like the American "Space Shuttle" that will soon be decommissioned, or now decommissioned Russian "Buran". Today we know that are operated only chemical multistage rocket or aircraft with outboard rocket boosters solid fuel or missiles, such as the tiny American Pegasus, which is transported to a great height before you start.

Suggested ways of reducing the cost of delivery into the upper atmosphere or higher most often involve the transfer of energy to the missile by either increasing their kinetic or potential energy prior to ignition of the main engine or engines. Suggestions by which this can be achieved include the following: raising by hanging under a one-time, free-flying balloon or forced ejection at high speed with big guns that use chemical fuels or compressed air or compressed hydrogen, or transported to great heights by attaching to the aircraft, such as jet aircraft, White Knight Two's company, Virgin Galactic, or transported to great heights by towing tethered on a rope outside the plane, or acceleration to a high speed using a land slide with linear induction�'s engines jet engines or rockets, before ignition of the main engine or engines of the rocket.

One proposed method of reducing the cost of delivery, which do not apply missiles, is the so - called "space Elevator" in which a large mass attached to the ground with one rope length of many thousands of miles. A large mass moves in a geosynchronous orbit of the earth and supports the cable is stretched tight. The cable would then be used similarly to the railroad tracks, which move the train.

The main complexity of the latter method is that the limit of the tensile strength of the material that you want to tether, significantly higher than that of any existing material, especially considering the fact that the own weight of the cable will be significant. Another difficulty is to pass the vehicle, climbing on this rope, sufficient energy to leave the Earth's gravitational field. Lightweight, super-strong tether material would be perfect for such a "space Elevator", but it does not yet exist. The problem of energy transfer to the height of the rope length of a thousand miles led me to think about the use of a focused microwave or laser energy for the climbing power of the vehicle. Defocusing and blocking the influence of the cloud� and atmosphere of focused energy with a high probability will greatly reduce the amount of energy which actually reaches the climbing vehicle. The dissipation of energy when you return (scrambling) of the vehicle on the ground is likely to be quite wasteful because of the need for braking, to avoid exceeding the limit speed of the mechanism that holds the specified vehicle on the rope.

Many of the proposed in the present methods require the development of new materials or massive structures, and it is unlikely that they will in the coming decades will reach commercial operation, if at all it happens.

The most current ways to start involve the use of large amounts of energy, primarily from fossil fuels such as coal or oil, for the production of cryogenic oxidizer liquid oxygen, cryogenic liquid hydrogen or other liquid hydrocarbon fuel or solid fuel. This use of non-renewable sources are inherently insufficient, because at this stage of fuel production is increasing technological inefficiency. In addition, a large mass and sometimes toxic nature of the exhaust of material used to move the vehicle beyond the atmosphere, often has a negative impact�on their ecology or may disrupt the balance of climate.

Accordingly, there is a need for method of delivery of useful materials, such as fuel gases for life support, etc. and products into the upper atmosphere and above, at such price per unit delivered mass, which is much lower than currently available on the market that uses the currently available materials and technologies. Furthermore, it will be helpful for the environment to minimize the mass of material used for the removal of the vehicle beyond the earth's atmosphere through the use of hydroelectric, geothermal or solar energy from photovoltaic panels to lift the vehicle as high as possible before igniting the engine or engines of the vehicle.

Atmospheric monitoring is carried out more than fifty years. Measurement of solar radiation, concentrations of trace gases, temperature, pressure and other parameters, which can predict the direction of the earth's climate changes, has significantly improved our understanding of global climate. This is particularly important in relation to the ozone hole, and a constant growth in carbon dioxide and other "greenhouse" gases in the atmosphere, and now more than fifty chemical compounds in the earth's atmosphere.

As rising levels of greenhouse gases and g�call, reducing the ozone layer, such as carbon dioxide, chlorofluorocarbons, nitrous oxide and sulphur hexafluoride, which lead to global warming and other global change of weather, increasing demands for a more permanent atmospheric monitoring. Current methods of monitoring atmospheric conditions are equipped with a large number of equipment manned and unmanned aircraft, uncontrollable gas balloons with an outboard unit of the apparatus; rockets with samples and measuring devices, as well as ground-based laser and radar stations.

Except for the ground stations they can provide only a relatively short period of sampling of atmospheric data. The longest control nanesennymi ways no more than a few days in the case of balls of gas, and the shortest, such as missiles, provides a measurement within a few minutes. In many of these methods of atmospheric monitoring are also used disposable units of the instrument, whereas the existing ground station cannot obtain physical samples to determine chemical composition, content of bacteria/microorganisms, analysis of the intensity and spectrum of sunlight, and other data across the entire depth of the atmosphere.

Therefore there is a need for structures extending from the surface of the earth on �greater height, which can be installed measuring equipment for continuous monitoring I. sampling of the atmosphere, solar and other radiation.

For security reasons, many countries worldwide are increasingly using radio and over-the-horizon radars.

Recent global concerns about security against the unexpected terrorist attacks, has forced countries such as the United States of America, to strengthen the monitoring of the use of radar and other means of detection using different regions of the electromagnetic spectrum. This is confirmed by the Act of Congress regarding the 9/11 Commission", 2007, partially concerning the radio system for the security of the United States. The scope of ground-based radars is limited by the curvature of the Earth, and to achieve a greater useful range radars and other systems are installed on Vysokaya flying machines or linked by cables gas balls at low altitude.

Similarly, the mobile operators are now trying to increase the area serviced by high-flying aircraft with receivers and transmitters that are scheduled to run in circles around the service area. Examples of such systems at an extremely high altitude are �satellite telephone system INMARSAT and IRIDIUM, which are extremely expensive and beyond repair geostationary satellites for communication.

Thus, as follows from the above, there is a need for cheap, located on high altitude platforms for wireless communications, and radar.

The present invention also relates to tourism. Visit high buildings, such as the Eiffel tower, high buildings, such as Empirestate building or high natural sites such as mount Everest, continues to be a regular activity for tourists. Indeed, recently there has been increased military interest in the expensive airplane flying at high altitudes. The recent award of the "X Prize" for safe flight at a height of 100 kilometers or more won by Space Ship One unit Bert Rutan, further pushing the commercialization of transportation nor greater heights. The problem with machines Space Ship One Space Ship and Two is that in their rocket engines use liquefied oxidizer nitrous oxide and other solid fuels on the basis of polybutadiene with terminal hydroxyl groups, an exhaust which produces soot, partially burned tires and other harmful materials. In recent publications it was stated about the development of alternative fuels for the machine Space Ship Two - asphalt and paraffin. There is a high probability that �that although it is cheap fossil fuels the combustion will be incomplete. The probability of generation of polluting products release in the case of asphalt, metal oxides, and acidic compounds of sulfur. The only influence of soot, which was recently calculated for 1000 launches per year by Martin Ross for Aerospace Corporation, speaks about the violation of the stratosphere and the rapid increase of temperature at the Earth's poles. Published frequency of starts means only a few times a week.

Because there is a growth market with cheaper and more frequent transportation of tourists to even greater heights.

Over the last few years of protracted skydiving as a sport has changed and now include wings, parachutes, acting on the principle of air flow, the use of auxiliary equipment, such as small hard wings, miniature surfboards, missiles and even a miniature turbojet engines. In addition, increased height at which skydivers jump, although it is limited to two main factors. Civil aircraft with wings and helicopters there are limited opportunities for work at high altitudes, which is provided on the half-hour limit for civil aviation for oxygen-enriched systems venting or the requirement for a sealed suit or cabin. Soon it is expected that for enthusiasts for�agnich skydiving will be available to civil airtight space suits with the development of high-altitude parachuting.

Now considered even more extreme form of skydiving. Suggested forms include jumping from the upper atmosphere or even into the atmosphere from space, which may be necessary if the inhabitants crashed orbital spacecraft have to safely return to earth.

Thus, there is a growing market for new high-rise platforms for a variety of new forms of skydiving. Indeed, there is also a constant demand for cheap platforms at heights of up to ten thousand feet.

Most recently, the fast delivery of the aircraft in places of military interest, has become almost a necessity for exploration or other purposes. In addition, increased interest in commercial ultrasonic transport. With this aim in many countries to meet these needs are developing a hypersonic aircraft with engines with supersonic combustion.

However, it was reported that the engines of this aircraft, designed for efficient operation at high Mach numbers, to run requires to achieve the speed, three times the speed of sound. To operate the motor in different flight modes from static to hypersonic requires very complex equipment associated with overweight�M. Besides using rocket boosters to achieve a starting speed, a different design path requires the use of the engine in two parts. The first part is a turbofan or turbojet engine, which prevails in the flight regime from subsonic to low supersonic Mach number, the transition to the engine at supersonic combustion at high Mach numbers and off of the first part.

Because the engines are designed to work only in the hypersonic range, many with no moving parts would be easier, simpler in design and therefore less expensive.

In 2003, U.S. manned spacecraft "Columbia" was destroyed when entering the Earth's atmosphere due to structural damage that occurred during the launch phase. In addition, over time is the accumulation of orbital aircraft requiring repair, accident victims orbital aircraft, as well as undesirable and hazardous waste, which must be removed from orbit.

Since aircraft such as the U.S. spacecraft Columbia, heavy, no main engines, which can operate for a long time after entering the atmosphere due to the dangers of overweight and portable cryogenic or other fuel used during the flight about�Ratno in the atmosphere, these aircraft must leave orbit in certain places, if they should be able to plan to multiple airports with landing strips of adequate strength and length, existing close to their orbital trajectory.

Therefore it is inevitable that others will create smaller aircraft, able to perform useful work outside the atmosphere with the possibility of flight with its own energy source in subsonic, supersonic or hypersonic long flight in the earth's atmosphere. They may very likely be run using the power of the rocket engine and re-entry into the atmosphere to fly to any of a large number of civilian or military airfields suitable for smaller aircraft and to land safely.

They will be used for a quick and safe return of passengers of the damaged orbital aircraft, repair, or removal of wrecked unmanned orbital aircraft, as well as undesirable and hazardous waste. Another option, which will soon go into operation, is a small utility vehicle for refueling and joining to the crashed spaceship and perform the role of a tug to extend the service life of such vehicles. Then a small vessel or missiles can be used to launch small satellites or modular components for assembling and filling the large structures in orbit that can be used to overcome the Earth's gravitational field for a possible deflection of hazardous asteroids or exploration of the Solar system. The European space Agency and its Russian equivalent of "Roscosmos" recently begun to consider the creation of a repair base in low earth orbit to facilitate missions to the moon or Mars with the use of modern aircraft returned (ARV), which has yet to be established.

It is also expected constant demand for service satellites and other orbital aircraft. Such service may include the delivery of food, fuel, compressed or liquefied gases for breathing and other applications, medicine and scientific materials, electrical, mechanical and other equipment for replacement or upgrade of vehicle systems, transportation of sick or injured personnel or replacement personnel.

It is therefore expected that there will be a need for a quick inexpensive means of launching modular components for Assembly and refueling in space, small utility boats, small satellites and other devices.

The sensitivity m�ogic telescopes used in astronomy, has deteriorated significantly due to atmospheric dust and aerosols, because the light is reflected and scattered them particles. The least affected telescopes are usually found on the tops of the distant mountains, well above the atmosphere, which is a large part of the dust and aerosols.

Therefore there is a need for high platforms, which can be installed sensitive telescopes. In particular, several platforms and telescopes can be used to simulate a telescope with a very large aperture, which are now being used to detect planets in other solar systems.

After the devastating tsunami happened in Indonesia in December 2004, it became clear that search on many of the affected areas and subsequent delivery of primary care was delayed for several days or even weeks after the incident, leaving many tens of thousands of people died; and the number of victims would have been much less if help would arrive sooner. There is therefore a need for a quick suborbital systems of rockets for the delivery of numerous small unmanned aircraft and saving thousands of tons of aid delivered by parachute, GPS managed at the last stage using a simple disposable rockets running GPS.

SU�of the INVENTION

Accordingly there is a need for method of delivery of useful materials, such as fuel gases for life support, etc. and products into the upper atmosphere and above, at such price per unit delivered mass, which is much lower than currently available on the market that uses the currently available materials and technologies. Furthermore, it will be helpful for the environment to minimize the mass of material used for the removal of the vehicle beyond the earth's atmosphere through the use of hydroelectric, geothermal or solar energy from photovoltaic panels to lift the vehicle as high as possible before igniting the engine or engines of the vehicle.

The aim of the present invention is to provide a launcher for missiles with a high frequency of starts useful for sending cargo into space, and also to satellites in space.

Another another objective of the present invention is to provide a launcher for missiles with a high frequency of starts, which can be used hydroelectricity or other renewable source of energy to lift the rockets to a height of tool.

Another object is the use of more environmentally friendly fuel and oxidizer, made using a�ternatively or renewable energy.

Another another objective of the present invention is to provide an upper rotating launch station, which uses electric starting truck, the starting station is attached to the ground by cables, which are attached to the balloons for tensioning and maintaining cables and associated structures.

An additional objective of the present invention is the provision of means of recovery of the potential energy arising from the return of empty trucks rockets to earth after starting the tethers through the use of regenerative braking with the use of motor-generators for reuse of this energy.

Another another objective of the present invention is to provide atmospheric control on a more permanent basis, because of elevated levels of greenhouse gases or other pollutants in the atmosphere lead to changes in global weather.

Another objective of the present invention is to provide a high radar platforms and platforms of radio communications for a significant increase cover spatial volume and surface area of the earth.

Another objective of the present invention is to provide regular, commercial, provide at a reasonable cost opportunities for tourists to visit the levels of the atmosphere, inaccessible to others�GIH funds with the exception of missiles, aircraft and free-flying aircraft lighter than air.

Another another objective of the present invention is to provide an higher platform than currently available, for a variety of new forms of skydiving from an extremely high altitude or space, and cheap platforms at heights of up to ten thousand feet, which can be reached without supplemental oxygen or high-altitude-compensation suits.

Another objective of the present invention is the provision of rapid, inexpensive means of launching a small business aircraft for safe return of passengers of the damaged orbital aircraft, repair, or removal of wrecked unmanned orbital aircraft, as well as unwanted and hazardous wastes.

Another objective of the present invention is to provide a high platform above the layers of clouds of the Earth, which may be installed, sensitive telescopes, especially those who can use computer tools to combine electromagnetic waves, including light and radio waves are received so as to act as a single telescope with a diameter equal to the distance to the most distant components of the matrix, to ensure the best opportunities neb�of Udine, than there are today, except for space telescopes.

An additional objective is the provision of facilities of satellites and other orbital aircraft, for example, for delivery of food, compressed or liquefied gases for breathing and other applications, fuel, medicine and scientific materials, electrical, mechanical and other equipment for replacement or upgrade of vehicle systems, transportation of sick or injured personnel or replacement personnel.

The aim is to provide a transport system for transporting the loaded missiles trucks along the ropes, going through the atmosphere to launch the station.

An additional objective is the provision of trucks for transport of missiles along the ropes to starting a station high in the atmosphere.

Another additional objective is the provision of apparatus for retention and referrals downloadable missiles trucks on the apparatus for moving the trolleys along the ropes to starting a station high in the atmosphere, and to move empty trucks from the starting station to the ground.

Another additional objective is the provision of a system for safe storage of missiles, as well as for the delivery of missiles or download missile trucks to the apparatus for transporting missiles or �agrogenic missiles trucks at the starting station, situated high in the atmosphere.

Providing apparatus for transporting loaded on the rocket trucks is also an aim of the invention.

Another objective of the invention is a system for the transportation of missile components missiles, trucks for missiles and/or holders of the transporting devices for missiles from the storage location for the installation of retention and assemblies for subsequent transportation to an apparatus for lifting the loaded missile truck to launch the station.

An additional objective of the present invention is the provision of transverse loader to load missiles on a truck.

An additional objective is the provision of a lifting Assembly for lifting the loaded missile truck to the apparatus for loading loaded missile truck raised a number of cables to station missile launch.

An additional objective is the provision of a tower for receiving the loaded missile truck and related equipment for the orientation of the loaded missile truck on the apparatus design guide for the location of the loaded missile truck on the ropes, aiming to launch the station.

Another another objective of the invention is the provision of devices to attach balloons to the system routing for stable retention and separation of cables designed to launch the station.

More about�aim of the invention is to provide a docking station for docking downloadable missile truck with a number of ropes, going to launch the station.

Power for transporting the loaded missile truck along a system of ropes to be raised to a height of launch station is another objective of the present invention.

Another objective of the present invention is the provision of lifting rings for lifting the loaded missile truck along a system of ropes on a dock.

An additional objective is the provision of a device for separation of cables from the ground to height of launch station and to stabilize the ropes.

Also the aim of the present invention is to provide a connecting apparatus for mounting frames and other apparatus to the ropes, coming between the earth and raised to a height of launch the station.

Securing system for holding the rockets inside the truck is also an aim of the present invention.

Another object is the provision of a mounting bracket of the telescope for use with a number of ropes held vertically in the atmosphere.

Do the rockets moved vertically in the truck to hold the person or persons, equipment and items is also an aim of the present invention.

An additional objective of the present invention is an improved hydrostatic compensation suit that must be worn man, h�Oba to withstand high acceleration during launch and return to the atmosphere.

These goals are achieved according to preferred embodiments of the invention, which are described below. Other objectives will be obvious to specialists in this field from the ideas of the invention, discussed below, as well as from the attached claims.

BRIEF DESCRIPTION of FIGURES

Fig.1 in schematic form shows some elements of a preferred embodiment of the system start-up of rockets of the present invention.

Fig.1A and 1B shows a detailed view of the elements shown in Fig.1.

Fig.2 schematic representation of the Assembly and basic bootable system missile according to a preferred embodiment of the invention.

Fig.3 shows how to load the missiles into the side of the transporting device according to the aspect of a preferred embodiment of the invention.

Fig.4 shows a schematic representation of another type of truck holding the rocket, the tilting mechanism and side carrying device.

Fig.5 shows a schematic plan tracking system for trucks, storage racks, stations retain and collect missiles, trucks, machine fuel storage and power supply system to prepare rockets for launch according to a preferred embodiment of the invention.

Fig.5A p�eveden enlarged detail view of part of the ruts, shown in Fig.5.

