Balloon-space power supply system
SUBSTANCE: invention relates to systems intended for power supply of ground objects from space. Power supply system comprises, at least, one space solar power station 1, ground control station 2 with accumulation system 3, and intermediate power reception station composed of controlled tethered balloon. Solar photo converters 5 and lasers 6 are arranged on the surface of balloon 4 for guidance to space power station 1 while on side facing the Earth IR converters 7 are arranged. Balloon 4 is preferably shaped to disc retained above clouds by cable 8 connecting it with ground system 3. Motors 9 connected with service module 10 are mounted on side surface of balloon 4. Cable 8 is connected with the system of balloon gas bags 11. Space solar power station 1 represents the Earth satellite composed of self-contained photo converting modules, focusing mirror system, super condensers, and remote power transmission system. Besides, it comprises instrumentation-propulsion module with control systems and data exchange system.
EFFECT: higher power production efficiency.
4 cl, 3 dwg
The invention relates to power supply systems, namely terrestrial consumers from space.
Known space solar power to provide electricity terrestrial consumers, including solar power plant and a system for remote transmission of energy on Earth in the form of microwave or laser radiation (application for a patent RU №94032672/11 from 08.09.1994, B64G 9/00; patent RU No. 2094334 from 18.04.1994, B64G 1/44, Chetland, "Space technology", M., ed. World, 1986, str-237). The disadvantages of these plants are:
1. Large design, which cannot be transported to orbit all at once, requiring a large number of start-up of the launch complex and expensive Assembly in space;
2. Multi-step conversion of solar energy equipment with large size parameters and the complex and heavy cable network, increasing the risk of failure of individual nodes and, in extreme cases, the equipment as a whole;
3. When using a laser beam as a method of energy transfer, the absence of reception of energies above the cloud zone will result in the loss of part of the radiation in the troposphere and, therefore, decrease the efficiency of the process.
4. When using the microwave beam as a method of energy transfer, with the considerable divergence, its area on the Earth will reach a large size, which requires the creation of the same size of the receiving rectenna that leads to higher power and lower efficiency of the receiving elements rectenna, which leads to lowering the efficiency of the power plant, increasing the area occupied by the ground point of the energy, as well as to the deterioration of ecological safety of the radiation field at the location of rectina;
Also known solar power, placed on a tethered aircraft lighter than air, on surfaces of which are covered with flexible solar cells, and the devices are located above the cloud layer (patents for inventions: EN No. 2377440 dated 18.06.2008, F03G 6/00; RU №2389900 from 16.03.2009, F03G 6/00). The disadvantages of these plants are:
1. The spherical shape of the balloon, leading to inefficient use of solar cells and, consequently, reduce the efficiency of the process to generate electricity;
2. Using film solar cells, having by their physical nature of low efficiency;
3. Daily operations of winding on the drum and unwinding with his rope-cable, which significantly increases the risk of accidents and wear and tear of the unit.
4. Use to generate electricity only solar radiation.
The closest is taken for about Otep, the power supply system of terrestrial consumers from space, which includes at least one space solar power and the ground station receiving energy transmitted from space solar power (inventor's certificate SU # 946372 from 31.10.1980, H01J 17/00, B64G 1/10). The disadvantages of this system are:
1. The presence of the cosmic power and a separate space relay or flotilla separate cosmic power plants with passive repeaters that redirects energy, greatly complicates and increases the costs of implementation of this power;
2. When the transmission power using a microwave beam, which has a significant divergence directly to Earth, its surface area on the Earth will reach a large size, which, as mentioned above, requires the same size of the receiving rectenna that, in turn, leads to higher power and lower efficiency of the receiving elements rectenna, and, accordingly, leads to a decrease in efficiency of the power plant, increasing the area occupied by the ground point of the energy, as well as to the deterioration of ecological safety of the radiation field at the location of rectina;
The technical solution of the present invention is directed to the achievement of the technical result consists in HC is the chances of improving the amount of energy in a smaller surface receiving the item, as well as to improve environmental performance in the area of the specified item.
Below, in the disclosure of the invention and the description of its implementation and use, including in cases of execution, shall be called and other types achieved technical result.
