FIELD: aircraft engineering.
SUBSTANCE: proposed aircraft comprises lifting air-bag and bearing air-bag and power plant with heater. Lifting air-bag is filled with working fluid of power plant arranged in its nacelle and including compressor, heater, turbine, power load and working fluid lines connected with lifting air-bag. Bearing air-bag is composed of sections and incorporates volume variator.
EFFECT: higher power-to-weight ratio.
9 cl, 1 dwg, 1 tbl
The invention relates to managed aerostatic aircraft, in particular to the airships, mainly to airships equipped with Autonomous systems and facilities energy use as fuels and renewable sources of energy, such as Solar energy.
Famous airships with power plants that convert primary energy into mechanical energy propulsion or electricity. Apply various plant that converts thermal (solar or nuclear) energy into electrical energy. Significant capabilities have nuclear energy sources, which are beneficial to use for a constant load, while managed aerostatic aircraft required load, variable stages of flight and objectives. In addition to the freight task, especially in areas remote from highways, such devices in the main areas of application include: patrol, special control lines and pipelines, photo and video, rescue operations, and luxury tourism. As seen from the transfer characteristics of power generating systems for airships, there is the problem of usage and energy consumption and to change the carrying capacity of the airships when exp is watachi. Thus, the challenge is to build power plants and systems capable of aerostatic aircraft drive propulsion, different types of electrical energy and load bearing lifting force required by the terms of the uneven consumption mode.
The energy potential of nuclear and renewable energy will solve geopolitical problems associated with uneven placement of natural fossil fuels, and also will lead a significant restoration of natural ecological potential and improvement of the environment that attracts these resources and managed aerostatic aircraft.
In particular, the proposed airship, comprising a casing, an air chamber, an Autonomous energy system for electricity generation, heating and air air chamber and molten-salt nuclear reactor with the three-loop heat removal system, consisting of hardware circuit molten fuel salt composition, circuit intermediate melt salt coolant and circulation flow of gaseous coolant. On the second version of the airship includes an additional heat exchanger molten fuel salt composition is melt intermediate salt coolant. Potratem option airship includes additional air chamber in the heat-insulated housing. On the fourth draft of the airship includes an additional heat exchanger and the air chamber in the heat-insulated housing (RF patent for the invention №2408496, publication date 2000.12.20). The disadvantage of this solution is the high cost and low efficiency of energy supply to the airship, which is associated with large costs for the establishment and operation of a multi-circuit system of heat removal from the molten-salt reactor (up to 1500 dollars. USA/kW).
Similar to the proposed technical solution is also a high-altitude airship proposed in the patent for invention №2376687 (publication date: 20.12.2009), which uses regenerative power plant, designed to move the airship in the environment, comprising a solar battery, an electric drive screw with a control unit, electrically connected to the solar battery cells electrically connected by electric lines with a solar battery, the electrochemical generator, electrically connected by electric lines to the control unit of the electric screw drive, power storage and supply of hydrogen and oxygen, is pneumatically connected to the electrochemical generator and the electrolyzer, the power storage and supply of water that is hydraulically connected with electrochemical generator and an electrolyzer, a pump, characterized in that it introduced the Kama is and mixing, the combustion chamber, turbine, shaft with the compressor and generator, regenerative heat exchanger and the heat exchanger-separator, which features a water level sensor connected to the control channels to pump out oxygen from the electrochemical generator connected to the first input in the mixing chamber, a second inlet into the mixing chamber is connected to the first output of the regenerative heat exchanger, the outlet of the mixing chamber connected to the first input in the combustion chamber, a second inlet in the combustion chamber is connected with the release of hydrogen from the electrochemical generator, the output of the combustion chamber is connected to the turbine inlet, the outlet from the turbine is connected to the first input of the regenerative heat exchanger, a second entrance to the regenerative heat exchanger connected to the air outlet of the compressor, the second output of the regenerative heat exchanger is connected to the gas inlet of the heat exchanger-air dryer, the air outlet of the heat exchanger of the air dryer is connected to the air inlet to the compressor, the water outlet of the heat exchanger of the air dryer is connected through a pump with a power storage and supply of water, and the output of the generator is electrically connected by electric lines to the control unit of the electric screw drive. The disadvantages of this solution is the low efficiency and high cost of installation.