Fig.6 in schematic form shows how to load the missiles into the Bay filling or Assembly according to a preferred embodiment of the invention.

Fig.7 shows a detailed transverse view of the loader shown in Fig.6.

Fig.7A shows an enlarged detailed perspective drawing of the leg and the torsion of the locking pin shown in Fig.7.

Fig.8 shows a schematic view of operation of the lifting system of a preferred embodiment of the invention with a lateral transport device and trolley retention missiles.

Fig.8A shows an enlarged detailed view of one embodiment of apparatus for maintaining the turntable for rotation.

Fig.8B shows an enlarged detailed view of another embodiment of the apparatus for maintaining the turntable 72 to rotate.

Fig.9 shows a schematic view of the hoisting system, a rotating base, lateral transport device, truck parts according to a preferred embodiment of the invention.

Fig.9A shows an enlarged perspective view of a conical centering pin.

Fig.9B shows an enlarged perspective view of a fragment of the torsion lock pin.

Fig.9C shows an enlarged detail view of the base of the truck.

Fig.10 showing�n apparatus for receiving, alignment and start inserting the trolley holding the rocket, cable in/cable according to a preferred embodiment of the invention.

Fig.10A shows an enlarged detailed view of the separator of the cable.

Fig.11 shows another part of the preferred part of the invention relative to a cable system for transporting carts holding the rocket.

Fig.12 shows a detail of the upper part of the preferred form of the invention in schematic form, showing a set of balloons to lift a system of ropes and placed them parts according to a preferred aspect of the present invention for lifting the truck, holding the rocket.

Fig.13 shows a schematic view of the upper part of the preferred part of the present invention, which shows a part of a system of ropes and attached to various components.

Fig.13A shows a view of the truck rear end cover in the open position.

Fig.13C shows a perspective view of the end of the cart for use in the apparatus shown in Fig.13, and Fig.13C - type truck side view partly in section showing the operating positions of some of its components.

Fig.14 shows a schematic sectional view of a preferred embodiment of the invention, which shows the system�and cables and various attached parts.

Fig.14A shows an enlarged detailed view of the end portion of the grip truck.

Fig.15 shows a schematic view of a preferred embodiment of the invention, which shows a stabilization part for balloons and a system of ropes.

Fig.15A shows a detailed view of part of the stabilization portion of the balloon shown in Fig.15.

Fig.15B shows an exploded perspective view of the upper connection of the splitter to the cable, and Fig.15S - its top view.

Fig.15D shows an enlarged perspective view of the arrangement of the cables in the middle bracket of the separation unit.

Fig.15E shows an exploded perspective view of the lower connection of the splitter to the cable and a large sling.

Fig.16 shows a detailed schematic top view of a part of the stabilization part of the preferred form of the invention, in the direction 16-16 of Fig.15.

Fig.17 shows another detailed view of a part of the stabilization part of the preferred variant of the invention, taken in the direction 17-17 in Fig.15, which shows a certain force vectors.

Fig.18 shows a perspective schematic view of a stabilization system with pushers according to a preferred embodiment of the invention.

Fig.19 shows a perspective view of the stabilization device cables ACC�SSS to a preferred embodiment of the invention.

Fig.20A and 20B shows the types of side two of a large number of core sets of balloons attached to the system cables according to a preferred embodiment of the invention.

Fig.21 shows a perspective view of a multicore cable that can be used in cable/rope way start system according to a preferred form of the invention.

Fig.22 shows the design of the installation element to the side surface of the cable, as shown in Fig.21.

Fig.23 and 24 shows the species in the context of variants of the structure shown in Fig.22.

Fig.25 shows a sectional view of the clutch cable friction wheels of the drive to move the cable up or down according to a preferred embodiment of the invention.

Fig.26 shows a perspective view of a retractable bracket according to a preferred embodiment of the invention.

Fig.27 shows a detailed view of the exhaust bracket to hold the rocket on the truck according to a preferred embodiment of the invention.

Fig.28 provides a schematic view of the upper part of a preferred embodiment of the invention launches, if the top main lifting balloon or balloons will be installed telescope.

Fig.28A shows a perspective view of the upper part of Fig.28.

Fig.28� the detailed, enlarged sectional view of part of the apparatus shown in Fig.28, includes a toothed rotational drive system, and a support ring, and Fig.28C - direction 28C-28C of figs.28B, and in General shows how cables can fail.

Fig.29 shows a possible mounting bracket telescope for use in a variant implementation, shown in Fig.28, the image shown in a detailed perspective form.

Fig.30 shows a schematic view of a rocket to launch one person in a space suit according to a preferred embodiment of the invention.

Fig.31 shows an embodiment of missiles for multiple separately detachable capsules or people in the suit.

Fig.32 shows a man in a suit on a detachable frame return to the atmosphere with an air tip to initiate an acoustic wave.

Fig.33 shows another variant detachable frame return to the atmosphere with an air tip to initiate an acoustic wave.

Fig.34 shows a schematic view of the suit's got to carry the passenger according to a preferred embodiment of the invention at the exit from the atmosphere and return to the atmosphere.

Fig.34A shows a detailed view of the helmet of the spacesuit, is shown in Fig.34, and Fig.34B is another detail view of the helmet of the suit of Fig.34.

Fig.35 shows an apparatus for �from the strange methods of changing the internal volume of the suit, shown in Fig.34.

Fig.36 shows a detailed view of the finiteness of man and parts of the housing shown in Fig.34.

Fig.37 and 38 shows aerospace mounts available with the option of returning to the atmosphere missile systems installed on top of missiles, one with protruding wings and one with wings folded for transportation inside the truck according to a preferred embodiment of the invention.

Fig.38A shows an illustrative representation of the aerospace vehicle with a monocoque body with folded lifting and control constructions with a preferred embodiment of the invention.

Fig.39 shows a schematic view of a satellite or other payload carried on the missile according to the preferred embodiment of the invention with a resettable, aerodynamic, protective shells.

Fig.40 and 41 shows a perspective view and a sectional view of the rod in the form of a type of cable that will be used instead of a wire.

DETAILED DESCRIPTION of PREFERRED embodiments of the INVENTION

A preferred embodiment of the invention are initially described in General terms with reference to some components, described in more detail below. The shared components shown in outline in Fig.1, 1A and 1�. The preferred implementation option is a system of missile 1, comprising apparatus for moving the launching of the missile 18. The missile 18 is located either in a container or transport device of the rocket, such as truck 20, or loaded into the cart 20 from the storage racks 7. The trolley 20 has a cylindrical longitudinal hole open in a continuous pressure-resistant and temperature pipes 836 (Fig.13, 13C), which are located and held in position for the reception of the missile 18. Truck 20 are sealed and have a longitudinal axis which is also the longitudinal axis of the tube 836. The 18 missiles, their components, and truck 20 that can be loaded or not loaded missiles at 18, moved to the storage racks 7 with the corresponding transport railway carriage along the path 3 to the discharge zone 5. The crane 48 port respectively rockets 18 and/or the trolley 20 and/or component of the missile 18 is moved or used to hold the various parts of the system launch 1 at a relatively narrow crane tracks 78. Rockets 18 can have feathering 21 (Fig.7), and each cart 20 has internal support in addition to the tube 836.

Cross loader 50 is moved on tracks of the 90 in the directions shown by arrows A in Fig.1A, with gauge 90 are spaced farther from each other than crane gauge 78. The cross�th loader 50, which is preferably used to move missiles 18, 20 trucks, etc. with racks for storage 7 compartments for Assembly or refills 10 includes trolley 92.to move on tracks of the 90, and has a wheeled trolley 98 moved by a pair of transverse parallel rails 97 on top of the beams 96, and lifting device 100 attached to a wheeled trolley 98. The crane 48, which preferably is used to perform maintenance of the system start-up, can also be used to relieve the rockets 18 and/or 20 trucks, etc. with racks for storage 7, and the transfer of missiles 18 and/or 20 trucks in the compartments of Assembly/10 refills (should typically be a large number of compartments of the Assembly 10). Lifting device 100 is moved along the rails 97 in the direction of the arrows V. the Trolley 20, which can be loaded or not loaded rocket 18 in one way or another, is placed in compartment Assembly 10. The whole system is under the control of the corresponding control equipment local control start or bunker management systems 120.

According to Fig.1A and 2 lateral conveying device 46 moves the cart with 20 loaded on it with rocket 18 along the row lines 17 arranged on the tracks below ground level 14 and 14A located between the vertical walls 16. Path 14A (also shown in Fig.5) leads � a closed path 15, where there are 17 gauge. Lateral conveying device 46 move in the direction shown by arrows C. the Lateral conveying device 46 carries the cart 20 with the rocket 18 launcher 119, comprising a lifting device 60. Lifting device 60 shown in Fig.8 and 9, includes an upper rotating mechanism 61. Truck 20 rises to the mechanism of the turntable 63 above ground level. The turntable mechanism 63 includes the base of the turntable 122 and tower unit 123 (Fig.8, 10, 11). Tower unit 123 includes the turntable 72, the lower guide tube 124 and the secondary guide structure 125, the latter is functionally linked with a number of the main power cables and conveyor cables 27.

The main cables 27 are suppliers of electrical energy for downloadable missiles 20 trucks which are being transported. Electrical energy may be provided by one set of electrically conductive cables, and the truck 20 can be transported with a second set hard transport cables. However, power lines and transportation lines missiles were combined into a single set of core power cables and conveyor cables, which act simultaneously as carriers of electrical energy and means of support missiles (preferably on t�the pups to a great height and from a great height). Primary cables 27 has a lower end portion of the secondary guide structure 125, or near it, or the mechanism of the turntable 63 and the upper end portion which during use is located on high altitudes. These main power cables and shipping, major cable 27 should preferably be three to transmit three-phase power supply. Primary cables 27, shown in Fig.1, 1B, 11, 12, 13 and 14 are attached to the docking station 166, from which the secondary set of cables/wires 184. Cables 184 functionally direct the Assembly of the lifting ring 182, which is configured to the desired height above the docking station 166 after adjusting the pre-selected starting azimuthal angle when the truck 20 is located in the block lifting ring 182 and an upper annular portion 172 of docking station 166. After lifting out of engagement with the upper annular portion 172 and is released from the end grip truck 196, block lifting ring 182 is configured to pre-selected starting corner spot. Block lifting ring 182 is located above the docking station 166 and is situated at a considerable elevation to perform the last step of firing rockets 18, as described below.

Cables 27, 184 and any other cables are supported in the upper layers of the at�of ospery balloons near 164 and 160, consisting of a sheath that holds a gas lighter than air. These balloons 164 joined to the main cables/wires 27 intermittently along the length of the specified main cables/wires 27 for aggregate hold its own weight in a specified set of basic cables/wires 27, and the design, the portable and specified the main cables/wires 27. Balloons 160 support the otherwise unsupported portion of the cables/wires 27 and any attached structures, all structures and assemblies from the docking station 166 to these balloons 160 and pull the cables 27 and 184 so that they could carry the payload. Cables 27 are separated from each other by a number of spacers and blocks stabilize 158. (In much of the previous description of the cables shown in the form of wire ropes, however they can be rods, as explained below).

Each assembled rocket 18 on the trolley 20 is transported from compartment Assembly 10 in the lower guide tube 124, then the secondary guide structure 125, and from there to the docking station 166 using the friction of the actuators 26, which include electric power apparatus 168. The clutch actuators 26 can include a set of friction wheels of the drive 26A attached to the apparatus for converting electrical energy into mechanical EN�Liu and for inter-connecting mechanical and electrical devices. Thus, a set of gears in the gearbox G can be functionally connected to the electric power apparatus 168. The latter may include a motor-generator M-G, functionally connected to the gear wheels in the gear G, as shown in Fig.9C, 15C and 25. The clutch actuators 26 are embedded in the cart 20. The trolley 20 is moved along, and the electric power apparatus 168 receives power from the main cables/wires 27, as when the cart 20 is lifted (or climbs) cables/wires 27, and other cables/ropes attached to them, as described below, using the friction of the actuators 26. The own weight of the cables/wires 27 and all stationary attached to the cables/ropes elements periodically compensated by balloons 164 strained and held by 160 balloons. Wheel friction drives 26A and an electric power apparatus 168 (includes gears in the gearbox G is connected to the motor-generator M-G) convert electrical energy into kinetic energy to power electrical apparatus power 168. It is desirable that the latter was reversible electric power apparatus for converting the potential energy into electrical energy when lowering the truck 20, and the transmission of electric energy on the transmission line that is part of the cables/wires, which move�truck is 20. If the trolley 20 requires electrical energy to lift, wheels 26A are driven by an engine-generator M-G via a Converter apparatus, such as a set of gears in the gear G, which rotate in response to receiving power from the motor generator M-G. When the cart 20 is lowered under the action of gravity, friction drives 26 act as a recuperative brake and affect the gears in the gearbox G (or any other device for converting mechanical energy into electrical energy). Balloons 160 and 164 preferably have sloping sides, as shown in Fig.1, 11, 20 and 28; a cylindrical part, as shown in Fig.20V, or may be spherical, and also have other shapes. High altitude balloons are well known, are constantly evolving and improving. Matching balloons 160 and 164 should preferably remain functional in applications of the present invention many months, and optimally - years. Balloons to move into the stratosphere known and used since the 1950s. Truck 20 is raised further by secondary cables/cables 184 and rotates, and is then inclined at a predetermined value, as described below, after which the missile 18.

The above description provides an overview of the components of the preferred VA�Yanta of the invention. Below is a more detailed description of the invention in the preferred form of its embodiment.

Rockets 18 and their corresponding payload is collected, loaded on a truck 20, refuel if necessary and stored in explosion-proof compartments of the Assembly 10 prior to starting. Each compartment 10 is located below the ground surface and constructed so as to limit damage in case of accidental detonation of the fuel of the rocket 18. Each compartment 10 is brought to the surface in the form of an inverted truncated cone 12, as shown in Fig.2 and 11, is made of the corresponding concrete or similar material to limit the consequences of any explosion by reflecting it upwards and sideways. Each compartment 10 is connected using the way below ground level 14 and 14A to a closed path 15. The path ends 14 is inclined open trough 86 (Fig.6) sloping vertical wall 16A (Fig.2) facing the side hole of the cover Assembly 10. It reflects any lateral components of a possible explosion from the compartment 10 up and away from the supporting structures (structures, equipment) for system 1 and start from the staff. Then the path 14 is rotated about 90 degrees to connect with the path 14A. Each compartment can hold 10 rocket 18 in truck 20. Each rocket 18 may include a motor short-missile userflags ejection of the missile from 18 open continuous pipe 836 (Fig.13A) on the trolley 20 with such speed, so even if the main rocket engine ignition miss, short booster rocket engine and the rocket 18 will not fall and will not harm the system launch 1. Booster rocket engine will only work in resistant to the temperature and pressure within the container in which it is held, as described below. Each rocket 18 has one or more engines for the launch of missiles on 18 design speed.

Each trolley 20 has opposite end openings 24 (Fig.9C, 13, 13A) and swivel end caps or outlet of the membrane 30 (Fig.9C, 13, 13A) at its both ends to protect the 18 missiles on the cart 20 when the truck 20 is moved from the earth through the atmosphere. These covers 30 may swing to open both ends of the truck 20 or the membrane 30 is allowed to be similarly open both ends of the cart 20, as shown in Fig.13A. On the opposite end holes 24 are reverse thrusters with variable step 31, which is suspended on hinges parallel to one side of the truck 20 so that they can be rotated to a position perpendicular to the ends using drive mechanisms 29 (Fig.13C, 13C). Each trolley 20 has a multiple of three the number of friction of the actuator 26 (Fig.9C) that are installed at an equal distance around the perimeter of the truck 20, for dragging and dropping truck 20 up finding�I at an equal distance power cables 27. Cables 27 and 184 are of a suitable high tensile strength and conductivity, as described below. The clutch actuators 26 are powered from the described above three are installed at an equal distance from each other power cables 27, and these cables 27 carry three-phase power, from which the clutch actuators 26 are powered. The clutch actuators 26 are reversible, use the power for lift truck 20 or generate electrical energy when used as regenerative brakes. The clutch actuators 26, operating in regenerative braking mode, convert potential energy of the cart 20 when it is lowered into the electricity supplied back to the cables 27, wherein the recovered electricity can be used to help raise other loaded truck in the adjacent systems start 1. Friction drives 386 (Fig.28) and 26 (Fig.9C) work in a similar way. The inner part of the truck 20 has a construction capable of withstanding the heat and the consequences of the explosion caused by a short-term booster of the rocket engine. The end caps or membrane 30 (shown in detail in Fig.9C and 13A) protect the rocket 18, held on the trolley 20, from any adverse weather conditions, and can be used to hold or inert relates�the comparatively inert gases inside the truck 20, surrounding the rocket 18, such as nitrogen, to inhibit combustion of any reactive material coming out of the rocket 18 during transport to the high position of the tool. The upper end of the truck 20 may have a locking socket for the torsion of the finger 32 (Fig.13A), such partial nests rotating torsion of the fingers 154 (Fig.9) (described below) for receiving the torsion fingers 204 (Fig.12 and 13), such partial rotating torsion of the finger 144 (Fig.9) (also described below), which are used for lift trucks 20 in preparation for the process of the launch, described below.

Each trolley 20 has an inner idler brackets 34 or 35 (Fig.26, 27), which securely hold the rocket on the cart 20 so that the centers of gravity 36 and 37 (Fig.13) truck 20 rockets and 18, respectively, are consistently in the center of the truck 20 in its center of gravity. Small elastomeric or pneumatic wheel 372 (Fig.27) can join the perimeter of the rocket to avoid frictional contact between the missile and the inner part of the trolley 20 at the time of release, if the vector of the thrust of the rocket does not pass exactly through the center of gravity of the rocket. Idler brackets 35 and associated parts are described below.