This technical result is achieved by the fact that, as known, is used as a prototype, the power supply system that includes at least one space solar power and the ground station receiving energy transmitted from a space solar power station, the proposed balloon-space energy system is supplied with the intermediate point of the energy representing the aircraft lighter than air as managed tethered balloon, with mounted on it service management module balloon. On the surface the specified device, facing away from the surface of the Earth are solar panels, for example three-stage nano-heterostructure the solar cells, and laser focused on space power. On the surface of the balloon facing the surface of the Earth, are infrared panels and above service module, with the specified balloon attached above the zone of clouds by means of a rope, cable, Saedinenie ground point of the energy. Tethered balloon made disc-shaped and forms the perimeter of the lateral surface evenly mounted motors (best of four), United with the service module. On the cable-the cable that goes from the service module, sequentially fixed obespechivaushyi balloon shell. Space solar power station is a satellite placed in orbit, consisting of Autonomous (independent) photoperiodic modules focusing the beam on the Ground, mirror systems, supercapacitors, remote power transmission, instrumentation and propulsion compartment with control systems, and systems for receiving control commands and outputting information about the state of operation of the satellite to the ground station.
The specified implementation of energy systems using intermediate receiving ground point as the aircraft lighter than air (tethered balloon), fixed at a height above cloud level, allows not only to take energy from space stations, but due to the location on its disc-shaped surface of the triple junction heterostructure and infrared panels in greater numbers than on the spherical surface, to increase production of electricity from solar radiation, and to use the e is ergiu thermal radiation of the Earth. Location above Ground level can reduce the area occupied ground adoptive point, in addition, clouds below the aircraft, do not close the panels located on its surface, and the development of their energy coming from the Sun, goes all day time, additionally, the cloud does not scatter the laser radiation from space solar power. The use of rope-cable allows you to avoid significant losses in energy transfer and destabilizing stability of the aircraft - and balloon-on the same, and obespechivanie cable-cable, directed and posting on additional balloon membranes. In addition, a uniform location on the perimeter of the balloon membrane having the form of a disk, electric motors allows you to maintain a static state intermediate receiving item (for example, when the wind) and to ensure its slope, seeking to normal against laser radiation with space solar power. The proposed system implementation can significantly reduce the area of its ground segment, significantly increasing the number of the received power (laser radiation from the space station, solar radiation and infrared radiation from the Earth).
The entity from whom retene illustrated by drawings, showing:
- figure 1 - balloon-space energy system;
- figure 2 - the balloon panels;
- figure 3 - ground segment system.
The proposed balloon-space energy system includes at least one space solar power system 1, the ground station receive power, including ground control station 2 power system and storage system 3, and an intermediate point of the intake of energy, representing an aircraft lighter than air as managed tethered balloon 4. On the surface of the balloon 4, facing away from the surface of the Earth are solar panels 5 and the laser 6 for guidance on space power plant 1, and on the side facing to the surface of the Earth, bred infrared solar cells 7. For the convenience of placing the panels 5 and 7 aircraft 4 is made in the form of a disc. When the device 4 is fixed above the zone of clouds through the cable-cable 8 connected to the cumulative ground system 3. On the side surface of the balloon 4 evenly along the circumference mounted electric motors 9, United with mounted in the bottom center of the balloon 4 service module 10, which houses all the control apparatus and apparatus for automotive and balloon, cables and antenna for accepting control signals from a ground point and issuance of state information systems of the balloon (not shown), the cable-the cable 8 extending from the service module 10, sequentially fixed obespechivaushyi balloon sheath 11. Space solar power plant 1 is a satellite placed in orbit, consisting of Autonomous (independent) photoperiodic modules focusing the beam on the Ground of the mirror system, supercapacitors, remote power transmission, instrumentation and propulsion compartment with control systems, and systems for receiving control commands and outputting information about the state of operation of the satellite to the ground station (not shown).
Balloon-space energy system works as follows.
After all diagnostics, pre-launch and guidance of the balloon 4 to receive laser radiation from the space stations 1, with a ground control station 2 is fed the signal to the main portion of space the plants 1 to start work in normal mode.
Next, the principle of operation is more convenient to split into two segments:
The space segment.