More for e is e the solution proposed in the patent of the Russian Federation for invention №2390466 (publication date 27.05.2010), the prototype, in which the aerostatic aircraft includes a housing shell for carrier gas and power plant, made in the form of the nuclear reactor. The apparatus has a cooling system of the reactor core and the temperature-controlled carrier gas. The cooling system of the reactor core comprises a heat exchanger, a first cooling circuit with a circulating pump and a second cooling circuit, designed to pick up heat from the coolant of the first contour and provided with a circulating pump. The temperature regulation system carrier gas in the form of highways, equipped with a circulation pump connected to the shell of the carrier gas and passing through the heat exchanger. The disadvantages of this solution are relatively low efficiency associated with the need to transfer thermal energy using the fuel solution, the high cost and the need for additional energy source for the needs of the payload airship.
The objective of the invention is to increase the capacity of the apparatus, the distance and cruising altitude, its total installed power, environmental, security apparatus, the land use for power supply reliability, reduce the cost of delivering payload, opportunities for the use of renewable natural energy sources.
The problem is solved in that
in aerostatic aircraft, containing the lifting ballonet and the power plant, including the heater, aerostatic aircraft is equipped with a bearing ballonets, lifting ballonet filled with the working fluid power plant, located in energokontrole, including the compressor, heater, turbine, power loading, highways working body connected with lifting ballonets;
- bearing ballonet partitioned and provided with means for changing its volume;
- the heater is selected nuclear reactor or heat the battery;
as the working fluid is selected the air, or helium, or a mixture of helium and hydrogen;
- lifting ballonet provided with means changes its volume and heat exchanger, cooled by the external air;
as the power load connected to the turbine, the selected generator or propulsion;
the path formed by the compressor, heater and turbine, equipped with adjustable bypass circuit;
- compressor mechanically coupled to the turbine.
In the drawing given a diagram of the apparatus, where 1 - bearing ballonet, 2 - lifting ballonet, 3 - loop working fluid, 4 - energihandel, 5 - compressor, 6 - heater, 7 - turbine, 8 - power load, 9 - bypass path 10 to the supply pipeline RA is Otsego body.
Aerostatic aircraft (Zeppelin) contains bearing ballonet 1, which is connected with the lifting ballonets 2 containing gaseous working fluid whose flow 3 is withdrawn from the winding ballonet 2 energogolodu 4, in which the flow path of the working fluid 3 is directed into the compressor 5, and then compressed heated in the heater 6 and flows into the turbine 7, which serves to drive a compressor, and power load 8. After tripping the turbine 7 enthalpy obtained in the heater 6, the flow of the working fluid is returned to the pipeline for supplying the working fluid 10 in lifting ballonet 2. Part of the working fluid flow after the turbine flows into the bypass path 9, which is closed at the entrance to the compressor 5.
Depending on the selected working fluid (air or helium or a mixture of helium and hydrogen) the inlet pressure of the working fluid in energogolodu 4 is chosen close to atmospheric, and the density of the working fluid in the compressor 5 may range from 0.1 kg/m3(a mixture of helium and hydrogen) to 0.8 (heated air), which can cause differences in the design of ballonets 1 and 2 of the apparatus and its energokontrole 4. In particular, for the working fluid of higher density can be increased bearing ballonet 1, to provide basic lift apparatus. The heater 6 can be selected samples of different objects of the second reactor or heat accumulator, charge, for example, solar panels on the hull of ballonets 1 and 2 or sbresny warm various devices on Board of the machine to which the heater may also be provided with a host of regenerative heat exchange (not shown). For the selection of the working fluid from the lifting of ballonet 2, for example in the embodiment of it in the form of a double-walled cavity, it can be put underwater and idler bellows tube. Double-walled cavity lifting ballonet 2 can also be partitioned and equipped with volume changes, made in the form of bellows, provided with, for example, mechanical, pneumatic or hydraulic actuator, and a heat exchanger, cooled by the external air, which will accelerate the change of speed of lowering of the apparatus, and reduce the work of compression of the working fluid in the compressor 5 in the mode of removal of the accumulated energy in the heater 6, for example in the embodiment of it in the form of heat the battery, or when the cooldown nuclear reactor that is used as a heater 6.