According to Fig.3-6 there are different ways of loading missiles 18 on the carriage 20. In one embodiment, the missile 18 initially going horizontally, �was in the cart 20 and initially placed on a wheeled loader 38 (Fig.3) in the direction of shown by the arrow D. the Cart 20 is then placed on a hydraulic rotator 39; rotator 39 having a hydraulically or otherwise rotating support base 40 mounted between the uprights 41 for rotating the fingers 42 using, for example, a hydraulic actuating mechanism 43 (or other suitable actuating mechanism). The piston rod of the hydraulic actuating mechanism 43 is almost entirely inside the cylinder when the cylinder 20 only went over the piston and the cylinder. In each of the four corners of the base 40 is provided by the counterweight 44 so that the center of gravity of the base 40 coincides with the axis of rotation of the fingers 42 and the center of gravity of the Assembly of the missile 18 and truck 20, thereby reducing the force exerted hydraulic actuator 43 or other means of rotation. Rockets 18 may be pre-placed on a horizontally oriented truck 20.lateral conveying devices 46 (or similar conveyors) before rotating to a vertical position by a hydraulic rotators 39, or 18 missiles can be placed in a vertical truck 20, previously located on the lateral conveying devices 46 in the compartments of the Assembly 10 through the portable loader 50. According to Fig.6 for carrying empty trucks on 20 previtellogenesis lateral conveying device 46 (as explained below) compartments of the Assembly 10 can be used cross loader 50 or crane 48, after that, the loader 50 or crane 48 is immersed rocket 18 on the cart 20.

Lateral conveying device 46 shown in Fig.1-6, 8, 9 and 10. Lateral conveying device 46 is moved along the track 14, 14A and track 15 of the 17 tracks. Track 15 form a closed loop, passing under located above the ground level of the turntable mechanism 63 (Fig.1A, 8, 10, 11, described below), which are moved truck 20, each of which is immersed rocket 18, explosion-proof compartments of the Assembly 10 to a lifting unit 60, as shown in Fig.2 and 8, and also move an empty truck 20. Each lateral conveying device 46 has a platform 54 (Fig.9) usually with a triangular recess 56 (Fig.2, 4) for inserting the end of the truck 20 to truck 20 is in a vertical position, and the upper edge of the truck 20 was part of the recess 56. Shown lateral conveying device 46 having independently driven wheels 58 (Fig.9) to move the lateral conveying device 46 on the tracks 17 and has an associated steering mechanism to the lateral conveying device 46 could be moved along the ways 14 and 14A, as well as track 15. To lock the trolley 20 in the recess 56 of the platform 54 is provided corresponding to the locking mechanism, which can be tapered alignment pins 142 (Fig.9, �opisyvayutsya below) and partial rotating torsion fingers 144 (Fig.9, are described below). In lateral conveying devices 46 have nests that are on the bottom of the trolley 20, to insert the centering fingers and partial rotating torsion of the fingers 144, as explained below, for detachable fastening devices 46 to the upper rotary mechanism 61. which, as stated above, is a part of the lifting unit 60, which will be described below.

Along the side of the track 15 on the storage racks 7, separated by a wall 64 houses a number of 18 missiles and their variants, other items, such as lateral conveying device 46, the trolley 20 and options such as tourist sealed truck and service truck start system. Rockets 18, if they do not use solid fuel, can refuel during storage on racks preferably 7 or in the compartments of the Assembly 10 using various combinations of propellant, such as liquid-liquid or liquid-solid fuel, depending on the type of missile 18. One of the combinations of fuel with high specific impulse is liquid oxygen (LOX) and liquid hydrogen (LH2) that can be stored in tanks storage 65 and 66 respectively, as shown in Fig.5.

Fuel combination can create the most environmentally friendly way using a system in which one or �number of turbines transmit mechanical energy and perhaps other turbine power electric generators 62, included in the power unit 468. Turbine(s) receives(s) water from an appropriate source such as a river, under sufficient pressure and with sufficient mass flow for electrical substation 70 from the coupled electric generator 62. and directly power the compressors in plants liquefaction of gases, such as substanance water electrolysis and liquefaction of gases in the installation of 74. The electricity from the substation 70 can be used for substance electrolysis of water in the installation of 74 and may be used to provide auxiliary power to substance liquefaction, driven by the turbine, the installation of 74 for liquefying the resulting oxygen (O2) and hydrogen (H2), which are stored respectively in the tank storage 65 and LOX tank LH2 storage 66, in addition, electricity is used to power all of the other parts of the launch system 1 and its supporting equipment requiring such energy. Alternatively can be used other sources of energy such as nuclear fission, if not available hydroelectric power and energy from turbines. Preferred is the use of renewable energy sources, such ka� geothermal, hydroelectric and solar.

As explained earlier, rockets 18 are transported to a land on trucks 20. Lateral conveying device 46 can move along the paths 14 and 14A, as well as track 15 on the relatively narrow parallel rails 17 (compared with the ruts 90, which will be described below). Empty cart 20 on the storage rack 7 is shown in Fig.5 and 6 near empty lateral conveying device 46. Fig.5 also shows an embodiment tourist sealed truck, variant means a service truck, truck with a spare balloon or aerospace plane for space tourism 76. Gauge pair of tracks 78 and 90 (described below) (Fig.5 and 6) running parallel to the direct opposite parts of the path 15, are used to move the crane 48 portable and wheeled loader 50. Empty truck 20 is shown above the lateral conveying devices 46 moving along the track 15, with which they can be removed for repair or re-load.

The loading system is shown in more detail in Fig.6. On the storage racks 7 are either equipped with 18 missiles and/or components of the rocket 18, shown as missile parts 18A, 18B and 18C, and/or aerospace plane for space tourism 76 (Fig.5) and/or empty truck spare 20 or side lift truck�e device 46. Missile units 18A-18C can be combined to obtain the final 18 missiles, but it does not limit the invention. Rockets 18 with the relevant parts of rockets 18A-18C are routed to their respective positions using rails 3 (see Fig.1), with 18 missiles, missile units, etc. can come from remote production sites worldwide. The trolley 20 and the lateral conveying device 46 is also shown on the racks 7. The crane 48 may move on the rails 78 to assemble the parts of rockets 18A-18C in the compartment inside the storage racks 7, and then into one of the trucks 20. The crane 48 may also be used to service routes 14 and 14A, as well as track 15. The crane 48 is a cable 49. The crane 48 by means of a cable 49 and the corresponding lifting mechanism can lift the assembled rocket 18 and transfer it into the compartment 10 (left part of Fig.6) for insertion into the pre-placed cart top 20 on the lateral conveying device 46. The crane 48 is needed in addition to the other aforementioned maintenance equipment for maintenance of the ruts 17, 78, and 90, and rails 97 (described below). Care must be taken when using tap 48 to transfer missiles 18, because the crane line 49 can swing while you move, which can lead to damage of the rockets, suspended on a rope 49.

As objasnjenje, there is always the danger of accidental detonation of the rocket 18 in the compartment 10 when using highly reactive combinations of fuel and oxidizer. For protection of various structures, equipment and personnel from the effects of explosion, such as detonation, with the opposite edges of the cage 10 is placed a pair of parallel, inverted l-shaped guides 80 (Fig.6). Each pair of guide 80 has penetrating 82 advanced in the direction shown by arrows E, penetrating 82 slides under the overlapping flanges 84 of guide 80 before refueling. Penetrating 82 after placement under the flanges 84 cannot be moved even with the explosion. Penetratio 82 is made of a material that is not destroyed, even if it needs to withstand an explosion within the battery compartment 10 during Assembly, filling or other activities, while the explosion is directed away from critical components with the help of chute 86.

Cross loader 50, shown in Fig.1 and 6, is part of a system load of 88 missiles, including a couple of wide lines 90 (wider tracks 78 for crane 48), which moves a pair of wheeled trolleys 92. The rail Assembly 94, comprising beams 96 and wheeled trolley 92, goes through a broad gauge 90 and moved on trolleys 92, which move along the broad lines 90. The rail Assembly 94 has parallel �else 97, shown in Fig.7 on top of the beams 96, which moves the lifting Assembly 100. The whole unit cross boot top 50 on the rails 90 is similar to passing on top of an overhead bridge crane with trailer trolleys. Parallel guide beams 96 are attached to the trolleys 92. Wheeled trolley 98 moves along the parallel rails 97, as shown in Fig.1, 1A, 6 and 7. Portable loader 50 includes a lifting device 100 shown in Fig.7, with the guide holder 101 and the lift 102, which can move up and down as shown by the arrow F on the holder 101, by means of suitable Electromechanical means, preferably with a counterweight. Portable loader 50 shoots rockets 18 or empty truck 20 or their variants or truck 20 that holds different types of missiles 18 or with various components of the storage racks 7, the compartments of the Assembly 10, with which the lateral portable device 46 is transported fueled rocket 18 to 20 trucks or other embodiments, trucks launcher 119.

Also with reference to Fig.7 shows another embodiment of a detail of the upper part of the transverse loader 50 in a slightly altered form. As mentioned above, transverse loader 50 has a lifting device 100 with the holder guide rails 101, in which the lift 102. The holder 101 is shown with p�tiopronin the protrusions 103, allows you to attach the holder 101 to a wheeled trolley 98 to move the lifting device 100 along the rails 97 up on the beams 96. To engage the missiles 18 for lifting the lifting device 100 has dependent legs 105, at least three (preferably) for stability, which is attached to the housing 106 attached to the bottom of the lift 102, which allows to lower the gripping unit 104 in the compartment Assembly 10, as shown by the arrow G. the Legs 105 may move radially in the guide rails 110 (as shown by the arrows N in Fig.7A) relative to the rocket 18, located between the legs 105, so you can install missiles of different diameter. Partial rotating torsion finger 111 or other means of attachment to the rocket 18, is located on the free end of each leg 105, and the upper part of the rocket 18 is located at an equal distance from each other nest for partially rotating torsion of the fingers 109 or other nests for other means of fastening for insertion of the respective partial rotating torsion of the fingers 111 to provide secure mounting of the missile 18 to the lifting Assembly 100. Jacks fingers 109 are located in the bow 19 of the rocket 18, generally parallel to the longitudinal axis of the missile 18. Jacks fingers 109 may have access covers 113, attached to the nose 19 18 missiles, however, can be removed from the solicitation�existing sockets 109, if necessary, provide access to the socket 109, and also have a smooth surface for the rocket 18, when nests fingers 109 are not used to reduce aerodynamic drag when the missile is in flight.

Upper and lower units stabilizing brackets 114 may be provided to stabilize the rocket 18 during lateral movement of held-lifting Assembly 100 when driving along ruts rails 90 and 97. Each block stabilizing bracket 114 has a hydraulic or other actuating mechanism 115, which is attached to the bracket 116 of each block of brackets 114. The brackets 116 can rotate along the paths shown by arrows I. the free end of each bracket 116 is provided eyelet 117 for insertion into a corresponding slot 118 in the rocket 18 for receiving each of the lugs 117.

As described earlier, Fig.6 shows a lateral conveying device 46 with the loaded truck 20 holding the rocket 18 moving along the path 15 in the direction of launchers 119, which is described below. Another lateral conveying device 46, which carries the empty cart 20 is moved from the launcher 119, which sent a rocket with 18 truck 20 at high altitude, moving along the path 15, returning an unoccupied compartment of the Assembly 10 to re-download the 18 missiles or returning to the storage rack 7 for ops�of uzivanie if necessary.

Referring again to Fig.5, the system of missile 1 additionally includes launcher, 119. Bunker local launch control 120 controls the operation of the system of missile 1, directing the flow of electrical energy to adjacent starting systems 1 and from energy sources, such as power plant 468, or other surrounding systems of the missile 1, and includes computer systems of management and control, uses data from various measurement devices and imaging, located at different places the trigger system 1. Here is usually a staff for local control system of the missile 1 and coordination of launches from other parts of the group launch systems to minimize power consumption.

Lifting device 60 is located below ground, as shown in Fig.2, 8 and 9. Lifting device 60 may have a lifting mechanism, such as hydraulic piston rod 68, which sits turning the upper block 61 (Fig.9) for rotation with the rotary actuator 134 truck 20 with the rocket 18 on it, loaded on the lateral conveying device 46 in the direction shown by the arrow J. the Lifting system 60, described in more detail below with reference to Fig.8, includes a stem 68 having a broad, non-rotating bottom base 135, attached to the stem 68 that is set to hold the top�th rotary unit 61. Turning the upper unit 61 consists of a rotating support base 136 (plot table 141) mounted on top of the lower non-rotating base 135 (which is not part of the mechanism of the turntable 63).

Look at Fig.8 and 9. The piston rod 68 is part of the piston 67 extending from a hydraulic cylinder 69. The hydraulic cylinder 69, the piston 67 and the rod 68 will not rotate.

The above hydraulic system is not the only option to actuate the lifting mechanism. Electromechanical system can form a linkage.

Turning now to Fig.10, the mechanism of the turntable 63 is the aboveground part of the launcher rockets 119 for receiving the loaded missiles 20 trucks with lifting device 60, and shows their orientation for transportation. Moving the loaded rocket truck up 20 shown by the arrow L. As mentioned above, the turntable mechanism 63 includes the base of the turntable 122 and tower unit 123. The base of the turntable 122 is fixed to the ground.

The rotating platform 72 may be quite heavy, weighing several tons and be based on design, able to withstand such a heavy weight, to withstand lifting and lateral forces, and smoothly rotate. Details of a suitable support device steering�a combined platform shown in Fig.8A.

Fig.8A shows the base of the turntable 122 having a horizontal surface of the base of the grip of the wheels 270 for gear wheels 284, vertical tubular portion 272, horizontal, annular flange 274, reaching out towards the outer circumference of the base of the turntable 122. Turntable 72 is going down the tubular portion 276 on the perimeter of the turntable 72, which is oriented inwards horizontal annular flange 278 having a number of holders of the axes of the wheels 280, 281 and 282, running towards the base of the gear wheel 270, vertical tubular portion 272 and a horizontal annular flange 274, respectively. Each holder axis 280, 281 and 282, respectively, holds the wheel axle 284, 286 and 288, respectively. The wheels 284, 286 and 288 are moved on the base surface of the gear wheel 270, vertical tubular portion 272 and a horizontal annular flange 274 to provide a smooth circular rotation of the turntable 72, shown in Fig.8 by the arrow K. as an alternative (see Fig.8B) the base of the turntable 122 may have a horizontal support base 290, a vertical tubular portion 291 and the horizontal annular flange 292. Similarly, the turntable 72 alternatively may be going down the tubular portion 293 and running inside mountains�horizontal annular flange 294. Between the horizontal annular flange 294 and a support base 290 and a horizontal annular flange 292 is the number of rolling bearings, such as balls of ball bearings or crossed rollers 295, moreover, there are two corresponding annular support surface, such as grooves 296, to ensure the rotation of the turntable 72 with reduced friction as compared with the case where the bearings are not used.

Turntable 72, depending on the size of the truck 20 may have a diameter of about 46 feet. For example, if the tubular inner part of the truck 20 to hold the rocket 18 has a radius of 8 feet, and the minimum thickness of the trolley 20 holding the rocket is 2 feet, with a gap located at the center of the cart 20 size 3 feet, a diameter of the turntable 72 will be about 46 feet.

For a fairly modest internal diameter of the tubular portion of the truck 20 for holding the rockets 18 size 16 feet, the inner diameter of the truck plus modest (∆=2 ft) clearance for construction of the trolley 20 and the tolerance of 3 feet (δ=3 feet), the facility has provided the rotation of the turntable 72, the diameter of the turntable 72 is about 46 feet, and the flat side 22 of the truck 20 is approximately 34.6 feet.

Tower block 123 is located on the ground level, above the subfloor 136 (Fig.8), Opir�is at the base of the turntable 122 and limited by them. A vertical axis of rotation of the tower unit 123 coincides with the axis of the lifting unit 60. Lower guide tube 124 has a hole 71 for receiving the loaded rocket truck 20 from the side of the portable device 46 through the opening 73, as shown in Fig.10, through the turntable 72 and the base of the turntable 122 by means of a hoisting unit 60. The rotating support base 136 (Fig.8, 9) has a conical alignment pins 142 and partially rotating torsion of the fingers 144 to lock with the possibility of releasing the lateral conveying device 46 of the trolley 20 on it to the mounting base 136. The cart 20 is fixed with the possibility of releasing a similar way to the lateral conveying device 46 with the aid of centering pins 142 and partially rotating torsion of the fingers 144. When the blockage with the possibility of release, the cart 20 can be driven, as explained below.

Again referring to Fig.8 and 10, tower unit 123 further includes a rotating platform 72 from rotating relative to the base of the turntable 122 in the direction shown above the arrow K, the collar 126 having a pair of parallel, spaced brackets 127 which can be rotated on the hinges on the rotating platform 72. Between these brackets 127 is lower eg�flausa pipe 124 (also part of the tower block 123). A pair of horizontal coaxial pivot pins 128 out of each bracket 127 and enters the opposite wall of the lower guide tube 124, lying in a pair of supporting elements 129. Internal guides truck 133 run along the inner cylindrical wall of the lower guide tube 124 and spaced from each other by 120° to enter the set angular grooves 130 (Fig.9), extending in the longitudinal direction along the corner edges 20 trucks. Angular grooves include friction actuators 26. Lower guide tube 124 and the secondary guide structure 125 is pivotally rotated by the rotational path of the arrow M in Fig.8 using a suitable rotational drive system around the same horizontal axis defined by the fingers 128. Each of the brackets 127 are described below includes a counterweight 131. The Central point of the lower guide tube 124 is positioned vertically above the rotating platform 72 tower unit 123 to the axis of rotation of the turntable and the lower guide tube 124 intersect orthogonally. A vertical axis of rotation of the turntable 72 is coincident with the axis of the lifting device 60 and any lateral conveying device 46 and the truck 20.

Secondary guide structure 125 has a single-piece pipe 143, which holds�I at a fixed distance from a common point of rotation of herself and of the lower guide tube 124. Thus, the secondary guide structure 125 is balanced on its horizontal inflection point and has internal guides truck 138 built-in inside of the pipe. The lower end of the solid pipe 143 secondary guide structure 125 may be aligned with the upper end of the lower guide tube 124, so that the pipes are coaxial, aligned internal guides are also truck 133 and 138. Lower guide tube 124 may rotate about coaxial pivot pins 128 and rotates until then, until the outer surface reaches the stop 132 (Fig.10) extending from an integral pipe 330 so that the guides truck 133 and 138 are aligned. Guides truck 133 and 138 are powered the same way as power cables 27 (described below), so that the clutch actuators 26 of the cart 20 can use the energy. The upper end of the pipe of the secondary guide structure 125 has an internal transient attachment point for the main cables 27 to cart 20 could be moved from the internal guides of the trolley 138 on the main cables 27.