When space solar power plant 1 is located at the illuminated part of the orbit, the electric current generated by photoprobes what aalami, located in fotoizluchayuschih module charges the supercapacitor and, in parallel, is the power of the laser diode bars that are used to pump a fiber laser. Further along the optical fiber from each fotoizluchayuschih module radiation comes in a mirrored system, located on the head part of the solar cosmic power plant 1, which is summed up in a single laser beam, and thereafter, is transmitted to the panels 5, located on the upper surface of the balloon 4.
When space solar power plant 1 is located on the unlit side of the orbit, the electric current required to power the laser diode bars, produced from the supercapacitors.
To maintain a stable connection with the satellite 1 uses a laser 6 for guidance on space power plant 1 and the electric motor 9 that supports the balloon 4 in a static position and ensuring the slope of the balloon 4 in the direction of the satellite 1.
In the lit time of day located in the upper part of the balloon 4, the panels 5 are processed solar energy and laser radiation coming from space stations 1. Infrared panels 7, located on the lower part of the balloon 4, process heat coming from the Earth's surface. Next, the entire electric current flows through the ROS-cable 8 to the drive system 3, located on the Ground.
In a dark time of day located in the upper part of the balloon 4, the panels 5 are processed laser radiation coming from the comic of the power plant 1. The panels 7, located on the lower part of the balloon 7, process heat coming from the Earth's surface. Equipment located in the service module 10 provides diagnostics, transmission of signals from the balloon to the ground control station and provides the electric motors 9.
This ensures-hybrid solar space power.
Thus, the proposed design of the balloon and space energy systems by introducing an intermediate point of the energy acceptance of the above-mentioned construction, will significantly reduce the area of the surface segment of the energy system, significantly increasing the number of the received power (laser radiation from the space station, solar radiation and infrared radiation from the Earth). In addition, this energy system can be used not only on Earth, but also by development of other planets.
1. Balloon-space energy system that includes at least one space solar power and the ground station receive power and, transmitted with a space solar power station, characterized in that the system is equipped with an intermediate point of the energy representing the aircraft lighter than air as managed tethered balloon with mounted on it service module, while on the surface the specified device, facing away from the surface of the Earth are solar panels and laser focused on space solar power, and on the surface facing the surface of the Earth, are infrared panels and above the utility management module of the balloon, with the specified balloon attached above the zone of clouds through the cable-cable connected to the ground point of the energy.
2. Balloon-space energy system according to claim 1, characterized in that the aircraft is lighter than air performed-shaped, and on the perimeter of the lateral surface evenly mounted motors, United with the service module.
3. Balloon-space energy system according to claim 1, characterized in that between the service module and the ground point of the energy on the cable-the cable that goes from the service module, sequentially fixed obespechivaushyi balloon shell.
4. The balloon cosmic energy the system according to claim 1, characterized in that the space solar power stations are placed in orbit, the satellite comprising independent of each other photoperiodic modules focusing the ray mirror systems, supercapacitors, remote power transmission, instrumentation and propulsion compartment with control systems, and systems for receiving control commands and outputting information about the state of operation of the satellite to the ground station.
SUBSTANCE: invention relates to assembly and testing spaceship onboard systems, primarily, telecommunication spaceship power supplies. Proposed power supply comprises solar and storage batteries and stabilised voltage converter (SVC) for matching said batteries and stable supply of service components and useful load. Apart from assembly, proposed method comprises preparing power supplied for operation and testing the spaceship. Note here that cutoff SVC power circuits are short-circuited on solar cells side by low-power relay switchboards. Solar cells power circuits are connected to SVC after short-circuiting via appropriate low-power temporary circuits. After electric connection of solar cells to SVC bridging circuits are withdrawn. Electronic power switchboards are arranged at SVC input power circuits on storage battery connection side. After pre-charging by limited current of said circuits and charging storage cells the latter are connected to SVC. Circuits are charged to voltage equal to that of open circuit of appropriate storage battery. After connecting storage batteries to SVC, they are periodically charged by ground sources for compensation of leak currents at SVC switched-on state. Pre-charging on storage battery side is performed from appropriate storage batteries via current-limiting resistors of preset resistance.
EFFECT: higher reliability of manufacture.