In turn, the bypass circuit 9 allows you to change the load of the heater 6 and the turbine 7 without changing the flow rate and temperature of the working fluid supplied to the lifting ballonet 2 through a pipeline for supplying the working fluid 10. This solution will allow to change the speed of ascent apt the rata and the power of the power load 8.
To reduce the temperature of the working fluid and/or condensation of the pipeline supplying the working fluid 10 can be connected with the cooling side of the battery is cold (not shown), the cold accumulation which may be due to the low ambient temperatures or refrigeration machines compression or absorption type (not shown). Rationally accumulating cold in the form of binary ice mixtures, so-called "liquid ice" (a mixture of water, alcohol and inhibiting corrosion additives).
In addition, the entrance to the turbine 7 and the compressor outlet 5 are provided with adjustable valves.
Taking into account the possible irregularity of the supply of thermal energy, such as using renewable sources such as solar energy, the heater 6 can be connected to additional heat accumulator, which in turn rationally be performed in a sealed insulated container filled heat storage substance: liquid, for example water or oil, or solids, such as salts and oxides of alkaline and alkaline-earth metals, and minerals with a high heat capacity.
Does this aerostatic aircraft (Zeppelin) as follows on the three main modes: climb, cruise and descent. When the apparatus on earth is, during land preparation, make the filling ballonet 1 and 2 gas environment, in particular feeding in lifting ballonet 2 working medium, for example a mixture of helium and hydrogen stored in the battery of the working fluid, for example, in the isothermal model capacity at a temperature of -35°C and a pressure of 12 MPa, the supply lead up to the ambient temperature in the fuel line supplying the working fluid 10 with pre-throttling the working fluid to ambient pressure. Before lifting the flow of the working body 3 serves to the input of the compressor 5, which is compressed, for example, to a pressure of 0.35 MPa, and then the heater 6, in which at a temperature of, for example, up to 300°C is heated, for example, due to the accumulated thermal energy.
In the mode of lifting the heated flow of the working fluid 3 is supplied from the heater 6 to the input of the turbine 7, where the working fluid expands to a pressure of 0.1 MPa and a temperature of 70°C, and then served in the artery supplying the working fluid 10. The heated working fluid of low density fills lifting ballonet 2, which together with the bearing ballonet 1 allows to ensure the ascent of the airship to cruising altitude, where the device goes into cruise mode in which the energy of the heater 6, creatively working fluid in the turbine 7, which is used mainly to drive power-load 8 spent on overcoming aerodynamic resisting film to prevent the effect of air (drive propulsion, for example, a screw) and ensuring the needs of staff and its payload. As the power load 8 can be used an electric generator, a propeller apparatus, the flywheel.
Changing the temperature of the working fluid, adjust the lifting force generated by the lifting ballonets 2, thereby controlling the position of the unit at a height that allows a wide range to change cruising modes and without ballast.
When the shutter device is activated bypass circuit and the bypass flow 9 returns the flow of the working fluid at the inlet to the compressor, bypassing the supply of the working fluid 10.
In this mode may be used as the cooling of the working fluid surrounding the apparatus by air lifting ballonet 2, for example, blowing air between the walls of the casing and the mechanism to reduce the amount of lifting ballonet 2, wherein the mechanical actuator compresses the shell lifting ballonet 2, which allows for reducing the volume of the working fluid to reduce and lift force, aided by a simultaneous increase in the pressure of the working fluid and its density.