As shown in Fig.2, the lateral conveying devices 46, each loaded truck 20 holding the rocket 18, moves along the path 15 from the compartments of the Assembly 10. The cart 20 with the missile 18 is removed from the track 15, is transferred to the launcher at�the climate rockets 119, and after the missile launch empty truck return empty lateral conveying device 46, then put on the track 15, which is returned to the compartments of the Assembly 10 or the storage racks 7.

Again referring to Fig.8-10, the lifting unit 60 raises or lowers the cart 20 with a lateral conveying device 46 attached to a rotating support base 136, by raising the piston 67 and the rod 68 in the direction shown by the arrow N (showing the direction of lifting and lowering) to move the truck 20 in the lower guide tube 124 and away from the turntable 72. The rotating support base 136 has the following structure for releasable attachment to the lateral conveying device 46 for exact alignment of the friction of the actuators 26 of the cart 20 with the respective inner rails truck 133 of the lower guide tube 124.

The lifting unit 60, the lateral conveying device 46 and the carriage 20 is shown in more detail in Fig.8 and 9. The hydraulic piston 67 at its upper end has an upper rotatable unit 61 composed of a non-rotating lower support base 135, the upper rotating support base 136 and section of the table 141. Lateral conveying device 46 can move in a place located in the center in relation to lifting and�regatta 60. As mentioned earlier, it is likely that the tracks 17 are wider than traditional rail track. Tapering cone-up alignment pins 142 (shown as four) (shown in detail in Fig.9A) from the plot table 141, and as a partial torsion fingers 144 (shown as four) (shown in detail in Fig.9V). They are connected with a lateral conveying device 46, as explained below. Of course, the position of the respective fingers/pins 142 and 144 and the corresponding sockets can be swapped with lateral conveying devices 46 on the plot 141.

Turning the upper rotatable unit 61 of the unit 60 is mounted on the rod 68 and may rise, as shown by the arrow N to the lower conical alignment pins 142 and partial turning of the torsion fingers 144, shown in Fig.9, could enter into the appropriate slots of the centering pins 152 and socket torsion fingers 154 in the lateral conveying device 46.

The upper surface of the lateral conveying device 46 has an upward tapered alignment pins and partial pivoting fingers, which is almost the same as the lower conical alignment pins 142 and partial turning of the torsion fingers 144 coming from the top section of the table 141. On the lower surface of the carriage 20 before�appropriate slot therein for centering the pin 155 and the socket for the torsion of a finger 153 for receiving a conical centering pins and partially rotating the fingers on top of the transport device 46 for mounting truck 20 to the lateral conveying device 46 with the possibility of separation.

Lateral conveying device 46 has four wheels 58, positioned and shaped to slide on electric rails or tracks 17, and includes gauge 17 adjoining table 141, in addition, has the capability of independent alignment, as mentioned earlier. Lateral conveying device 46 can be powered from an electric rail 17 like electric trains or trams (which are connected to the power source) or some other on-Board power sources such as fuel cells or internal combustion engines.

Lower guide tube 124 has an inner rails truck 133 (Fig.8, 10) included in the angular grooves 130 that runs along the vertical lines of contact of the sides 22, also shown in enlarged form (Fig.10) truck 20 so that the friction drives 26 each trolley 20 is moved per truck 20 truck along the rails 133, and to preserve the orientation of the trolley 20 in the lower guide tube 124. Provides friction drives the carriage 26 for engagement of the main power cables 27. Friction drives the carriage 26 is in the mechanisms cross section which partially covers the main cables 27, which are moved t�maturation 20, from which they receive energy or which they transmit energy. Referring to Fig.15C shows one of the friction of the actuator 26 having two opposite wheels of the friction of the actuator 26A, geared with the main cable/rope 27. Each friction drive 26 includes a gear G and the motor-generator M-G. As mentioned earlier, for friction drives 26 may include engines, generators, M-G, the gears G and pairs of functionally associated oppositely located cylindrical wheels 26A, each of which has an annular groove 137 for receiving cable/rope 27, as shown in Fig.9C, 15C and 25. Wheels 26A are rotated in opposite directions, as shown by the arrows 01 and 02. The clutch actuators 26 are located along the length of the truck 20. May provide roughness or surface modification on the gripping surfaces of the drive wheels 26A to increase the corresponding surface of friction pairs of friction wheels actuators 26A, which clamp the respective cables 27. Electric motors-generators, M-G traction-drive 26 receives electrical energy from the main cables/wires 27 (and any subsequent cables) to drive/rotate the respective pairs of wheels 26A through the gears G during the lifting of the trolley 20 by main cables/wires 27, and the engine-generator M-G both�workers electrical energy for the main cables 27 during opalania 20 trucks on the main cables/wires 27. The engines can rotate more than one pair of friction wheels of the actuator 26A. May also be the individual engines, functionally connected to separate pairs of friction wheels actuators 26A. It mostly depends on the transferred load and the size of truck 20.

The clutch actuators 26 move the trolley 20 along the cables/wires 27 or the guide 133 and 138 (Fig.10). The clutch actuators 26 generating energy, which returns to the cables, when every cart 20 is moved in the opposite direction to gravity direction. The generation of this energy causes the reaction to gravitational force and slows down the movement of an empty truck 20 when moving down, as happens some time after the launch of the rocket 18. Each friction drive 26 can have at least one opposite pair of wheels 26A, as shown in Fig.25. The traction-drive motors should provide constant torque or variable frequency to compensate for stretching of the cable or the wheels slip, so that each group of wheels did the same contribution and supported the trolley coaxial with the center of gravity of the cables/wires 27 or the inner guides truck 133 of the lower guide tube 124, or inner guides truck 138 integral pipe 330 of the secondary guide structure 125 when moving the cart 20 up.

As monsters�nalos earlier installation of rockets 119 according to the present invention has a lifting device 60 for raising and lowering the truck 20 vertically before falling into the lower guide tube or exit lower guide tube 124, mounted on the turntable 72 of the mechanism of the turntable 63. Lateral conveying device 46 can move relative to the side of the table 141, so that a partial rotating torsion fingers 144 could enter the nest torsion fingers 154 on the bottom side of the transport device 46. Lifting device raises 60 table 141 a short distance from the support base lines 17 to grip the bottom side of the transport device 46. Table 141 is then secured to the bottom lateral conveying device 46 before its wheels 58 and all that part of the table 141 rises over the 17 tracks on which part of the table 141 can rotate with lateral conveying device 46 and the carriage 20 are installed on it, using a rotary actuator 134 to align the friction drives the carriage 26 with the inner guide rails truck 133 in the lower guide tube 124, which rotates freely, or if necessary, with amplifier, with the tower unit 123 to maintain alignment under varying wind strength. This provides stable alignment of the trolley 20 with haibara�givemy on her rocket 18 in the lower guide tube 124.

Referring to Fig.1, 10 and 11, the system of the missile 1 comprises a basic set of cables/wires 27 which are separated from each other by separation or stabilization blocks 158. Dividing the blocks 158 shown in detail in Fig.10A and include a three-way parts 159 to form a triangle, brackets or flanges 161, orthogonal to the plane of the specified triangle gear for the appropriate cables/wires 27. Flanges 161 or side details 159, or both made of non-conductive material. Cables 27 can transmit electrical energy, are light weight, as explained below, as well as high tensile strength under tension. The preferred design and the application of the separation of blocks 158 shown in Fig.10A. From each cable/rope 27 depart adaptive connectors 501 (each of which is similar to the adaptive connector 247, described below). Adaptive connectors 501 is provided along each main cable/rope 27 at intervals, wherein the connector 501 is aligned along the corresponding cables/wires 27. Each adaptive connector 501 has a pair of spaced, parallel aligned flanges 503, usually radially adjacent to the corresponding cables/cables 27 (but not precisely radially, because they clamp the loop wires running from the respective cable�/cables 27). On each flange 503 has a pair of columns 505, 506 of holes, wherein each column of holes 505, 506 on each pair of flanges 503 aligned. Column of holes 506 closest to the corresponding cables/wires 27 connected to the cables/wires 27, as explained below, in relation to adaptive connector 247. Through the respective aligned openings 505 and the holes are aligned on respective orthogonal flanges 161, passes through a series of eyelets (not shown) for securing each corner of the respective separation units 158 to the respective main cables/wires 27. Each bracket 159 of the respective separation units 158 has an enlarged portion 520 preferably of tubular construction for rigidity and resistance against bending, reaching between adjacent main cables/wires 27, which have a hanger and the tapered surface 522 to limit the movement of the cables/wires 27 in relation to each other, and create the side clearance between the separation unit 158 and each cable/wire 27. Brackets 159 are of smaller end portions 524 for fastening to each other and corresponding orthogonal brackets 161. Dividing the blocks 158 may have a different configuration; separating the blocks 158 are shown with a square cross section, but preferred� are also of circular cross-section. Dividing the blocks 158 may be integral, bent for the formation of triangular form and worn by the three major cable/rope 27 or brackets 159 can be welded together before or after installing the cables/wires 27. Brackets 159 are preferably welded to the separating blocks 158, although bolted connections are also possible.

In the upper part of the system of missile 1 is the number of suspended balloons 160 (Fig.1, 1B, 12-14); there are also other stretch balloons 164 (Fig.1, 1B, 11, 15, 17, 18, 21), located along the cables/wires 27 to compensate for the self-weight of cables/wires 27 and certain to secure their tension. The balloon 160 is attached to the mounting frame stretched balloon or upper large harness 162 (shown in Fig.12-14) for the retention of the weight of the main cables/wires 27 and all components over other tensioning balloons 164, docking station 166 (Fig.13, described below), including the operating weight of a truck with 20 ready to fly rocket 18. Balloons 160 and 164 should extinguish any lifting vibrations and reaction forces resulting from movement of the trolley 20 and its contents and other components. There is hesitation in lifting force of the tension balloons 160 and 164 due to daily fluctuations in temperature and atmospheric pressure. Additional value of the lifting force to ensure�ing the tension in the main cables/wires 27 to a substantial part of their safe working load, because the cables 27 should be maintained as close to vertical as practicable. As mentioned, you need to distribute along the cables/wires 27 one or more additional sets of balloons 164 or 164A (Fig.1, 11, 15, 16, 17, 20A, 20B), which can be less than 160 balloons to weaken the own weight of the cables/wires 27, the weight of the support structure and the separation of the blocks 158 main cables/wires 27 and diurnal variations of lift force with safety factor to prevent rupture of the cable/rope under its own weight, and the combined effect is such that the cables 27 with the respective balloons are approaching the cables/cables with no weight or negative weight. Primary cables 27 are hooked to a winch or hoist 169, which is described below, or send them energy, and form a cable/cable 170, shown in Fig.11 and 13. Cable/cable 170 is formed from the main cables/wires 27 that truck captures and 20 which receives energy, so that it can move along the cables/wires 27. Mounting frame stretch the balloon 162 consists of an upper ring 145 and the lower ring 146 (Fig.13-14) that rotate in opposite directions on the rotatable support 149. The top ring 145 and the lower ring 146 are actuated system� gear rotational actuator 177 and are described below.

Docking station 166 shown in Fig.13 and 14. Docking station 166 has an upper annular portion 172, which can rotate relative to the lower annular portion 174, parts 172 and 174 which engage with an annular support 176 is driven by a gear system rotary actuator 147 (corresponding to the rotational drive system 379 see also Fig.28), which includes the reaction plungers 178, which contribute to its work. System gear rotary actuators 177 and 147 are also used to provide opposite rotation of the upper ring 145 in relation to the lower ring mounting frame 146 of the tension of the balloon 162, and the upper annular portion 172 and the lower annular portion 174 docking station 166, which are mentioned above. Rotary drive systems 177 and 147 of the mounting frame stretch the balloon 162 and the docking station 166, respectively, are consistent so that all the components between the upper annular part 172 and a lower ring 146 are rotated together as one unit, with associated cables/ropes held from twisting around one another. Power lifters 178 and 148 of the resist caused by the wind to spin or rotation that is generated due to rotation of the trolley 20, when the lower end of the trolley 20 is retained within the upper annular portion 172 of docking station 166, and the cart 20 presets� in the best possible position to start. Docking station 166 has two sets of three internal guides trucks 180A, 180V (Fig.13, 14) to enter the radial grooves 130 each truck 20 for the purpose of maintaining proper alignment and stability of the respective carriages 20, while the power supply to the friction drives trucks 26.

Fig.13 and 14 shows a block lifting ring 182. Block lifting ring 182 includes a short tubular ring 183 with a triangular or perhaps a circular cross section, and is sent to a secondary cables/wires and connected electrically with the secondary cables cables 184, going upward from the upper annular portion 172 of docking station 166 to attach to the bottom ring mounting frame 146 of the tension of the balloon 162. Tertiary cables 186 (Fig.13, 14) coming up from the block lifting ring 182 to the frame of the lower pulley block 198. Block lifting ring 182 is sent to the secondary cables/cables 184, is connected to a docking station 166, and receive electrical energy. Block lifting ring 182 is held tertiary cables/cables 186, which are connected to the holder bottom lift 200, which is the lower frame of the lifting unit 198. As can be seen in Fig.14A, an end grip truck 196 has a set of four holes 195, through which freely pass the secondary cables 184 and a pair of holes 197 through which freely pass the tertiary cables 186. Power supply for end grip truck 196 may be supplied by secondary cables/cables 184.

Tubular lifting ring 183 has a set going into track structural components or internal guides truck 188, which are inserted into the corresponding three slots 130, running longitudinally in the cart 20 to maintain the orientation of the truck 20 in a tubular lift ring 183 and supplying power to the trolley 20. Block lifting ring 182 includes a tubular lift ring 183, block truck turn 189, which includes a pair of opposing pivot pins 190 and rotational drive system 194, the guides of the lifting ring 192 and reverse friction drives 193. The rotational drive system 194 rotates the tubular lift ring 183 which can be rotated around a horizontal axis defined by the fingers 190. The center of gravity of the tubular lift ring 183 hits its geometric center that coincides with the axis of the fingers 190. Tubular lifting ring 183 has a clamping mechanism or lock to secure the mount to the truck 20 with the possibility of separation so that the center of gravity 36 of the trolley 20 is maintained at the axis of the fingers 190. The axis of rotation of the reversing pusher 31 variable pitch made parallel to the horizontal axis defined by the fingers 190. Tertiary cables 186�responsibly connected to respective rails of the lifting ring 192. Tertiary cables 186 represent two groups of cables/cables of a fixed length, are fastened to the lower holder Tali 200 at the angle of 180° to attach the holder 200 to the guidelines of the lifting ring 192 and bottom to help guide the movement end capture truck 196 (described below), in addition, if necessary, they can also transmit electrical energy.

Block lifting ring 182 includes a rotational drive system 194 to change the elevation angle of the arrow R (Fig.13) of the tubular lift ring 183 and held her truck 20 in relation to the cables/the cables 184 and 186. End grip truck 196 is also shown in Fig.12, 13 and 14. End grip truck 196 may be held in place by the cable/wire bottom lift 201 attached to the lower lifting block 198 mounted on the holder bottom lift 200. Cable/rope bottom lift 201 is moved in the directions shown by arrows Q in Fig.14. End grip truck 196 is sent during the movement of the secondary cables/cables 184, by which electrical energy is transmitted, and retained tertiary cables/cables 186. End grip truck 196 can be attached to the top of the truck 20 with the possibility of separation with the aid of locking pins 204 that are inserted into the slots locking pins 32 at the top of the trucks or any other vehicles�and 20. When end grip truck 196 is rigidly secured to the trolley 20, end grip truck 196 may raise or help raise the cart 20 from the docking station 166 and up through the block lifting ring 182, while the center of gravity 36 of the trolley 20 does not coincide with a horizontal swivel axis of the block lifting ring 182 defined by the fingers 190, when the block lifting ring 182 is lowered to contact with the upper annular part 172 of docking station 166. The length of the cables/wires 186, guides the movement of the end gripper 196, must be sufficiently long to allow the cart 20 can rotate around the horizontal axis, when the end gripper 196 is disengaged from the carriage 20 and rises for a short distance with gear with connecting block 166.

Lower the lifting block 198 is attached to the lower end of the holder bottom lift 200, as described above, and also, as stated above, used to lift or help the friction of the actuators 26 of the cart 20 in the moving truck 20 to the entrance to the tubular lift ring 183 or out of it. The holder bottom lift 200 is raised and lowered, as shown by the arrow R on the cables/wires lift 202 from the upper lift 169 attached to the mounting frame stretch the balloon 162, as shown in Fig.12, 13 and 14. Power is supplied to the lift 169 through the secondary cables 184. For Pete�Oia lift 168 can be used three-phase or direct current. In the illustrated three-phase system, the group of four secondary cables/wires 184, additionally marked (Fig.14) from left to right as cable/rope A is the first phase of the three cable/rope V is the second phase of the three cable/rope S is the third phase of the three, and 184D that can be used as an electrical neutral or duplicate one of the three phases. As mentioned above, the balloon 160 also hold the upper system components start-up of rockets 1 and provide much of the tension required to hold the main cables/wires 27 and secondary cables/wires 184 taut, even with the workload. As shown in Fig.12, 13 and 14, the fixing frame stretch the balloon 162 is placed under tension 160 balloons.