4 cl, 1 dwg
SUBSTANCE: inventions relate to space power engineering and can be used for intensification of photosynthesis on the Earth. The system contains satellite (2) with at least two optical units. The first unit (3) is for sunlight collection and at all times is solar-oriented. The second optical unit (6) which is smaller and less inertial is for retransmission a light flux with higher energy density than the collected flux density to area (Z). Its orientation is remotely regulated from control centre (11). Between the optical units (3) and (6) there is facility (10) for light transmission from unit (3) to unit (6). The optical unit (6) retransmits light in certain frequency ranges only - about 450 nm and 660 nm. This is achieved by filtering the radiation flux for example by special treatment of devices (6), (10) surfaces and their manufacturing of certain materials.
EFFECT: possibility to illuminate with solar flux of high density and in required spectral range sufficiently large areas of celestial body (the Earth) to intensify photosynthesis on them.
6 cl, 2 dwg
SUBSTANCE: invention relates to aerospace engineering and may be used in producing telecommunication space apparatuses. Proposed method comprises producing component parts, assembling space apparatus, preparing electric power sources for operation, conducting electric tests of space apparatus for operation, mechanical strength, heat-and-vacuum endurance, and final tests including control over attachment of solar and storage batteries. Mechanical tests and control over said attachment are conducted using standard storage and solar batteries. Prior to mechanical testing, storage batteries are charged under conditions identical to standard conditions of prelaunch charging. All other tests are conducted using handling functional simulators of solar and storage batteries. Note here that solar battery simulators are connected directly to industrial power supply while storage batteries connections are implemented in two ways: directly in the case of charging interface and via guaranteed power supply system in the case of discharging interface. Standard storage batteries are stored as-charged with disconnected stabilised voltage converter.
EFFECT: higher operating performances and test reliability.
2 cl, 1 dwg
SUBSTANCE: invention relates to space exploration, particularly, to space transport systems Proposed method comprises trapping and accelerating space air and cargoes, transfer of accumulated cargoes to other spaceships, compensation of accumulating spaceship speed losses caused by atmospheric air and cargo trapping and acceleration, and drag. Spaceship power supply is ensured, partially or completely, by exploiting chemical, kinetic and thermal power of carried cargoes. Chemical power is provided in the case of transfer of oxidiser and fuel. Oxidation products are transferred to other spaceships for further use and/or processing. Kinetic power, as deceleration pulse, is provided in exchange of cargoes between accumulating spaceships in head flights or in delivery of cargoes by suborbital missiles. Thermal power is provided by decelerating cargoes entering accumulating spaceships and air, and from heat-accumulation substances transferred from other spaceships. For wasteless reuse in accumulating spaceship, interorbital power-carrier cargo transfer cycle system is organised to recover chemical and thermal power at satellite electric power stations located in higher orbits by means of interorbital tugs, carrier ships, tankers and other spaceships in higher orbits with which spaceship exchanges cargoes.
EFFECT: reduced weight and sizes of power plant.
SUBSTANCE: invention relates to spacecraft power supply. Proposed method comprises charging-discharging of storage batteries, their storage as-charged and voltage equalising. Temperature conditions of storage batteries are controlled by temperature gages, local heaters and radiators. Spaceship incorporates also onboard control unit with computer, stabilised voltage converter and storage battery control device. Said converter incorporates charge-discharge converters and analog transducers of charge-discharge current. Said transducers and gages effect data exchange via storage battery control device with said stabilised voltage converter, thermal control system and computer. The latter incorporates software to correct operation of said converters, local heaters and equalising circuits.
EFFECT: higher efficiency, improved operating performances.
4 cl, 2 dwg
SUBSTANCE: invention relates to electric power supply systems of spacecraft. Proposed system comprises storage battery and solar battery electrically interconnected via micromechanical interlocking modules. Each said module comprises substrate with input and output buses with terminal groups. Switch made up of moving thermo mechanical actuators interacts with said terminal groups. Said actuators are made up of two or more layers that feature different thermal expansion factors. One of the layers may be made with reversible thermo mechanical shape memory. When irradiated by the Sun, solar batteries generate electric power to heat interlocking module actuators arranged on the batteries. Said actuators, when heated, get deformed to close contacts of input and output buses. This allows charging the storage battery and supplying current to other loads. With solar batteries shaded, actuators get cooled down to open contacts of said buses and rule out the storage battery discharge that causes, in particular, heating of breakdown of solar battery photo converter.