Tactical-technical characteristics of the device can be estimated based on the following indicators shown in the Table.
|The volume of the shell||10000 m3|
|Structural mass of the airship||6500 kg|
|Payload mass||3000 kg|
|The maximum allowable takeoff weight||9700 kg|
|Maximum dynamic lift force||1000 kg|
|The minimum speed control||0 km/h|
|Cruising speed||0...100 km/h|
|Maximum speed||130 km/h|
|Power of main engine||2×350 kW|
|- cruising speed of 70 km/h||24 hours|
|- maximum speed||5 h|
|Ferry Yes inost flight||up to 6000 km|
|Practical ceiling||3000 m|
|Operating altitude||up to 1500 m|
|The starting team||6-8 people.|
Proposed aerostatic aircraft (Zeppelin) compared with the prototype has the following advantages:
- increases the power of the apparatus, the range and cruising altitude, its total energy supply, as the device does not require energy input in peak mode from the external energy source adopted in the prototype solution;
- increases reliability and reduces the cost of delivering payload and perform flight tasks due to a sharp (by several orders of magnitude) reduction of volume of the working fluid outside the membrane ballonet;
- provides full environmental security apparatus, since the working fluid is not released into the environment;
- using heat accumulators installation is stored for any desired amount of energy sufficient to ensure stable and uninterrupted work apt the rata, even in periods of interruption in supply of heat energy from a renewable source;
- provides the opportunity to use this device to generate electricity and supply of various objects thermal energy in the mode razoblachennogo graphics consumption in areas based system;
- technically simple and reliable provided the ability to change energy production regardless of the mode of motion of the system;
- ensured effective utilization of waste heat from various heat engines, as well as expands the possibility of using renewable natural energy sources, with significant resource potential and at the same time, the high irregularity of receipt of their energy, as well as further improve the efficiency of the installation in cold climatic periods;
- increases reliability and reduces the manufacturing cost of the apparatus due to the moderate temperature and pressure parameters of the working fluid.
An additional positive feature of this apparatus is the possibility of using already existing materials, technical solutions and equipment necessary for its creation.
1. Aerostatic aircraft, containing the lifting ballonet and power installation, comprising a heater, wherein the aerostatic aircraft equipped with bearing what allonym, lifting ballonet filled with the working fluid power plant, located in energokontrole, including the compressor, heater, turbine, power loading, highways working body connected with lifting ballonets.
2. The apparatus according to claim 1, characterized in that the bearing ballonet partitioned and provided with means for changing its size.
3. The apparatus according to claim 1 or 2, characterized in that the heater is selected nuclear reactor.
4. The apparatus according to claim 1 or 2, characterized in that the heater is selected heat accumulator.
5. The apparatus according to claim 1 or 2, characterized in that the working medium is selected, the air, or helium, or a mixture of helium and hydrogen.
6. The apparatus according to claim 1 or 2, characterized in that the lifting ballonet provided with means changes its volume and heat exchanger, cooled by air.
7. The apparatus according to claim 1 or 2, characterized in that as the power load connected to the turbine, the selected generator or propulsion.
8. The apparatus according to claim 1 or 2, characterized in that the contour formed by the compressor, heater and turbine, equipped with adjustable bypass circuit.
9. The apparatus according to claim 1 or 2, characterized in that the compressor is mechanically coupled to the turbine.
FIELD: power industry.
SUBSTANCE: invention relates to wind industry and can be used in heating and hot water supply systems of residential and industrial buildings. Friction heat generator comprises vertical cylindrical body with lid and bottom, drive shaft, cold water inlet manifolds and hot water outlet manifolds, movable disc at the bottom with blades and stationary disc. Pipe rigidly put on the shaft has rocker arms on the top attached to it from both sides, and cantilever beams at the bottom, supported by disc. Disks are attached at the bottom on both sides of cantilever beams, vertical rods attached to them come out from their centre. These rods have discs with blades and discs with hollow rings around them, which are put loosely on them. Rods are fixed at the top in the sleeves attached to the rocker arms.