Fig.1, 1B, 11, 15, 16, 17, 20A and 20B shows the number of groups of balloons 164 or 164A used to reduce the self-weight of the cable/rope 27, and associated support structures and barrier blocks. Balloons 164 are tapered, and the balloons 164A - cylindrical, although other shapes and configurations, however, they are included in the scope of the present invention. Each of the large number of wire harnesses 206 with the holders of stretch the balloon 208 is attached to the main cables/wires 27 through tripartite bottom of the separation or stabilizing blocks 210. Each lower section�enforcement unit 210 is designed and attached to the main cables/wires 27 as well, as the spacers 158, which is designed and used as described previously. Balloons 164 or 164A respectively joined to the holders of balloons or the attachment points 208 (Fig.18). Bottom separation unit 210 has three bracket 211, forming an equilateral triangle when viewed from above, wherein the bracket 211 parallel with the corresponding brackets 222 large harness 206. Bottom separation unit 210 has a connecting structure 214 at the intersection of brackets 211, which are the wires 215. Each wire 215 of the bottom separation unit 210 is for attachment to the respective holders of the balloon 208 large harness 206. There's also a number of upper separation or stabilizing blocks 216, which, as of the separation units 210, share the basic cables 27 and kept in place with a cable/cable couplers 218 and 219. Top of the separation units are designed and used as the dividing blocks 158 and bottom separation blocks 210. Each of the upper stabilizer 216 has three bracket 217 forming on the top of an equilateral triangle, wherein the bracket 217 parallel with the corresponding brackets 222. Cable/cable connector 220 is located at the intersection of the respective brackets 217. A pair of stabilizing couplers 218 prisoedinjays� at one end to a cable/cable connector 220 at the opposite end of the arm 217 and to the holders of couplers 221 in the center of the brackets 222 in parallel to the respective brackets 217. Another set of cable/wire rope 219 is connected between coupling connectors 220 and the holders of the balloon 208. This configuration helps to keep a stable wiring 206 in place. The wiring 206 are set periodically with balloons 164 and 164A, respectively, along the length of the main cables/wires 27 to compensate for the self-weight of cables/wires 27 and any attached structures, as well as to cause the tension of the cables/wires to help hold them in an upright position.

Specific connection system of the various components of the upper divider 216 is described below. Top of the separation unit 216 and its associated elements shown in Fig.15A, 15B and 15C. As indicated above, the upper divider 216 consists of three brackets 217, forming an equilateral triangle. As shown in Fig.15B and 15C cable/cable connector 220 includes a base plate 902 having a Central bracket 904 and two bracket 906 and 908 is separated from the Central bracket 904 an angle greater than 90°. Cable/cable connector 220 further has a supporting portion 910, which is usually the opposite bracket 904. The base plate 902 is preferably flat and perpendicular to it is cable/rope connection flange 912 running along the center of the support portion 910. A pair of support flanges of the brackets and 96 914 is also perpendicular to the support plate 902 and is located at equal distance from cable/rope connecting flange 912. Brackets 904, 906 and 908 have openings for the reception of lugs 920, 918, and 922, respectively, going perpendicularly through the respective brackets. 904, 906 and 908. Cable/rope connection flange 912 has a number located equally spaced holes for the reception of lugs 924 along the height of the flange 912.

Each cable/wire 27 has at least one but more likely several coupling designs 925, with each of these connective structures 925 consists of pairs of parallel, opposing, spaced connecting flanges for the reception of the flange 926, 927, each of which is parallel to the corresponding axes of the cables/wires 27. Flange 926 is aligned parallel columns of holes for receiving the lugs 928 and 930, which are aligned with the corresponding holes 928, 930 on the other flange 927. To attach each cable/cable connector 220 to the place on the corresponding cable/rope 27, cable/cable connection flange 912 is inserted between the connecting flanges for the reception of the flange 926, 927 with holes 924, aligned with each of the respective holes 928. Set of eyelets 932 is inserted into the respective aligned holes 928 and 924 and is attached to the receiver nut or other fastening element 933. To further connect the appropriate cable/cable connector 20 with the corresponding cables/cables 27 are used the same bolts 256, as shown in Fig.22, for clamping loops 244 cable/rope 27. Connecting flanges for the reception of the flange 926, 927 are close enough to each other so that the friction actuators 26 can engage the respective cables 27, when the truck 20 with a friction actuator 26 is transferred flanges 926 and 927 in full working engagement with the corresponding cables/cables 27.

As previously indicated, a pair of stabilizing couplers 218 attach the cable connector 220 to the respective centers of the pair of brackets 222 large bundles 206. Each stabilizing coupler 218 is at one end of the connecting yoke 934 with a pair of parallel flanges 936 with aligned apertures 938, through which the eyelet 940, which also passes through the opening 908 for further reception of a nut or other fastener receiver 942 to attach stabilizing couplers 218 to cable/cable to the connector 220. Similarly cable/rope tie 219 has a coupling yoke 944 with a pair of parallel flanges 946 with a pair of aligned holes 948. Bracket 904 is inserted between the flanges 946, and the eyelet 950 inserted into the holes and 920 948, as well as in a nut or other fastener receiver 952.

Fig.15E shows a detail of the joining of the bottom separation unit 210 (Fig.15) to the cables/the cables 27 and harness 206 using soy�internai structure 214. A pair of connecting structures 925 is attached to the cable/wire 27 by means of hinges 244. Connective design 925 consists of a vertical flange 960 having a connection flange 962, which comes from him, and includes a column of holes in the lugs of 963. A set of support flanges of the brackets 966 goes from vertical flange 960 to which they are welded using a suitable weld procedure, and respectively connected to the respective brackets 217 bottom of the separation unit using a suitable welding or other procedure. The abutment flanges of the brackets 966 are angled to each other and at an angle in contact with the respective brackets 217, to provide a structurally strong support. The connecting flange 962 is located between the parallel flanges of the connecting structure 925, with the holes aligned with the holes 928 (see Fig.15 (b) and eyes 932, and insert through the respective aligned holes of the connecting flange and holes 962 928, as well as through nuts and other fastener receiver 933 (see Fig.15A) for attaching the connecting structure to the cable/rope 27.

Vertical bracket 960 has a finger-shaped section 968, which passes through a hole 970. The end of each wire 215 for fastening of the bottom separation unit 210 to balamurali 206 has a coupling yoke 972, consisting of parallel flanges 974, 976, which pass through aligned openings for the reception of lugs 978. The clamp 972 is moved so that the finger-shaped section 968 is inserted between the flanges 974 and 976, and the holes 970 and 978 aligned. Eye 980 is inserted through the openings 970 and 978 and nut or other fastener receiver 982.

We mentioned earlier that the stabilizing coupler 218 is joined to the center of the brackets 222. The apparatus for this purpose is shown in Fig.15D. Flange connection couplers 984 is attached to the center of each bracket 222 and goes away. Flange 984 has two short bracket 986, each of which has a hole for receiving the eyelets 988. Each coupler 218 has a connecting clamp 944 with flanges 946, as described above. Clamps 944 from each coupler 218 are placed on the corresponding bracket 986 flange 984, and the eyelet is inserted through the holes and 988 948 and is tightened in place by the fastening element, such as a nut.

Design for attaching each harness, separator and stabilizer preferably comprises the same type of components and sub-components. This type of construction is durable, stable, easy to manufacture and commissioning.

A number of tripartite separation or stabilizing blocks 260, which is almost identical to the separation units 210, are located over most of� harness 206 (as shown in Fig.18). Detailed design of separation units 260 and its fastening to the main cables/wires 27 are practically the same as dividing the blocks 158 and bottom separation blocks 210. Dividing blocks 260, shown in Fig.18, are attached to the cables/cables 27 by means of connecting structures 262 at the intersection of pairs of connected brackets three brackets 264, forming an equilateral triangle. A set of lightweight cables/wires 266 (compared to the relatively heavy cables/wires 27) comes from the connecting structure 262 to the holders of the balloon 208, the design of which keeps them in large bundles 206. Lightweight cables 266 hold large bundles 206 during Assembly of the launch system or during maintenance of the balloon 164.

A set of three electrical reaction thrusters 800 attached to a rotating bearing joints 802 at the intersection of the respective brackets 222, as shown in Fig.18 and 19. Each pusher 800 switches the fan 804 mounted in the casing 806. Every 806 housing is mounted on hinges between the pairs of brackets 808. Each bracket 808 has a coaxial pivot pins 809, reaching into the housing 806, enabling every 806 housing to rotate around the axis S-S in the direction of the arrow T in clockwise and counter-clockwise. Brackets 808 branch off from Portland�Central bracket 810, which is attached to rotatable support the joints 802, as described above. Pushers 800 is an electric pushers in the gimbal. Pushers 800 can swivel to turn and rotate and act to hold the trigger system 1, oriented relative to the vertical. Pushers 800 compensate for wind power, as well as partial or complete deflation of any balloons 164, until they are replaced or otherwise repaired. The position of large bundles 206 relative to the base of the launch system 1 is controlled by the position sensors 812, which may be a global navigation and positioning (GPS) for transmitting control data of the situation on the computer controlling the direction and force of the pushers 800.

The following is an explanation of a case in which the balloons 164 (applies to balloons 164A) are attached to the main cables/wires 27 (see Fig.15, 16, 17, 18, 20A and 20B). Fig.15 for the sake of clarity not shown the separation unit 260 and lightweight cables 266, shown in Fig.18, located above the upper stabilizer 216. If you look at Fig.15, shows part of the main cables/wires 27, and a lower stabilizer 210 and the upper stabilizer 216 to stabilize the upper harness 206. There are three balloon 164 (only one is shown in solid line in Fig.15) to compensate �own weight of the cable/rope 27, various stabilizers, and the excessive load applied to the cables 27. Depending on the diameter of the balloon 164 may be required tubular separators, made of the same material as the balloon, and inflate the same gas is lighter than air. To protect the cables 27 from contact with the balloon 164 (or balloons 164A), provides a stabilizing straps or mesh 227 (Fig.15A) for attaching balloons 164 to the separators cables/wires, such as the top of the separation unit 260 (Fig.18), to prevent such contact. Each stabilizing strap 227 is part of the stabilizer 228 that is attached to each cable/rope 27 as well as other stabilizers are attached to the cables/cables 27. Stabilizers 228 further have a connecting element 229 to hold respective stabilizing straps 227 on the spot. How this can be done in more detail shown in Fig.16, which is a top view in the direction 16-16 of Fig.15. As can be seen, each stabilizer 228 is attached to the main cables/wires 27 within three intersections of the stabilizer 228. The stabilizer 228 is composed of three respective brackets 234, which mutually intersect, forming an equilateral triangle. Each connecting element 229 a pair of stabilizing straps 227 forms an angle so that the corresponding�following pairs regarding these balloons 164, they are almost tangent. Each belt 227 is attached to the balloon 164 tangent connector of the belt 224. Connectors straps 224 prevent the touch of the cables/wires 27 to the balloon 164 (or balloons 164A). Connectors belts 224 (Fig.15) preferably may be glue, plastic welding or stitching with a strong enough thread to attach the stabilizing straps 227 to the respective balloons 164 (or balloons 164A).

Fig.17 shows three of a balloon 164, attached to a large harness 206 in the holders of the balloon 208. The upper stabilizing unit 216 having its stabilizing ties cable/rope 218, attached to the holders screeds on brackets 221 222. Fig.17 shows vectors of force FF directed along the tensioning cable/rope 219 and represents the tension force from the cable/cable connectors 220 to the holders of the balloon 208.

Side view of the mounting system shown in Fig.20A and 20B. Each balloon 164 (Fig.20A) and 164A (Fig.20V) is lightweight, strong, tension, lower connectors 232, attached to the balloon holder 208 large harness 206. One or more connectors 232 may have a tubular shape for feeding gas lighter than air as a substitute in each balloon 164 to compensate for leakage. Balloons 164 and 164A is balloons lighter than air, so stretch�their force FF of the arrows along the connectors 232. The connector 232 is directed tangentially to the shell of each balloon 164 and 164A. Shows the set of three or more connectors or stabilizers 228 (Fig.16) to connect the respective balloons between each other at several points.

As explained earlier, the fixing frame tensioning balloons 162 has an upper rotating portion 145 and the lower rotating portion 146 (Fig.13, 14) that are connected via a support ring 149 on the vertical axis to reduce friction against rotational movement, as shown in Fig.12. The reaction pushers 148 tangentially attached to the perimeter of the upper rotating part 145. Similarly, the reaction plungers 178 is attached to the perimeter of the lower portion 174 of docking station 166. Motor modules mounted on the upper rotating part 145 and part 174, are used to prevent their rotation. Motor modules on the top 145, together with the toothed rotational actuator 177 contribute to the rotation of the lower rotating portion 146 relative to the upper rotating part 145. Similarly, motor modules on the bottom portion 174, together with the toothed rotational actuator 147 (Fig.13, 14) contribute to the rotation of the upper rotating part 172. Secondary cables 184, collected in two groups are attached opposite each other (180°) of the lower rotating�Xia portion 146. Upper lift 169 is fixed to the lower rotating portion 146. Cables/wires mounting frame 184 of the balloon 162 is attached to the docking station 166 (Fig.13, 14) and is transferred to electrical energy in case of need. Cables 184 also direct the movement of the holder bottom lift 200, end gripper truck 196 and block lifting ring 182. Cables 184 are of sufficient length to allow safe acceleration down at the local acceleration of the holder bottom lift 200 under the action of gravity and suspended items to it, of sufficient length to remove the missile 18 from its limiter in free fall and accelerated the liberation of the truck 20. Also required additional length of cable/cables 184 to provide an extra period of time to reduce speed to a complete stop holder bottom lift 200 and all items (including loaded or empty truck 20), which suspended him. Additional cable length/cable will allow a reduction in the speed of a fully loaded truck 20 to dormancy in case of a short time the misfire booster.

As explained above and further described below, must be a means for mounting the elements of the system 1 to various cables/wires. Fig.21 showing� cable/rope 240, made of lived wire 242. Each strand 242 cable/tether 240 can have loop portions or loops 244 extending from the outer surface of the housing of the cable/tether 240 for fixing the elements to the cable/rope 240, a large portion of the outer surface of the cable/rope remains free. Each loop goes from 244 of the housing each cable/cable 240 and returns to the body of the cable/tether 240. As an example in Fig.22 shows an adaptive connector 247, which is explained in more detail below. Adaptive 247 connector has a protruding flange 248 with a number of bolt holes 249, as well as a number of bolt holes 250 through a pair of parallel walls 252, forming a common base 253. Adaptive 247 connector can be customized to the cable/rope 27, loop 244 is moved between the parallel walls 252 and their respective loop holes 254 are aligned with the holes 250. Bolt 256 can be inserted through loop holes 254 and bolt holes 250 for mounting adaptive 247 connector to the cable/rope 27, and corresponding bolts 256 may be covered by the nut to ensure a strong connection. Top view shown in Fig.23. Alternatively can be used parallel walls 255, separated by the delimiter 259 as an alternative adaptive connector 257, as shown in top view in Fig.24. Cable/t�OS 27 can be captured by a pair of friction wheels actuators 26A trucks 20, as shown in Fig.25, rotating in opposite directions O1 and O2.

To use the system launch 1 described so far, 18 missiles are loaded in truck 20, respectively, in one of the devices shown in Fig.5, and transported along the track 15 lateral conveying device 46. Lateral conveying device 46 is attached to the lifting unit 60 by means of corresponding conical centering pins 142 and partially rotating torsion of the fingers 144 and their respective nests for centering pins 152 and nests for partially rotating torsion of the fingers 154, as explained with reference to Fig.9. Secondary cables 184 and primary cables 27 are held taut by means of a tightening of 160 balloons and balloons 164, respectively, wherein the balloon 164 provide the tension in the main cables/wires 27. Tension below the cables/wires is passed through the mounting frame suspended balloons 162, and the separation of cables/wires and additional tension is achieved through large bundles 206, separators separator 158 and 228 (Fig.11,15 and 18).

Each trolley 20 is rotated to align with internal guides truck 133 and loaded into the lower guide tube 124 (Fig.8). The upper part of the lower guide tube 124 is then dumped into engagement with �igna part of the secondary guide structure 125 (Fig.10), while the lower guide tube 124 reaches the stop 132 to align the guides of the trolley 133 and 138, as previously described. Then used the clutch actuators 26 to move the truck 20 along the cable/cable 27 via the docking station 166 in its upper portion 172 and partially in block lifting ring 182, which is lowered with the lift 169 so that the block lifting ring 182 is included in the upper part 172 of docking station 166 (Fig.13, 14). End gripper 196 is lowered and secured to the upper end of the truck 20. Lower the lifting block 198, powered by secondary cables/cables 184 transmitted from the cables/wires 27, raises the cart 20 to engage with the block lifting ring 182 so that the combined center of gravity of the block lifting ring 182, truck 20 rockets and 18 coincide with the axis of rotation of the block lifting ring 182. Thus, the lower lifting block 198 friction helps the actuators 26, which engages the inner rails of the truck 180A and 180V in the lift truck 20 upstream relative to the docking station 166. Then end grip truck 196 disengages locking pins 204 of nests locking pins 32 of the trolley 20 and rises to the minimum distance using the lower lift 198. Block lifting ring 182 is sent to the secondary cables/cables 184 and is held tertiary cables/Tr�themselves 186. Lift 169 additionally raises the cart 20, while the lower end of the truck 20 is no longer in the lower part 174 of docking station 166, but only in the upper part 172. Now system gear rotary actuator 147 in the bottom of the docking station 166 and gear system rotary actuator 177 in the frame of the stretch of the balloon 162 rotate in unison all the components between the ring bearings 176 and 149 in the direction appropriate for the missile 18. The pushers 148 and 178 are working simultaneously to prevent rotation of the lower portion 174 of docking station 166 and the upper ring fixing frame 145 of suspended balloons 162 (Fig.14).

Lift 169 then raises the cart 20 is completely out of engagement with the docking station 166 (truck 20 holding the rocket 18, must rise higher and higher with their combined weight) and as high as you need it, in the center of the tubular ring 183 for safe firing of the missile 18. The rotational drive system 194 in conjunction with the reverse thrusters with variable step 31 is rotated 90°, rotates a short tubular ring 183 of the trolley 20 at an appropriate angle with respect to horizontal, suitable for start-up. Reverse thrusters with variable step 31 are used to facilitate rotational drive system 194 and prevent rocking of the truck 20 around a horizontal OS� on the fingers 190. When the truck 20 is at a desired elevation for start-up and is sustainable reversible thrusters with variable step 31 further rotate around their hinges to avoid contact with hot rocket gases.