EFFECT: reduced weight and sizes, higher reliability and longer life.
2 cl, 6 dwg
SUBSTANCE: invention relates to power supply of spacecraft, particularly, to that of mars rover. Proposed system comprises solar batteries, storage batteries, distributor, and elements with triboelectric surfaces. Said elements are, preferably, mounted on the base adjoining mars rover body to turn thereabout. In compliance with preferable version, elements with triboelectric surfaces and solar batteries open and operate in turns, the former in dust storm and the latter in no dust storm conditions.
EFFECT: continuous power supply of mars rover.
3 cl, 4 dwg
SUBSTANCE: invention relates to spacecraft power supply. Proposed method involves replenishing spacecraft power supply from external sources. One or several spacecraft-mounted electric power stations are located on working orbits in spacecraft line of sight. Spacecraft location is determined to cut on spacecraft tracking system and electromagnetic power is transmitted to spacecraft onboard receiver. Transmission can be performed in the range of laser to microwave radio radiation, or in the form of high-power electron beams. Spacecraft power supply system in normal state, supply of electromagnetic power from spacecraft-mounted electric power station is terminated and it is moved to standby orbit. Proposed system comprises device to transmit electric power arranged on spacecraft-mounted electric power station platform driven by rocket engine. Said platform carries also laser range finder optically connected with one or several angular reflectors arranged on spacecraft. Said reflectors are used to align spacecraft-mounted electric power station conducting channels with spacecraft electric power receiving channels.
EFFECT: reliable power supply, longer active life of spacecraft.
5 cl, 2 dwg
SUBSTANCE: invention relates to spacecraft electric power-saving systems. Proposed system comprises solar and storage battery, as well as automatic control, test and storage battery equalising units. ACS allows simultaneous operation of said batteries for supply of onboard circuitry. Test and storage battery equalising unit effects element-by-element control of voltages and temperature in storage battery and leveling storage battery voltage misbalance. Said leveling is performed by charging separate storage batteries by preset algorithm by onboard computer or microprocessor incorporated with this unit. Structurally, the latter unit can be incorporated with both storage battery and automatic control unit. Charging voltage source can be incorporated with one of aforesaid units.
EFFECT: higher efficiency and longer life of storage batteries.
10 cl, 2 dwg
SUBSTANCE: invention relates to power supply systems of space objects, particularly incorporated with artificial Earth satellites (AES). Method consists in cycling accompanied by control over power characteristics of storage batteries (SA) connected in series in storage battery module. Tests are performed at operated AES. SA module A number is restricted by available excess power in AES power supply system. SA charge and discharge is controlled by onboard computer. SA discharge is performed by stabilised current and SA thermal state is continuously regulated in tests. Proposed method exploits device comprising solar batteries (SB) connected to load via voltage converter and storage batteries. The latter are connected to solar batteries via charge converters and, via discharge converters, to load. Load comprises onboard computer, telemetry hardware and command-and-measure radio line. Said module comprises thermal control plate with SA mounted therein, separate charge and discharge converters connected to the load of independent power supply system and onboard computer. Note here that individual discharge converter represents a current stabiliser. Thermal control plate is provided with temperature transducers and heaters while module incorporates discharge resistance. Note that said transducers and heaters are connected with onboard computer. Individual discharge converter output is additionally connected via switch with discharge resistance.
EFFECT: higher efficiency and validity.
2 cl, 1 dwg
SUBSTANCE: invention relates to method and device for transfer of long-length bulky cargoes using lifting body on guide cables. Cargo (windmill blade) carried by balloon on guide cables is tightened by bearing cable at its center of gravity in rotating-tipping front-end tool. Said cargo is carried by several mobile controlled winch by means of transfer windlass cable secured at front-end tool. Crane windless cables are lifted by lifting cables to crane assembly and locked thereat by remote control means. In crane mode, crane windless cables are unlocked to be lowered from crane assembly to controlled winches and connected therewith. By varying free length of separate crane windless cables, cargo is set to required position. Crane assembly represents spatial structure in diameter increasing relative to vertical axis toward center from both ends to maximum. Crane bottom section has several cane windless cable guide rollers while top section has guide rollers for lifting cables of transfer safety ring.