EFFECT: performance permits to increase the conversion factor of one form of energy into another, compared with similar heat generators.
2 cl, 3 dwg
SUBSTANCE: invention relates to heating equipment, particularly, to water heater incorporated with heating system and hot water supply. Windmill heat generator comprises cylindrical housing with cover and bottom and cylindrical horizontal partition accommodating thrust bearing and journal-and-thrust bearing. Vertical shaft runs in said bearings and is equipped with coupling fitted from above to receive power from windmill, rotary vane element being secured thereto from below. Cold water inlet pipe is fitted inside the housing, at its bottom, while hot water discharge pipe is arranged at its top section connected with cold and hot water supplies, respectively.
EFFECT: enhanced performances, heating of two and mote premises.
FIELD: power industry.
SUBSTANCE: wind friction heat generator comprises cylindrical housing with lid and bottom, drive shaft and fittings of cold water inlet and hot water outlet at the top right side of the housing. Drive shaft under the lid has a flange rigidly connected in the bottom with flange of screw, and from sides with plate, having openings for connection of peripheral screws to it. The centre screw at the bottom has opening in which the axle rigidly connected with movable disc attached on the bottom, is installed on the sliding key. Peripheral screws at the top are freely located with clearance of 1.5-2.0 mm in the openings of plate and at the bottom have discs attached to them, contacting with annular disc attached to the bottom. All screws at the bottom are combined by hollow ring filled with heat accumulating material of phase transition, and their surface has the raised roughness.
EFFECT: improvement of efficiency of liquid heating.
SUBSTANCE: invention relates to power engineering and can be used for heating water in housing and utilities sector and in agriculture. Essence of the invention consists in the fact that the acceleration bush of a heat generator is made as a set of concentrically embedded fixed bushes with radial gaps, the bush is installed in a water heating device comprising an operating network pump, feeding and return pipelines with shutoff valves providing for interaction of the heat exchanger with the heat generator which includes at least one casing fitted by a cylindrical part made as a vortex tube with a braking unit being set at the base of the casing and its other side being connected to the end face side of a fluid accelerator which is made as a volute connected to the pump and fitted by the acceleration bush set coaxially to the vortex tube axis line and connected to the discharge tube of the pump by a channel.
EFFECT: device arrangement will make it possible to increase fluid heating efficiency and reach stable performance.
12 cl, 8 dwg
FIELD: machine building.
SUBSTANCE: invention relates to the method of a hybrid unit control and to the hybrid unit in which this method can be implemented. Control method for a unit 1 comprising at least a compressor plant 2 and/or a drying unit on one side and a heat regeneration system 3 on the other side. The heat regeneration system 3 absorbs heat from the compressor plant 2. Additionally the hybrid unit 1 comprises a controller 5 and a device 6 to set one or more system parameters. The controller 5 performs control both of the compressor plant 2 and/or the drying unit and the heat regeneration system 3 on the basis of the said system parameters along with the optimisation of the overall efficiency of the hybrid unit.
EFFECT: reduction of total power consumption by the hybrid unit.
3 cl, 1 dwg
SUBSTANCE: invention is referred to the field of electric engineering and operation of systems with asynchronous electric motor and frequency control, in particular to control of rotation speed and prevention of critical operation modes. Technical result of the method lies in that reliability of the cavitator is improved; its stable operation is maintained by means of operation mode correction when the detected sign proves potential stalling with change in the electric motor rotation speed. The method for control of stability improvement in cavitator operation includes liquid passing in a gap between the rotor and stator and subsequent conversion of the received energy into thermal energy, control by the heating process. The claimed method for control of the cavitator operation modes is based on the analysis of higher harmonics ratio in the electric mains, its comparing with the threshold value and shaping of the control signal for frequency control unit which controls the rotation speed of the electric motor.
EFFECT: control method allows reaching maximum efficiency for activation of process liquids for the purpose of their use in different processes of chemical production such as dilution, heat generation, and synthesis.
FIELD: power engineering.