There are variations to facilitate rotational drive system 194. This includes the positioning and stabilization of the cart 20 in the block lifting ring 182, in particular to prevent the vibrations of the truck 20 to the hinge fingers 190. As shown in Fig.13C-13C, on both ends of the truck 20 may be provided for reversing variable pitch pusher 31 and a pair of associated hub motors 822. Each pusher 31 and the hub engine 822 may be located at one end of the truck 20 under the end cap 830. Each pusher 31 has a set of rotating blades 826, which are mounted in a rotatable support pusher 828 on both ends of the truck 20. Each support 828 is mounted on the block 829 loops and moves between a rest position (shown in dashed lines in Fig.13C) and an active position parallel to the longitudinal axis of the truck 20 (shown in solid lines in Fig.13C) using the hydraulic actuating mechanism 832, which is rotated around the hinge actuating mechanism 834. When the Cam followers 31 are in the active position, creates an air stream until�this arrow U. This prevents oscillation of the trolley 20. Hub motors 822 are reversible, because the airflow can flow in both directions. Similarly, the pitch of the blades 826 may change to account for changes in ambient air, in which the blades 826 rotate. However, when the ignition of the rocket engine 18, the Cam followers 31 can be moved at an obtuse angle, as shown by dotted lines in the left part of Fig.13C, in order to avoid short-term exhaust of the booster. The upper end of the pusher 31 is also moved in its obtuse-angled position, so that you can load the rocket 18 on the cart 20. It should be noted that the inner part of the truck 20 has a continuous resistant to pressure and temperature pipe 836 extending from one end to the other to hold the inside of the rocket 18. A set of three or more centering supports 840 retain centering reverse of each of the variable pitch pusher 31.

The upper end of the lifting cable/cable 202 (Fig.14) is removed from the top of the lift 168, reversible friction drives 193 block lifting ring 182 start to navigate down, being in functional engagement with the secondary cables/cables 184. Lifting cable/rope 202 is unwound and moves the block lifting ring 182, the cart 20, the missile 18 and all other components held by the cable/wire 202 in a downward direction by means of drives 193, contribute to overcome the friction and resistance of air, so that they are in free fall with an acceleration of lg and rocket 18 becomes weightless relative to the cart 20. In the upper hoist 168 has a small friction to maintain control during free fall, as well as to avoid sagging and uncontrolled unwinding of the cable/tether 202. Before a free fall open outlet end cap 30 (Fig.9, 9C, 13, 13A) of the truck 20 (or open the end caps 830, shown in Fig.13C). Disposed idler brackets 34 or 35 (Fig.26) inside the truck 20 that kept the rocket 18 in truck 20 (as described below), and ignited a short-term booster rocket engine rocket 18 for the launch of missiles from 18 truck 20. Short booster rocket engine works only in resistant to the temperature and pressure of the truck body 20, to prevent damage to the starting system 1.

After the missile 18 is held far enough on its ballistic trajectory, it is possible to safely light the main engines, which is necessary to prevent damage to the starting system 1. Removal of cables/wires 202 of the upper lift 168 (Fig.12) is being phased out, while the reverse friction drives 193 block lifting ring 182 (Fig.13) work in brake�EIT mode, to prevent free fall of the truck 20, the holder bottom lift 200, end gripper truck 196 and block lifting ring 182 (Fig.12, 13, 14). Reverse thrusters with variable step 31 (Fig.13C) can then be used to facilitate the rotation of the truck 20 in a vertical position, before they are allotted to the ends of the truck 20 and can be used to remove exhaust gas from inside the truck before closing the lids of weather protection 30.

Short tubular ring 183 of block lifting ring 182 with an empty cart 20 is rotated to the vertical position (in preparation for the rotation around the vertical axis, since the rotational moment of inertia is smallest when the truck 20 is in the upright position), descends through the top of the lift 168 connected to the upper part 172 of docking station 166, shown in Fig.13 and 14. The trolley 20 and the end grip truck 196 can then be connected to lock the truck 20 to the end grip truck 196 before the cart 20 is lowered until contact with the upper part 172, if you need additional support or direction. The lower end of the truck 20 is then lowered until contact with the upper part 172 of docking station 166. The lower portion 146 (Fig.14) mounting frame suspended balloons 162 and the upper part 172 of docking station 166 �ATEM rotate, what are the internal guides truck 188 block lifting ring 182 (Fig.13, 14) and the inner rails of the truck 180 upper portion 172 are aligned with the cables/wires 27 docking station 166 (Fig.13). Then lift 168 limit lowers the seizure of the truck 196 on top of the block lifting ring 182 (Fig.12, 13, 14) and releases the cart 20. Block lifting ring 182 is also disengaged from the trolley 20.

The trolley 20 is moved quickly down the cable/rope route 170 (Fig.11) formed by the main cables/wires 27, using recuperative braking to maintain the speed of movement of the truck 20 down to a manageable level. The energy is returned to the main cables 27 in this and other launchers stations to the other of starting the station to Supplement or replace the energy required to lift another truck 20 up her cable/rope path 170. Provided for group of minimum four active launch systems, and fifth used as a ready reserve for light jobs, such as Hiking or skydiving using special lightweight trucks, while active the launcher will not require maintenance or will need a high speed missile. Combined speed trigger once an hour it seems appropriate.

After p�pack truck 20 again enters the secondary guide structure 125 (Fig.1A, 2, 8, 10 and 11), it is further lowered until the cart 20 is disengaged from the secondary guide structure 125 and becomes centered in the lower guide tube 124 at the point at which the combined centers of gravity of the truck 20 and the lower guide tube 124 coincide with the axis of rotation of the lower guide tube 124. Then the lower guide tube 124 is returned to the upright position and the cart 20 is lowered on a properly aligned lateral conveying device 46 on top of the lifting unit 60. Lateral conveying device 46 returns the empty cart 20 by explosion-proof compartment Assembly 10 to re-download or on storage racks 7 for replacement and repair. Another pre-assembled rocket 18, the cart 20 and the lateral conveying device 46 may be loaded into the system 1, and the next rocket 18 can be started, as described above.

One possible design of a retractable idler bracket is a bracket 34 in the direction of the arrow V to hold the rocket 18 in truck 20, as shown in Fig.26. Rocket 18 has at least six spaced at an equal distance from each other adjustable grooves 300 for receiving idler brackets 34, each bracket 34 is designed for installation in one groove 300.

As shown in Fig.27, can be planned for�atrani different alternating angle brackets 35. Each idler bracket 35 has a head element 302 to log into one of the notches 300, and a base element 304, which are opposite coaxial pivot pins 306. The rod 308 connects the head element 302 and a base element 304, wherein between the base element 304 and the rod 308 are amplifying jumpers or stretch marks 310. The trolley 20 has an internal explosion-proof pipe 312 with the cavity 314. Tube 312 has a pair of protective doors 316 mounted on hinges 318, which may be installed so as to cover a portion of the cavity 314 (as shown by arrows W) or turn out for the opening portion of the cavity 314, as shown in Fig.27. Pipe 312 is also closing the cavity face of the door 320. The door 320 may have an airflow deflector 322 to protect the doors 316, 320 and cavity 314, the amplifying rod stretched element 324 and the finger holder 326, holding pivot pins 328 for entering into the hinge slot 331 on the near sides of the side walls 332, defining part of the cavity 314. The door 320 is rotated by the fingers 328 between the open and closed position. Wall 332 also have a swivel socket 334 for receiving the fingers 306 drop bracket 35.

Closing the cavity of the door 320 also has a hydraulically bypass a finger 336 to move in the slot 338 and out of the bracket 340 of the door 320, and a hole 339 in b�call element 304. The door 320 also has parallel legs 342 aligned with holes 344. The rod 308 a retractable bracket 35 has a vertical section with a groove 346 348 passing in the rod 308 in the longitudinal direction. Plot 346 goes between the legs 342, and the trailing finger 350 passes through the groove 348 in each hole 344 for discharge connection bracket 308 with the locking groove of the door 320. Hydraulic bracket 352 is 354 feet with aligned holes 360 to pass between a pair of legs 362 on the lower end surface 364 of the cavity 314, the legs 362 aligned with holes 366, 354 feet are held in place with a finger.356 and pass through the apertures 360 and 366. Another pair of parallel legs 368 goes from the shaft 369, usually going forward from the bracket 352, and a pair of aligned holes 370 receives the finger 371. Door 316 to open and close hydraulic or Electromechanical means in concert with a door 320.

In the previous design of the door 316 and 320, shown in Fig.27, are locked in the open position, and the head elements 302 of each of the exhaust bracket 35 remain in the respective grooves 300 in the rocket 18. When the rocket 18 is in a state of free fall of the trolley 20 and becomes weightless relative to the cart 20, the brackets 35 quickly disperse into the respective cavities 314 along with the rest of the block, rabotajushih� with brackets 35, and doors 316 and 320 are closed immediately before the ignition of the booster rocket motor of the missile 18. Each rocket 18 may have small sets of wheels 372 to hold the missile 18 is centered in the tube 312 during start-up if the direction of the force of thrust is not exactly coaxially with the inner pipe of the truck 20 or does not pass through the center of mass of the rocket.

Another version of the invention in addition to the launch of missiles can be used if need to raise up the telescope. Fig.28 and 28A shows the restraint system of the telescope 373. Fig.28A shows the balloon 160 in a reduced form. Components associated with the telescope are described below. System 1 has three major cable/rope 27, which is transferred to electrical energy and which are attached to the docking station 374. Docking station 374 has an upper portion 376, which can rotate in the direction of arrow X relative to the lower part 378 using a rotational drive system 379. As shown in Fig.28B and 28C, a rotating drive system 147 rotates the upper portion 376 and the lower portion 378 in relation to each other using the ring support 850, having turned re-formed l-shaped element 852 in cross section, with sets of ball bearings 854 and 856 in ruts 857, 858 and 859, 860 in the upper part 376 and an l-shaped element 852, and the lower part 378 and an l-shaped element tin.

The upper ends of the cables/wires 27 are held firmly, as shown in the figures. One cable/wire 27A is at an angle through the opening 862 in the lower portion 378 and a corresponding clamping mechanism 864 for a durable hold cable/rope 27A. The second of the cables/wires 27 proved as a cable/wire 27B and is firmly held by appropriate means on the flange 866, as further shown in Fig.28C. The third of cables/wires 27 is held firmly in a similar way. The engine 868 rotates the toothed wheel 870. Gear 870 sequentially connected to the teeth 872 of the upper part 376 to provide the specified rotation shown by the arrow Y. In the protective casing may be enclosed motor 868 and gear 870.

Can be used three or more of the reaction of the follower 380 to compensate for the mutual rotation of the parts 390 and 378 held stationary, when the rockets used an alternative launcher system shown in Fig.28. Like other docking stations, between the upper and lower portions 376, 378 docking station 374 is annular bearing 377 and rotational drive system 147. Secondary cables 184 are also used for transmission of electrical power to operate electrical components. This can be a two-cable system DC or chetyrehkamernoe three-phase�system.

Lifting ring 382 is moved up or down in the direction of the arrows Z on the cables/wires 184. Lifting ring 382 includes a reversible friction drives 386 and design 387 to hold the truck 20, which can rotate in the direction shown by the arrow AA and the rotational actuator 381 to change the angle of the lifting ring 382 and truck 20. Top docking station 388 has an upper portion 390, which is typically held stationary, and the lower portion 392, which can rotate in the directions shown by arrows BB, around a vertical axis using a rotational actuator 381. The annular support 394 reduces friction from such rotation. A minimum of three reaction pusher 397 counteract the rotation of the upper parts 390 around the vertical axis.

Hard lift shaft or lift pipe 396 may carry special truck 398, each of which is arranged the telescope SS, to the upper support 399. Can also be used special lightweight truck or truck 20A for the transport truck 20 to the lifting pipe bearing 396 399 after the transfer of the lifting ring 382. Inside the lifting tube 396 can be installed a set of electric cables or rails, which move the wheels of carriages 398 or 20A and which will transmit electric energy (as in the case of friction wheels types of duty for actuators� 26, regarding cables/wires 27) to provide transportation truck 20A up and down inside the lifting tube 396. The 160 balloons are attached to a lift pipe 396 and surround her, as previously described, to provide sufficient tension on the cables/wires 184 to transport the lifting ring 382 with a truck 398, holding inside the telescope SS and retention of cables/wires and apparatus attached to the cables/wires.

The upper bearing of the telescope 399 includes tower platform 402, which hosts the turntable 404, which rotates against the stationary upper portion 390. The receiving telescope aperture 405 passes through the platform 402 and the pivot platform 404, as shown in Fig.28A and 29. Mounting wall 406 coming from the turntable 404. Holding the telescope design or a ring clamp 408 special trolley 398 with her telescope SS, with the centre of gravity of the truck 398 is located in the center of the ring 408, which acts as a lifting block 182, however, without friction drives. As shown in detail in Fig.29, ring 408 has a coaxial pivot pins 410 included in the slots 412 of the mounting walls 406. Has mounting wall 406, the ring 408 and pivot pins 410 for telescopic inclined structure 411. Therefore, the 398 cart and mounted on her t�lescop SS can be tilted in the up position to the desired position, and the azimuth rotation shown by the arrow DD turntable 404 directs the cart 398 and the SS telescope in any desired direction. Turntable platform 404 and 402 can be made independently rotating in respective opposite directions, shown by arrows HH and II (Fig.28A, 29) relative to the lifting tube 396. This rotation is provided by the rotational actuator 383, similar to the actuator 381. Platform 402 may have a radial adjustable cargo to make its rotational moment of inertia equal rotational moments of inertia of the turntable unit 404 and parts on it so that when they rotate in opposite directions to lift the pipe 396, there has been effective torque when the rotary platform 404 and the parts above it rotate.

System of the missile 1 can be used for different purposes. For example, it can be used to start a single person or a base rocket 601 having a motor direction control 603, as shown in Fig.30, which can move, as shown by the arrows of HER, to control the direction of movement of the missile 601. Shows someone or passenger GG in liquid-filled pad the suit or the suit for refund in the atmosphere with couplings 605 607 blocked in optimal aerodynamic�ish vertical position to start, and locked his feet to the top of the rocket 601 for resistance overload during acceleration of the rocket 18 during start-up. The suit 605 detaches from the rocket 601 at will when you stop using the rockets 601, and articulation of the suit is unlocked to allow the passenger GG to move freely. If the suit is to be used to return to earth, some of the fluid that surrounds the passenger GG, can be pumped through the porous pads to cool by evaporation the outer part of the suit to return to the atmosphere 605 after entering the atmosphere, starting with the feet. (The same pumping and cooling effect are used also in the start menu). Rocket 601 with standing on top of the passenger GG in the suit 605 must offer the passenger the GG beautiful view of the startup phase. Aerodynamic fairing around a spacesuit 605 may not be required, unless it is stipulated in the design, and the set of joints 607 is locked in place, aerodynamic resistance remains higher required for optimum start-up.

Fig.31 shows a possible method of transporting tourists in spacesuits 605 or materials in hard capsules 608, which are attached to rod rocket 604 with the possibility of disconnection. The main rocket 601 terminates controlled start after a certain time after start-up. Rod rocket 604 can then disconnect�trust from the main rocket 601 after a controlled start-up of the main rocket 601. To protect travellers in spacesuits 605 or capsules 608 from high-speed air can be used windscreen 609, when the rocket 601 penetrates the atmosphere on the way to space, where the spacesuits 605 or capsules 608 can be free in the direction of the arrows JJ. Rod rocket 604 can have a set of rotary fins 602, which is rotated in the directions QC system control the direction of the rocket 601.

Fig.32 shows an alternative capsule 610 with frame return to the atmosphere in the form of a slide 616. The passenger GG is starting a suit or a suit for refund in the atmosphere 605. Frame return to the atmosphere in the form of a sled 616 includes feathering control the direction of movement of the 619 and the air edge 611. Air edge 611 has an extendable design, the antenna with the disc 613, performing the role of front of the initiator of the acoustic waves to generate acoustic waves 615 to reduce aerodynamic heating of the suit 605.

Fig.33 shows a suit for refund in the atmosphere GG man, laid in more like a missile in the form of a frame 617 with the managing direction of the plumage 618 and air-headed 611. Frame 617 has drive 613, described in Fig.32. In the rear the inside of the frame 617 can be accommodated with the control and storage compartment.

Favourite space skafandr shown in the man GG in Fig.34 and 35, which also is designed to ease the overload. Space suit 605 allows the passenger GG to survive, to stay conscious and be able to remain active in an upright position under conditions of high acceleration. For advanced operations this is achieved by immersion of a passenger in a liquid approximately the same density as that of the body, inside the hard suit with external Electromechanical or hydraulic constant volume joints with servo. Space suit 605 650 has a helmet (Fig.34, 34A, 34B, 36) surrounding the person's head GG, and hard outer shell 648. Internal suit 651 lies close to the GG, and the inner mask to protect the face 653 with visor 655 hermetically attached to the inner spacesuit 651. Nontoxic liquid 656 (Fig.34, 34A-34B) fills the space between the rigid outer shell 648 and inner spacesuit 651. If the liquid 656 heated to a comfortable temperature, the inner 651 suit may not be used. Between the inner 651 suit and mask to protect the face 653 used double seal 654. Internal suit 651 may encircle GG man, and the mask to protect the face 653 can get some air from the source of air supply through the tube, the air supply 661. On the mask to protect the face 653 of the space suit 605 provides a leakage path 652 to drain the water � case of leakage in the space between the double seal, surrounding the man's face GG. Water or other suitable non-toxic liquid 656 fills the space between the inner spacesuit 651 and the outer shell 648, a mask to protect the face 653 and visor 655, as shown in Fig.34, 34A and 34B. The GG man in a space suit 605 can rotate the head in the helmet 650 being suspended in water 656. Space suit 605 is a rigid, lightweight design, however, in the mask to protect the face 653 or visor 655 may be provided for volumetric air flow sensors for directing hydraulic or Electromechanical drive piston (described below) that is moved in and out to compensate for volume changes during respiration. Additionally, to compensate for the respiration rate, i.e. the change in volume divided by change in time, the pressure sensors at various points (particularly near the chest) in a space suit 605 maintain constancy of fluid pressure by lifting and lowering of the piston. The use of external hydrosaline high pressure, so that GG can move freely in the suit 605 overload conditions, for example, during start-up or return to the atmosphere, eliminates the possibility of water or other hydraulic fluid used to activate the compounds of the suit, inside a spacesuit that could lead to crushing GG man.