EFFECT: transfer over great distances in highlands and other sever conditions.
10 cl, 8 dwg
SUBSTANCE: invention relates to development of tethered balloons. Proposed complex comprises balloon gas bag, tether, coupler secured to gas bag whereto attached via top support element are gimbal joint with two degrees of freedom and bottom support element to carry payload, surface control station and communication means to transmit control commands. Payload is arranged for azimuth rotation about bottom support element vertical axis, driven by electric motor controlled by electronic control unit incorporating speed and acceleration transducers. Top support element is furnished with knock-down lock whereto attached is rotary fastener rigidly secure to horizontal top disc. Gimbal joint upper fork is jointed to upper disc bottom surface and accommodates gimbal joint ring fitted on joint first pin. Gimbal joint bar is arranged inside joint ring on joint second pin arranged perpendicular to aforesaid first pin. Gimbal joint bar lower end is jointed to bottom support element. Top ends of two extra dampers are secured to one vertical element of joint fork on the side of two opposite side surfaces. Bottom ends of said dampers are attached to damper bracket arranged on bottom support element so that dampers in initial position are located vertically and in parallel.
EFFECT: stable images, higher accuracy of observation camera alignment, simplified design.
10 cl, 2 dwg
SUBSTANCE: invention relates to lifting devices for transportation of long and bulky cargoes, in particular, windmill blades. Device with lifting body on guide cable ropes comprises rotary tilting gripper 12 connected with mobile controlled winch by pull cable rope and with lifting body by bearing cable rope so that bulky cargo tightened at the center of gravity in gripper in transportation may spontaneously rotate in wind and retain horizontal position. Proposed method is characterised by using above described device.
EFFECT: transportation of bulky long cargoes.
19 cl, 7 dwg
SUBSTANCE: invention relates to aeronautics. Proposed method comprises using ground vehicle in carrying cargo and, in carrying counter cargo, using rope and aerostat. Note here that second rope, ground vehicle with winch for rope and aerostat with suspended pulley block are used. Winch rope is secured to aerostat, while second rope is secured to ground vehicle and, via aerostat pulley block, to counter cargo so that, with vehicle moving on slope, winch is unwound to keep aerostat at one altitude.
EFFECT: higher efficiency of overcoming sand runs.
FIELD: aircraft engineering.
SUBSTANCE: invention relates to lighter-than-air airships. Proposed kytoon comprises balloon, anchor rope, ground support equipment and pay load. Anchor rope represents rope-hose with one or several gas spaces to feed gas to fill balloon and that for electric generator that supplies onboard equipment, payload and motors. The latter are used to oppose wind force and hold kytoon at preset operating point.
EFFECT: increased time of continuous operation at larger altitudes.
SUBSTANCE: balloon has an envelope filled with a gas lighter than air and/or with a hot air, a rigid carcass carrying the said envelope, a nacelle, slings to suspend the nacelle and anchor cables. The nacelle is tightly coupled with the envelope and features a funnel-like widening at its top and a central channel along its lengthwise axis to limit air intake into the envelope. The balloon envelope can be made from conducting material to make an electrode in a storage battery intended for utilisation of atmospheric electricity, or can be used as an antenna, or can house a particular antenna for communication purposes.
EFFECT: expanded potentialities.
2 cl, 4 dwg
SUBSTANCE: method comprises producing elevating force for an aircraft, climbing the platform for wireless net for transmitting information up to a given level, and locking the aircraft and platform at a given point of the surface by means of a flexible link. The flexible link is made of a flexible torsion that is set on the cylindrical shell and has a length no less than the given height of the platform. The device comprises hollow housing provided with two mutually perpendicular openings and closer of the circuit of transmitting torque mounted in the space of the housing for permitting axial movement and rotation around the vertical line. The flexible link is made of a flexible torsion that is set in the cylindrical shell. The top end of the torsion is secure to the pin of the thrust propeller, and the bottom end is provided with the clutch member having gearing member connected with the source of torque. The flexible link passes through the mutually perpendicular openings in the housing. The closure of the circuit has outer teeth of spline transmission for engaging the source of torque provided with teeth of the conical transmission.