SUBSTANCE: thermoelectric link comprises a coolant pipe, coated with a layer of a dielectric material with high heat conductivity, made of separate circular toothed ribs with teeth that are tightly pressed to each other, inside of each one there are circular zigzag-shaped rows of thermoelectric sections, made of alternating and joined thermoemission converters, each comprising a pair of sections made of different metals M1 and M2, ends of which are flattened and tightly pressed to each other and arranged in zones of heating and cooling, near the edge of the rib tooth and the external surface of the coolant pipe, accordingly, besides, free ends of zigzag-shaped circular rows of each thermoelectric section are connected to each other by links, and free ends of circular rows of extreme thermoelectric sections, in their turn, are connected by electric wires with collectors and current leads.
EFFECT: increased reliability and efficiency of a thermoelectric link for a pipe.
SUBSTANCE: method comprises the following steps: (a) mixing a first substance which includes an oil-bearing rock and a second substance which includes sensitive particles in form of dipole antennae to form a mixture of 10-99 vol. % of the first substance and 1-50 vol. % of the second substance; (b) exposing said mixture to radio frequency energy with frequency or frequencies from said set of one or more radio frequencies and power sufficient for heating the sensitive particles; and (c) continuing exposure to radio frequency energy over a period of time sufficient for heating sensitive particles of said mixture to average temperature higher than about 100°C (212°F). The method is characterised by that said sensitive particles are conducting carbon fibres with length between 1/2, 1/4, 1/8 and 1/16 the wavelength.
EFFECT: said sensitive particles can have advantages for radio frequency heating of hydrocarbon compounds, for example high temperature, anhydrous treatment as well as higher rate or efficiency.
14 cl, 3 ex, 1 dwg
SUBSTANCE: liquid heating apparatus comprises a heat generator comprising a housing having a cylindrical portion and a liquid movement accelerator, designed as a cyclone, a pump connected to the heat source via an injection nozzle, where at least one insert is placed, and a heat exchange system. The insert is formed as a continuous plate along the injection nozzle oriented perpendicular to the ends of the cyclone. The insert in the injection nozzle forcibly expands the jet in its entry into the cyclone, which results in formation of a vacuum region, downstream the compression region, the vacuum again, compression, etc. As we move into the cyclone, collapse and cavitation are formed in turns on each element of the jet flow in these regions, providing hot water or other process fluid.
EFFECT: invention makes it possible to improve heating efficiency and reliability of a fluid device.
10 cl, 5 dwg
FIELD: engines and pumps.
SUBSTANCE: electrically driven pump-heat generator comprises encased scroll, impeller, discharge outlet, stator and drive motor hollow rotor running in plain bearings. Heat tube is made inside said hollow rotor. Hydrodynamic rotary cavitator fitted on the shaft incorporates ultrasound resonance cavitation amplifier. Coaxial heat tubes are fitted on hollow shaft between said stator and rotor.
EFFECT: higher efficiency, decreased electric power consumption.
2 cl, 1 dwg
SUBSTANCE: invention relates to aircraft engineering and may be used in designing local airline aircraft of 18-24 seating capacity. Aircraft comprises fuselage, wing, empennage, power plant composed of two engines, and propeller. Engine are arranged inside fuselage tail and integrated by main gearbox to transmit torque via transmission and angle gearbox to coaxial multiblade propeller. Said propeller is arranged at cruciform fin of empennage behind sealed bottom of passenger compartment, above fuselage top surface. Center-section of trapezoidal low wing is located under passenger compartment floor without increasing fuselage mid section.
EFFECT: higher safety, reduced in noise in passenger compartment.
3 cl, 9 dwg
SUBSTANCE: system of tail fin (1) for aircraft includes fuselage (3), wing (2) and traction engine (5, 5a, 5b) mounted in fuselage aft portion of this aircraft which is located behind the wing (2) relative to longitudinal axis of aircraft. System of tail fin contains air foils fixed on fuselage aft portion. System of tail fin is formed by horizontal air foils (41a, 41b, 43) and vertical air foils (42a, 42b) made to form ring structure containing ring fixed on fuselage. Traction engine is held in the ring formed by system of tail fin. Central vertical stabiliser is used to form two rings in the ring structure. Versions of aircraft are characterised by tail fin features and mounting of one or two engines in the ring zone.