The piston is also shown in Fig.35. In this image, the suit 605 has water (or a non-toxic liquid with a density approaching the density of the human body) 656 filling the spacesuit around GG, and the piston 657 moves inward and outward from the cylinder 660 under the action of hydraulic fluid under high pressure or by direct casting of the piston 657 in motion by means of an Electromechanical device to change the volume in the suit 605, required for normal breathing.

Hard outer shell 648 has a design typical of the suit 605, shown in Fig.34, and shown in Fig.36. Hard outer shell 648 suit 605 includes a pair of rigid sleeves, each of which has an inner sleeve 664 (only one shown), each of which is made of an open, flexible mesh or soft foam material with open pores, and a pair of rigid legs, each of which has an inner leg of the same construction as that of the inner sleeve 664. The inner sleeve and the inner leg referred to herein as the "inner sleeve". The pores must be large enough to provide substantial barriers to the flow of water through the sleeve 664. The sleeve 664 is held centered within a spacesuit 605 with a weak elastic tighteners 668 attached to one end of the suit 605, which is pre�Yat through the sleeve 664 and fastened to the sleeve 664 and pass tangentially thereto, to which they are attached to the other end. Tension elastic tension elements 668 perceived by the sensors and used to provide feedback to control the mechanical joints of the suit 605 for the purpose of mirroring the movements of a person with GG hold it in the center of the suit. Man GG just slips in suit 605, and his body slides in a typical sleeve 664. The suit 605 is a practical and efficient space suit that a man wears GG rocket 601 or within 18 missiles, especially during start-up, acceleration, and return to the atmosphere. The outer shell 648 can have ablative outer material with insulation and thermal insulation.

Other versions of the rocket shown in Fig.37, 38, 38A and 39. Rocket 700 has an air-space plane 702 with unfolded and folded structures control the lifting and movement direction 704 is attached to the housing shown in Fig.37, 38 and 38A, and put in the directions shown by the arrows LL and MM. The vehicle to return to the atmosphere type lifting body 706 is shown in a retracted launcher form in Fig.38 designs with control lift and direction 704 in the folded state. The vehicle to return to the atmosphere type lifting body 706 designs with control lift and direction 704, folding � additional direction the arrows NN, shown in Fig.38A in the folded and unfolded state. Rocket 700 original is a military version of the missile 18.

Fig.39 shows a more typical rocket 720. Rocket 720 includes a satellite or other payload 722, which is protected during launch and flight of a pair of disposable aerodynamic shell 724. After the 720 rocket leaves the atmosphere, the shell automatically detached 724 shown by the arrows in PP directions and preferably falling back to the ground and the satellite or other payload 722 out into space. Rocket 720 original is a commercial version of the missile 18.

Described above a preferred variant of the implementation can be implemented using currently available materials and products. Model truck loaded with rocket, estimated to weigh 80 tons, but possible and more weight. Each cable/rope should be strong and electrically conductive. It should also be durable to withstand the movement of the drive wheels up and down the cables/ropes. Thus, the cables 27 and 184 should have a steel exterior aluminium intermediate part and the steel core. Cables shall be stranded copper and steel wires, and steel wires with copper coating or have another p�Dhorasoo design. To lift 70 tons of cables shall have a diameter of approximately 2/3 of an inch. Each of the three cables/wires may have a diameter of 1.25 inches, and each of the secondary cable/rope shall have a diameter of one inch.

As mentioned earlier, the weight of the cables/wires should preferably be a periodic payment. Steel cables having a diameter of 1.125 inches, weigh about 2,03 pounds per foot. You must use a margin of safety not less than five. Cable/cable with a diameter of one inch holds a weight of 120 tons on the tensile strength.

The preferred gas for balloons must be hydrogen, which is much more buoyant than helium, and can be generated from water, while the limited supplies of helium is mainly extracted from natural gas fields. However, safety is an important factor. The farther into the atmosphere balloons go, the more increases the risk of lightning strike. So turning, lifting unit and components over all of them must be isolated from earth is electrically charged to the same electric potential as that of high-altitude atmosphere, to avoid attracting lightning strikes, and inductively connect the source of electricity. Isolating parts of the system start-up of rockets can preferably be made of ceramics or glass.

The shell of the balloon should be light, durable� and resistant to ultraviolet (UV) radiation. Recently done much work on these membranes in the construction and operation of airships and other balloons.

Advantages of the system start-up of rockets of the present invention in comparison with used at this point is quite obvious. The first stage of the Saturn V rockets launched by NASA, consumed 203000 U.S. gallons of RP-1 (refined kerosene) and 331000 U.S. gallons of liquid oxygen (LOX) for 2.5 minutes. The present invention can significantly reduce the amount of fuel to lift the same payload due to the rise of many smaller missiles with the help of electric trucks with equivalent payload up cables/ropes that held the balloon, at the right height before you start. In the existing level of technology using a huge amount of non-renewable energy from fossil fuels. For example, the ship Virgin Galactic White Knight Mothership uses tons of kerosene JET A-1 for the starting height for Space Ship Two, which uses a kind of rubber with a liquid oxidizer, giving black sgeometry exhaust. Solid boosters often leave fluoride and chloride compounds and partially burned hydrocarbons, among other harmful residue in the exhaust. All these emissions and residues pollute the atmosphere. On the other hand, the energy used to lift trucks in �predpochtitelno form of the present invention, produced from renewable energy sources, and much of it is recovered when the friction drives are switched to the regeneration mode when the truck comes back down on cable/rope path.

In addition, the present invention significantly reduces the cost of space flight to remove debris in orbit around our planet and even for the construction of orbital repair facilities. A living example of dangerous orbital waste in space was the clash unused Russian telecommunications satellite Cosmos 2251 with the American satellite mobile communications, owned by Iridium-February 11, 2008. Each satellite moving with an orbital speed of 17500 miles per hour. The wastes from this collision were estimated at $ 500k. NASA stated that these wastes from the collision, increasing the risk of collision with the International space station. International Association for the advancement of space safety offered be sure to remove unused satellites.

Thus, the present invention includes a number of cables/ropes that held the balloon, which can very effectively be used for different purposes. When you use to launch the amount of fuel required for start-up, is greatly reduced, because the missiles are transported in the upper layers of the at�of ospery before starting their engines. The use of missiles for different purposes and because of the reduced energy consumption and thus reduce costs in such applications as sports entertainment with the use of rockets, parachutes, small jet engines or other devices, can be economically advantageous. Similarly, the system for servicing satellites become more feasible and economical. Using high-altitude platform, for example, for telescopes, can be extremely beneficial to scientists.

In the above-described preferred embodiment, the implementation includes three cable/cable for three-phase power supply. It is likely that each cable/rope will transmit exactly one third of the electricity. If this is impossible or, if possible, this can be done during use of the system start-up of rockets of the present invention, it is necessary to provide the design or in the form of the neutral line, or ground to achieve the desired electrical balance between each of the three cables/wires.

The present invention has many applications in addition to described above. There is a huge amount of debris orbiting around the earth from many in the space for missiles. According to estimates by NASA in 2009, the network of observation stations to�smijesni space USA tracked nearly 14,000 objects. Many of these threatening objects to other devices that can pass through the respective orbits of these objects, because collisions can cause significant damage. The present invention can be used to place traps debris in orbit for the removal and excretion of orbit such trash economical and safe manner, or reuse such items that can be recycled to create useful structures in orbit.

Described in this document, the cables are the standard cable consisting of twisted metal he lived and shows how twisted in a spiral. This is the wire ropes, which are electrically conductive, similar to those used in cars cable cars, funiculars and chairlifts. Also described various embodiments of cables/wires. However, the term "cable/rope" is not limited to wire ropes. Cables/cables can be rods of different sorts, in the form of separate sections connected by various types of welding, or a number of small units that articulate between themselves to achieve the required length. Important characteristics of any used cable/wire rope of the present invention is the strength, conductivity and the ability to make such�tion and stretching, which exist at high altitudes, for transporting devices for transporting missiles and other devices described herein. These rods or other types of cables/wires can be modified in various aspects, for example, to change the surface or configuration of the surface of the rods or cables/rods to make the system work more effectively, when the rods or other cables interact with friction drives the respective devices transporting missiles. Such rods may have a cylindrical cross section or other cross-section depending, for example, from the nature of the friction drives. Fig.40 and 41 on the rod 990 is shown connecting flanges 992 connected by joints 994. The flanges have mounting holes 996 necessary for attaching the dividers to other designs on the side of the rods were to be bolted, and other joints. They can be mounted by gluing, welding in the solid phase and other types of welding (e.g., friction welding, explosion welding, brazing, etc.) or articulation, as deemed appropriate. The rods can be modified differently depending on such factors as the nature of the connection of the respective terminals, the conductivity of the rods, security wiped�her, etc.

The invention has been described in detail with particular reference to its preferred implementation option. However, possible variations and modifications within the essence and scope of the present invention for specialists in this field on the basis of the above material and the attached claims.

1. The system launches, including:
a set of transmission lines for transmitting electrical energy from a remote power supply system on earth, thus the electric energy can be continuously removed along a specified set of transmission lines, the transmission lines have a lower end section for location at low altitude and the upper end section to lift to high altitudes;
the set of lines in the device for transporting the rockets to transport the device transporting missiles between low altitude and high altitude, with the specified line device for transporting missiles have lower end section for location at low altitude and the upper end section to lift to high altitudes;
secondary lines, functionally attached to the specified set of transmission lines and to a specified set of lines in the device for transporting missiles to its location at high altitude, the greater height of these lines and �lines shown in the device for transporting missiles.
functional design, functionally connected to said secondary lines to perform the functions specified system of rockets;
balloons attached to these sets of power lines and these lines in the device for transporting missiles to hold these sets of power lines and these lines, the device for transporting missiles up at high altitude, and
stretch the balloons attached to the secondary lines for the transmission of tension specified secondary lines, when these lines and these lines handling devices for missiles at high altitude above the earth.

2. System of a missile according to claim 1, in which the corresponding lines of the specified set of transmission lines and the corresponding lines of the device for transporting rockets specified set of lines in the device for transporting missiles wholly integrated into the main power and transmission cable/cable, which is part of the basic set of power and transporting cables/wires.

3. System of a missile according to claim 2, in which the specified set of core power and transporting cables/cables consists of three units for three-phase transmission of electricity.

4. System of a missile according to claim 3, in which these balloons are functionally periodic�key attached to the specified set of core power and transporting cables/wires along the length of the specified set of core power and transporting cables/cables for total retention of the specified collection basic cables/cables, and any other construction, portable a specified set of core power and transporting cables/wires.

5. System of a missile according to claim 4, which further includes a set of dividing blocks located periodically along the length of the specified set of core power and transporting cables/wires, with each specified set of the separation of the blocks has a design capture cable/rope to capture the relevant elements of the specified set of core power and transporting cables/cables to preserve a certain distance between the main power and transporting cables/cables in the specified set of core power and transporting cables/wires, these balloons appropriately functionally attached to at least one specified separation unit.

6. System of a missile according to claim 4, which additionally includes the docking station, functionally attached to the specified set of core power and transporting cables/wires in end position along the length of the specified set of core power and transporting cables/wires, and the specified docking station has a construction providing for the reception of the device for transporting missiles in �amkah preparation for the launch of the rocket, which is transported in the transporting device of the missiles.

7. System of a missile according to claim 6, in which these secondary lines contain power and guide cables, functionally attached to said docking station and which can be raised to a greater height than the height of the specified docking station and system launch additionally includes balloons, functionally connected to said secondary power guides and cables/cables for tensioning the specified main power and transporting cables/cables and secondary power and guide cables/wires.

8. System of a missile according to claim 7, which additionally includes block lifting ring, functionally coupled with said secondary power and guide cables/cables to generate electricity from specified secondary power guides and cables/cables and the direction of them, which makes the specified block of the lifting ring is located above the specified docking station and can functionally coupled to the device transporting missiles positioned in said docking station, and comprises a tubular lift ring that surrounds and functional gear device transporting missiles, and block rotation of the device for transporting missiles to tilt truststoretype ring to the desired angle of the missile launch.

9. System of a missile according to claim 8, in which the specified block turning the device transporting missiles mounted rotatably tubular lift ring about its axis, the tubular lift ring includes a clamping mechanism for clamping with the possibility of disconnection of the device for transporting missiles to the center of gravity coincides with its geometrical axis.

10. System of a missile according to claim 8, which additionally includes the lower lifting block located above the specified block lifting ring, when the system of the missile is operational, a set of holding tertiary cables/wires coming from the specified base lift unit, for functional connection to the specified block lifting ring and retaining the specified block of the lifting ring, and end capture device for transporting missiles, located between the specified lower lifting block and the specified block of the lifting ring, and functionally attached to the specified base lift unit, moreover, the specified end grip can be hooked with the possibility of disengagement and locking device with the transportation of missiles in the specified block of the lifting ring, and the specified lower lifting unit that lifts the specified limit capture to lift �disorder of the transport of missiles to engage with the specified block device is rotated transporting missiles to the missile from the device for transportation of missiles is in the specified block of the lifting ring.

11. System of a missile according to claim 10, which additionally includes a device for transporting rockets to transport missiles along these lines, friction drives for the propulsion of said device transporting missiles along these lines, the device for transporting missiles, and these friction drives include: the electric power apparatus for receiving electric power from a specified set of transmission lines, when the specified friction drives requires energy, the device transporting the rockets moved up on the designated lines transporting missiles and for supplying electrical energy to the transmission line; when the specified electrical supply apparatus generates more electrical energy than required friction drives, because the specified device is transporting missiles moves down the mentioned lines in the device for transporting missiles.

12. System of a missile according to claim 11, in which each of respective said devices transporting missiles is the corresponding truck having an interior compartment designed to accommodate therein the missiles, and the missile is ejected from the specified internal compartment during start-up, and the specified block turning the device transporting missiles is a block p�gate truck.

13. System of a missile according to claim 12, in which these friction drives include a set of friction wheels associated with the said respective carriage for engaging relevant specified main cables/wires of a specified set of core power and transporting cables/cables for transporting the respective specified truck along a specified set of core power and transporting cables/wires.

14. System of a missile according to claim 13, in which the specified tubular lifting ring, is a hollow device, which surrounds the gears and functionally corresponding to the specified cart.

15. System of a missile according to claim 13, which further includes the lower lifting block containing a set off of it holding tertiary cables/cables for functional connection to the unit lifting ring and retaining block lifting ring, and end the seizure of the truck, located between the specified lower lifting block and the specified block lifting ring and functionally attached to the specified base lift unit, and the specified end grip truck can hang with the possibility of disconnection and lock with one of the respective dollies in the specified block lifting ring, moreover, the specified lower lifting block lifting �analogo capture specified truck for lifting the said truck to the appropriate gear with the specified block turning the truck to the launch of a rocket from the said truck is in the specified block lifting ring and stabilizes the specified carrier during its ascent or descent while in a vertical position.

16. System of a missile according to claim 12 in which the said truck includes a continuous pressure-resistant and temperature of the pipe to hold the missiles, and this pipe prevents the release of hazardous exhaust gases from said truck through either side of the said truck.

17. System of a missile according to claim 12, in which the mentioned secondary lines represent power and guide cables, further comprising a mounting frame suspended balloons, attached to said secondary cables/ropes, and these stretch a balloon attached to said mounting frame suspended balloons to transmit sufficient tension for the purpose of the aggregate hold at least one pertinent of these trucks, the secondary cables/cables and any other structures that are held by specified mounting frame suspended balloons under said mounting frame.

18. System of a missile according to claim 12, in which a specified docking station is attached to the upper ring portion with an axis of rotation, the lower annular portion coaxial with the said upper annular part, wherein the upper annular portion and a lower annular portion are connected by a lower support ring,�asana upper annular part and the lower annular portion can rotate relative to each other, and lower system rotary actuator for driving the specified upper annular part and said lower annular portion in the opposite direction with respect to said lower support ring, the specified mounting frame stretch the balloon is attached to the top ring with the axis of rotation, and the lower ring coaxially specified top ring, the top ring and the bottom ring are connected together by the upper support roller ring, and the upper system of the rotational drive unit for driving the movement of the upper ring and the lower ring in the opposite direction around said support upper rotating ring; the upper system of the rotational actuator and the specified lower system rotary actuator functionally connected to each other to coordinate the rotation of this lower ring portion and said upper annular portion, rotating as one unit, to counteract caused by the wind rotation and rotation that occur because of rotation of the respective one of these trucks, when the lower end of the said truck is held in said upper annular portion and corresponding to the specified cart rotates for tool.

19. System of a missile according to claim 18, in which the specified upper Vra�atelnoe drive system includes top power lifters to rotate or facilitate the rotation of the design specified upper rotational drive, the specified lower rotational drive system includes lower power lifters to rotate or facilitate the rotation of this lower rotational drive system.

20. System of a missile according to claim 18 in which each of the applicable designated trucks have a longitudinal axis and an external radial grooves running along the respective specified truck, and the specified upper annular part and the lower annular part of the said docking station coaxially aligned, defining an internal space for reception and transmission of respective one of these trucks, this docking station has an internal guides truck for transmission to the specified friction drives and to enter into specified radial grooves to maintain the appropriate trucks in a level and stable position when power is applied to the relevant specified truck.

21. System of a missile according to claim 15, in which respective truck have a triangular cross section with angular edges and radial angular grooves running along these corner edges; wherein said block lifting ring is retained specified tertiary cables/cables and the tubular lift ring has a triangular cross section for receiving one of COO�concerned these trucks, moreover, the specified tubular lift ring has coming in, the inside rails of the truck that are injected into these radial grooves corresponding to these trucks to maintain the appropriate orientation of these trucks in the specified tubular lift ring, wherein the tubular lift ring has a longitudinal axis coincident with the longitudinal axis of the said truck, and a specified angle to the longitudinal axis relative to the earth is the angle of elevation of the specified tubular lift ring.