EFFECT: enhanced reliability.
3 cl, 2 dwg
FIELD: means for support of navigation of air platforms used for forming wireless information transmission systems within line-of-sight range in preset geographic region.
SUBSTANCE: proposed method includes creation of lifting force of flying vehicle for keeping the platform at preset altitude and holding the flying vehicle and air platform in preset point of surface with the aid of flexible rod which is used as channel for feeding the supply energy for forming the thrust vector of flying vehicle lifting force. According to invention, gaseous medium is used as energy carrier for forming the supply energy. Working medium is charged under pressure to energy supply channel of flexible rod and at outlet of this channel energy of gaseous working medium is converted into energy creating the lifting force of flying vehicle. For creating the lifting force, energy of gaseous working medium in form of combustible or natural gas may be converted into electric power or reactive thrust at output of energy supply channel. According to first version, instrument bay of air platform is provided with at least one fuel element for conversion of combustible or natural gas energy into electrical energy and flexible rod is provided with hollow channel whose lower end is brought into communication with combustible or natural gas source; upper end of flexible rod is provided with at least one fuel element whose electrical output is connected with input of electric motor of tractor propeller. According to second version, flexible rod is provided with hollow channel whose lower end is brought into communication with combustible or natural gas source or compressed air source and upper end is connected with rotating engine of tractor propeller made in form of jet engine or in form of ramjet engine provided with ignition element for ignition of combustible or natural gas or in form of converter for conversion of compressed air pressure into rotary motion of tractor propeller.
EFFECT: enhanced reliability of navigation of air platforms due to enhanced lightning protection and climatic stability of power supply to tractor propeller engine and air platform instruments.
7 cl, 2 dwg
SUBSTANCE: proposed captive lifting device has three captive cables; first end section of each cable is secured to aerostat envelope and second end is connected with ground winch mechanism. Inclined bearing surfaces of device are located radially relative to aerostat pad center; they are inclined in direction from center of this pad outside. Each bearing surface is provided with carriage mechanism including the carriage and pressure roller located above carriage. Second end section of each captive cable is passed between pressure roller and carriage and is rigidly secured in upper part of inclined bearing surface. Each carriage is engageable with flexible transfer device which is used for control of motion of carriage over inclined bearing surface; this device includes drive pulley, driven pulley secured in upper part of inclined bearing surface and run of transmission which are oriented along inclined bearing surface.
EFFECT: increased service life of aerostat; enhanced stability of aerostat.
2 cl, 1 dwg
SUBSTANCE: proposed captive balloon has envelope made from gas-tight material and captive cables. Captive balloon is additionally provided with aerodynamic stabilization unit made in form of feathering unit secured on rod passing through upper pole of balloon envelope by means of lines; feathering unit is provided with keel; feathering unit is made in form of three-dimensional streamlined body inflated by air flow; when it is filled with air, it has shape of aerodynamic wing in plane of longitudinal section. Three-dimensional body is formed by upper and lower gores stretched on framework; edges of these gores are fastened over their perimeter forming air intake slotted opening and inner cavity filled with air flow. In zone of intake hole, upper gore has sizes exceeding sizes of lower gore, so that when three-dimensional body is filled with air, upper gore overhangs above lower gore.
EFFECT: simplified construction of balloon stable to wind load.
3 cl, 4 dwg
FIELD: transportation power systems.
SUBSTANCE: proposed system includes transport facilities, captive balloon, captive cable used for holding and guiding the transport facilities and wind-power electric stations mounted on captive balloon and used for motion of transport facilities. Captive cable is provided with two (or more) current conductors fastened with insulating layers made from high-strength material. Each current conductor is located in vertical longitudinal plane and is fastened to ends of captive cable through insulating layers and is connected with respective wind-power electric station. Outer surfaces of current conductors located in vertical longitudinal planes are provided with current-conducting wear-resistance coats.
EFFECT: enhanced efficiency and reliability of system in upper layers of troposphere.
2 cl, 2 dwg