22. System of a missile according to claim 21, in which the specified block rotation of the trolley is mounted for tilting of the specified tubular lift ring with respect to said secondary cables/cables; and
pair these tertiary cables/wires located on opposite sides of the specified tubular lift ring; and
this block rotation of the bogie includes:
the rotational drive system, functionally attached to the specified tubular lift ring for rotation of the specified lifting ring;
guides of the lifting ring, functionally attached to said tertiary cables/cables; and
pivot pins attached to the specified tubular lift ring and extending from the tubular lift ring, and these pivot pins pivotally PR�mounted to each of the guides of the lifting ring; and
the specified rotational drive system rotates the specified tubular lift ring for rotation around the specified pivot pins to change the elevation of the specified tubular lift ring and any of the trucks taken thereon; and
the center of gravity of the specified tubular lift ring falls into the geometric center of the specified tubular lift ring, wherein said center of gravity coincides with the axis of these pivot pins.

23. System of a missile according to claim 22, in which the specified tubular lift ring includes a clamping mechanism for clamping with the possibility of separation of the relevant specified trucks with the center of gravity of the respective last-mentioned specified truck, located on the axis of these pivot pins; and the tertiary cables include two groups of cables/wires fixed length specified tertiary cables are installed with the possibility of adherence to these guiding of the lifting ring for mounting the unit moving the lower lift guide to the lifting rings, these tertiary cables spaced at 180°, and these tertiary cables are installed with the possibility of acceding to the specified block movement of the lower lift.

24. System launch on �.3, which further comprises at least one big harness having interconnected brackets and holders of a balloon on a specified great harness for attaching these balloons, wherein the said holders of the stretch of the balloon is attached to said main power and transporting cables/cables to ensure the specified tension.

25. System of a missile according to claim 24, which additionally comprises at least one bottom of the separation unit for the separation of these main power and transporting cables/wires from each other and attach the applicable designated holders balloons to these large bundles and corresponding to these balloons.

26. System of a missile according to claim 25, in which at least one big gut has three bracket, forming an equilateral triangle, and the specified at least one bottom of the separation unit includes triangular brackets bottom of the separator, forming an equilateral triangle, parallel to the respective brackets corresponding to these large bundles, wherein at least one of the separation unit has a connecting design of the bottom of the separation unit between the respective brackets of the lower separator and the specified one system launch additional�individual includes the wiring harness of the lower separator, connecting the corresponding connecting structure of the bottom of the separation unit with the relevant specified by the holders of the stretch of the balloon.

27. System of a missile according to claim 26, which further comprises an upper separation unit, which bracket has three forming an equilateral triangle, having a design in the respective intersections of the three brackets to separate these main power and transporting cables/wires from each other.

28. System of a missile according to claim 27, in which the specified upper separation unit includes three upper bracket separator, forming an equilateral triangle, and these brackets are parallel with the corresponding respective brackets these large bundles, and the system of missile further includes a connecting construction of the upper separator, located at the intersection of the respective brackets of the upper separator and the connecting ties of the upper separator connect specified the connecting construction of the upper separator and the opposite ends of these brackets corresponding to these large bundles.

29. System of a missile according to claim 24, which additionally comprises the reaction pushers large bundles, functionally connected to at�asanam with at least one big bundle for orientation specified docking stations, in this case the specified lifting ring and the specified limit capturing device transporting missiles should be oriented relative to the vertical to compensate for the force of the wind and blowing any of the balloons.

30. System of a missile according to claim 10, in which the specified block turning the device transporting the missile is in free fall after the misfire and failure of the rocket from the specified device transporting missiles, these power and guiding secondary cables have sufficient length to secure a sufficiently long period of time when the local acceleration under the action of gravity lower pulley block with any hanging items on it, which should be sufficiently long after the misfire to ensure reliable braking device transporting missiles with her rocket until it stops.

31. System of a missile according to claim 2, in which the specified core strength and conveying cable/rope represents the main part of the cable/wire rope, consisting of a wire having a loop parcels coming from a specified main part of the cable/tether for attachment of items to the specified basic cable/rope, with each loop comes out of the designated primary frequent� and returns to the main part of said main cable/rope.

32. System of a missile according to claim 31, which further includes an adaptive connector having aligned holes on the wall, and also the connector to pass through a couple of these aligned holes and one of the loop sections to attach the specified adaptive connector to the specified basic cable/rope.

33. System of a missile according to claim 6, further comprising a launcher for launching the respective devices transportation of missiles, and missile launcher includes a turntable mechanism for receiving the respective devices of transporting missiles for delivery specified on the docking station, wherein the swivel mechanism includes:
the base of the turntable; and
tower unit mounted on the specified radix turntable, the lower end portion of a specified set of core power and transporting cables/ropes attached to a given tower unit, and a conveying structure for conveying the respective devices transporting missiles from the specified tower block and along these main cables/wires.

34. System of a missile according to claim 33, in which the specified tower unit includes:
rotating turntable, rotating in relation to specified�at the base of the turntable, the given turntable has a hole rotating turntable for receiving the respective devices transporting missiles;
lower guide tube mounted on said rotatable turntable, and the specified lower guide tube has a hole in the lower guide tube, which can be aligned with said hole of the rotating turntable and has a size corresponding to the specified hole of the rotating turntable; the indicated lower guide tube receives the appropriate device for transporting missiles, while the lower guide pipe guiding structure includes a lower guide tube to accommodate the respective devices transporting missiles in the specified hole of the lower guide tube;
secondary guiding structure comprising a one-piece tube having orifice tube, and a secondary guide structure that can be aligned with the specified design guide lower guide tube for connection of the specified main cables/wires to the secondary guide structure; and
a rotating unit for rotating the specified bottom of the guide tube in relation to said secondary guide structure for aligning the specified overstaining of the guide tube and the specified hole one-piece pipe, and for alignment of the guide structure of the lower guide tube and said secondary guideway design;
the specified rotating turntable, rotating the specified lower guide tube and a specified secondary guiding structure in the desired direction to move said device transporting missiles.

35. System of a missile according to claim 34, in which the corresponding device for transporting missiles have respective longitudinal axis and a set of external grooves running along the length of the respective devices transporting missiles, wherein said lower rail structure and the specified secondary guideway design are the inner rails of the truck, plug in a set of external grooves in the respective devices transporting missiles.

36. System of a missile according to claim 34, in which the specified tower block further includes a clamp comprising a pair of spaced brackets mounted on pivots on said turntable, wherein said lower guide tube installed on the hinges between said pair of brackets, the specified guide tube and the specified secondary guideway is installed on hinges between said pair of brackets, wherein the axis of rotation specified turntable and MC�provide lower guide tube intersect orthogonally.

37. System of a missile according to claim 34, further comprising a lifting unit for lifting the transportation device of rockets specified in a tower block, lifting block for connection of the respective devices of transporting missiles for moving the respective devices of transporting rockets specified in a tower block.

38. System of a missile according to claim 37, in which a specified rotating turntable has a hole for receiving the respective devices, transportation devices, and the lifting unit includes:
the hydraulic cylinder;
the hydraulic piston is functionally located inside the hydraulic cylinder;
the hydraulic piston rod attached to the specified hydraulic piston and movable in the axial direction relative to the hydraulic cylinder;
upper swivel unit, functionally mounted on the specified hydraulic piston, for receiving the respective devices transporting missiles and alignment devices transporting missiles with the specified hole of the rotating turntable; and
the rotational drive for rotating the specified upper swivel block.

39. System of a missile according to claim 38, in which the specified upper rotary unit further includes a table mounted on the uke�ƈ rotating support base for receiving for transportation related devices transportation of missiles; and
upper swivel unit takes appropriate device for transporting missiles from the lateral conveying devices having a set of side wheels of the transporting device and the specified section of the table is associated with the ruts, aligned with a set of side wheels of the transporting device to enable the receiving side of the transport device on a specified section of the specified table pulley block.

40. System of a missile according to claim 39, in which the devices transporting missiles are truck, the system of missile further includes a closed track having a set of ruts, along which moves a set of side wheels of the transporting device, the design of the missile within the specified closed-loop paths for the storage of trucks missiles, loaded with missiles, which must be run with the specified system launches, the compartments of the Assembly specified on a closed track storage carts missiles, loaded with missiles, lateral transport device for transporting the respective truck loaded with missiles from this construction, the storage of rockets in one of the compartments of the Assembly and to the specified section of the table for movement to said lifting means.

41. System of a missile according to claim 40, which further includes a system load�narrow missiles to remove trucks, loaded with missiles, from this construction, missile storage and moving the respective carriages to the respective compartments of the Assembly, the design load of missiles includes:
cross loader is moved relative to the respective compartments of the Assembly;
a set of ruts, which moves the corresponding transverse loader; and
the guide block for the specified direction transverse loader and components specified transverse loader.

42. System of a missile according to claim 41, in which the cross loader is moved longitudinally with respect to the compartments of the Assembly, wherein said transverse loader includes a lifting unit that is moved transversely to the specified transverse to the boot loader and vertically for receiving the respective devices transporting missiles at a relatively great height, and lowering the respective devices transporting missiles in the appropriate compartments of the Assembly.

43. System of a missile according to claim 42, in which the specified guide unit includes:
wheeled trolley that can move along a specified set of ruts and move the specified transverse loader along a specified set of ruts; and
rails going across a specified cross-loader, wherein said lifting unit can be moved along the specified rela�S.

44. System of a missile according to claim 43, which further includes a wheeled trolley of the lifting unit to move the specified lifting unit along these rails.

45. System of a missile according to claim 44, in which the specified lifting unit includes:
guide support apparatus mounted on said wheeled trolley pulley block and running in a vertical direction; and
lift, functionally associated with the specified reference guide apparatus, wherein said Jack has a Electromechanical design to move the specified lift at the specified reference guide device;
specified lifting unit that lifts the rocket and trucks with these storage racks and lowering these missiles and trucks on the corresponding compartments of the Assembly, and the specified portable loader, moving the missiles and the trolley between the shelves and the compartments of the Assembly.

46. System of a missile according to claim 45, in which the missiles have fastening receivers of the lifting unit and the lifting unit further includes a gripping unit for functional actuation of the fastening receivers of the lifting unit for the respective missiles located in the relevant specified compartments of the Assembly to the collection�and had the opportunity to raise the missiles from the respective compartments of the Assembly.

47. System of a missile according to claim 41, in which the specified sections of the Assembly are located beneath the surface of the earth, have the form of an inverted truncated cone, made of concrete to limit the damage caused by the detonation of rocket fuel by the reflection of the blast upwards and sideways.

48. System of a missile according to claim 12 in which the said truck includes opposite end of the hole and the end caps on the applicable designated terminal holes to protect the internal parts of the respective specified truck and under any applicable designated truck rockets from atmospheric influences.

49. System of a missile according to claim 2, which further includes a docking station, attached to the specified set of core power and transporting cables/wires in end position along the length of the specified set of core power and transporting cables/wires, and the specified docking station has a construction providing for the reception of the trucks transporting the telescope and the containment system of the telescope, functionally connected with the specified docking station.

50. System of a missile according to claim 49, in which a specified retention system of the telescope includes a rotating turntable, the design of the retention of the telescope to hold the telescope to the specified torque�Xia rotating platform and the design of the tilt of the telescope.



 

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FIELD: aircraft engineering.

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FIELD: aircraft engineering.

SUBSTANCE: aircraft (AC) is placed in the Launcher, or in a Launcher transport and starting barrel, or partially in Launcher TSB with an external arrangement of the jet nozzles, or a transport and starting container (TSC), or TSC of Shaft Launcher, the starting propulsion system (SPS) is fixed in AC front part, AC is partially moved forward, SPS is started, the traction is formed by two jet nozzles located on a lateral surface of SDU at an angle to a longitudinal axis of AC, the front part of LA is protected during acceleration by the fairing fixed on SPS, SPS is separated by means of draft force.

EFFECT: invention allows to decrease the weight of an aircraft structure, launcher start load and simplify a launcher design.

7 cl, 4 dwg

FIELD: weapons and ammunition.

SUBSTANCE: device for missile launch contains a running launch pipe with front and back end faces, which is connected with the carrier, a reflector hingedly fixed at a back end face of the running launch pipe and the reflector driving mechanism. The reflector is made consisting of bow-shaped trapezoid plates fixed hingedly on the launch pipe and installed with overlapping one with reference to another, forming a convex hemispherical screen. Plates are fitted with the driving mechanism.

EFFECT: improvement of reliability of operation of the device by decrease of gas-dynamic impact of discharge jet onto the reflector and the starting pipe with decrease of power impact onto the carrier during the missile launch.

3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: device for missile launch contains a running launch pipe with front and back end faces, which is connected with the carrier, a gas reflector located at a back end face of the running launch pipe and connected to it. The gas reflector is designed as a circular solid fuel charge with the ignition source located in the circular housing from outer side of the running launch pipe. In the bottom part of the circular housing from the back end face of the running launch pipe a circular row of exhaust outlets is made.

EFFECT: improvement of reliability of work by decrease of power impact of a shock wave on the carrier during start of missile from the launch pipe due to interaction of shock wave with powder flows of gas flowing from the circular housing.

3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: fireproof cover of a multi-barrel launching unit (LU) from pressed fibre glass with flat layers, which is fixed on the front end face of a launching pipe by means of a locking device, includes an outer surface with conical and radial surfaces, a fire-resistant coating with an epoxy composition from epoxy resin, Aerosil glass powder, technical carbon, a hardening agent - polyethylenepolyamine, asbestos fibres cut to pieces and with partial saturation of edges of cut layers of fibre glass depending on saturation depth, thickness of one layer and epoxy composition.

EFFECT: invention allows improving reliability of a fireproof cover.

4 cl, 3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: method of missile takeoff from the transporter-launcher containers (TLC) consists in inflation with the gas which does not support combustion of sub-cap volume of TLC with simultaneous ingress of gas through the obturator in the bottom volume, after which the inflation is switched off when achievement of the desired pressure in the sub-cap container volume, followed by inflation of the bottom volume of the container with gases from powder pressure accumulator (PPA). The device for implementation of missile takeoff from the TLC comprises an obturator, a PPA, a high-pressure cylinder with an on-off valve connected to the sub-cap container volume by the pipeline, a pressure indicator unit with the pipeline, the opposite end of which is located in the sub-cap container volume.

EFFECT: creation of conditions for reliable underwater missile takeoff from TLC by eliminating hydraulic, oscillating and vibrating effects on the missile housing.

2 cl, 2 dwg

Launching facility // 2544037

FIELD: weapons and ammunition.

SUBSTANCE: launching facility for missile launching includes base (1), rack (2), and frame (3) with guides (4). The guides have a possibility of independent guidance from each other as to an angle of elevation. On guides (4) there installed are remotely controlled devices (5) of depression of a limit stop retaining the missile. The guides are charged with target-missiles (6) in launching containers. Missiles (6) are electrically connected to connectors of the launching facility.

EFFECT: enlarging technical capabilities of a launching facility; improving quality.

2 cl, 2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: device for launching rockets comprises a launch container having front and rear ends, mounted on the base of the sighting and launching module (SLM), and a gas-blast shield. The gas-blast shield is made in the form of a flat sheet-roof, rigidly secured to the SLM base and placed over the launch container. The roof in the area of the rear end of the launch container is bent upward by the amount of 20-30°. The bending line is perpendicular to the longitudinal axis of the launch container and is spaced from the rear end by the amount of (0.6-0.7)D in the direction of the rocket launching, where D is the inner diameter of the launch container, and the length of the bent part is (1.9-2.1)D.

EFFECT: reduction of the impact of the component force of the gas jet on the container, reduction of the size and weight of the container, and increase in reliability of firing of the launching device.

3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: antitank missile system comprises a launcher with a backsight and guidance and control equipment, the transport and launch container with a guided missile mounted on the launcher, the measurer of the coordinates of the launcher location, radar of target acquisition and tracking independently mounted relative to the launcher, the measurer of the coordinates of location and the measurer of the radar point angles relative to the coordinate system of shooting, device of target detection made in the form of two modules, the first of which comprises the measurer of point angles of the launcher, and the second module with the indicator is connected to the radar through the communication channel. The launcher with the backsight and the guidance and control equipment, the first and second modules of the target detection device, the measurer of the coordinates of the launcher location is mounted on the first self-propelled machine. The measurer of point angles of the launcher is made in the form of sensors of rotation angles of the launcher on azimuth and the angle of altitude relative to the first self-propelled machine. The measurer of the coordinates of the launcher location and measurer of position angles of the first self-propelled machine relative to a geographic coordinate system are made in the form of the navigation system of the first self-propelled machine. The second module of the target detection device is made in the form of a computer system with a keyboard and an indicator for indication and control. The radar of target acquisition and tracking, the measurer of coordinates of the location and the measurer of the radar point angles relative to the coordinate system of shooting are mounted on the second self-propelled machine with the ability of the radar antenna rotation with additionally built-in automated drives of vertical and horizontal guidance and with the ability of powering from the power supply system of the second self-propelled machine.

EFFECT: increasing automation of control of the antitank missile system and improvement of survival of the fighters of the subunit.

1 dwg

FIELD: aircraft engineering.

SUBSTANCE: rocket cryogenic upper stage (RCUS) designed according to the tandem layout comprises a fuel tank with an instrument compartment and transitional system for fastening of a spacecraft, an oxidizer tank (OT), intertank spacer, RCUS mid-flight engine (MFE), an intermediate compartment, fire and explosion prevention system, thermal mode maintaining system with the unit of demountable connections of communication with the land equipment and separable inlet pipelines, manifolds for purging of stagnant zones and device for maintaining of the thermal mode of the zone and RCUS equipment, a sealing diaphragm, the detachable head fairing (HF) with windows for detachment of the fire and explosion prevention system and devices for maintaining of the thermal mode of gases for purging of RCUS zone, additional thermal insulation of RCUS zone, a part of separable inlet pipes of manifolds with demountable joints and the unit of demountable connections for communication with the land equipment, an intertank spacer, conjugated with the intertank frame for fastening OT with MFE and conjugated to the top spacer of the separated intermediate compartment with the units of connection and separation with US and HF.

EFFECT: invention allows to improve fire and explosion safety of upper stage.

2 dwg

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