EFFECT: higher safety of operation.
13 cl, 4 dwg
SUBSTANCE: invention relates to aircraft engineering. Proposed flight vehicle comprises power plant, fuselage and wing fragments. Set of wing fragments comprises bearing and control surfaces and their mounts. Wing fragment includes structural set including spar, stringer and ribs. Fuselage includes set of frames, spars, stringers and skin. Frames and spars have opening to fasten wing fragments. Engine reversing device comprises flap pivoted in housing to close its openings and provided with grids composed of gas flow guide vanes. Air intake with jet engine integrated in fuselage tail features variable-depth grooves arranged opposite each other on supports. Control system comprises control rod with pedals at its bottom and handle at its top. Said handle has landing gear extension/retraction knob and that of electric drive of bottom set of fragments. Methods of flight vehicle control comprise exploiting air and gas flows.
EFFECT: simplified servicing.
47 cl, 30 dwg
SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft power plant and aircraft proper. Aircraft power plant comprises propulsor 1 to create forward thrust exploiting flight energy transferred therein first power converter 4 to provided propulsor 1 with first flight energy derived from first second fuel. First converter 4 makes an engine running on various fuels while first fuel differs from first one. Besides, power plant incorporates control device to control first and second fuels feed into first converter 4, first tank 6 to supply first fuel to first converter 4 and second tank 11 to supply second fuel to first converter 4.
EFFECT: decreased emission of pollutants.
17 cl, 6 dwg
SUBSTANCE: invention relates to aircraft engineering. Proposed device comprises first onboard generators of power to be accumulated, second onboard accumulators of power produced by first generators, and third onboard means to generate aerodynamic forces by power accumulated in second means. Said first onboard means comprises screw to be rotated by relative displacement of aircraft relative to air mass. Said screw is connected with one generator of accumulated power. Said power may be accumulated in pneumatic, electric or kinematic form.
EFFECT: higher efficiency.
20 cl, 6 dwg
SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft power plant and aircraft proper. Power plant comprises first power converter 4, second power converter 5, propulsor 1, first tank 6 with first fuel and second tank 11 with second fuel. First converter 4 generates first power, second converter 5 generates second power for propulsor 1. Propulsor 1 allows generation of straight thrust using aforesaid first or second power. Said first and second tanks 6 and 11 supply first and second fuels that differ. Note here that first and second converters run of first and second fuels, respectively. Proposed method consists in supplying first power to first converter and second power to second converter, feeding first and second power to propulsor 1 for it to generate straight thrust. Note also that first converter 4 runs on either first or second fuel. Note here that first fuel differs from second one.
EFFECT: ecologically safe power plant.
16 cl, 6 dwg
SUBSTANCE: invention relates to aircraft engineering. Aircraft comprises holder 2 of modules designed to accommodate multiple modular elements 3, each being provided with built-in system element. Modular elements and system elements form a structure making an appropriate model of aircraft.
EFFECT: flexible adaptation to various types of equipment.
14 cl, 1 dwg
SUBSTANCE: invention relate to an aircraft with a mixed solution with aerodynamic and space flight and how it is flying. The aircraft includes a fuselage, wing, air-jet engines and rocket engines. The wing holds still, essentially straight and elongated in the lateral direction fuselage. Wingspan makes the length of the fuselage. Wing tanks and rocket fuel are located in the rear fuselage. In front of the fuselage, located cabin. The method of piloting an aircraft contains four phases of flight. The first stage of aerodynamic flight at subsonic speeds, corresponds to 0.5 M-O, 8 M, with the use of jet engines without air refueling. In the second stage of exit in outer space rocket engines are used after giving the command to change the tilt of the aircraft between the first stage and second stage. In the third stage of descent by planning mode to the fuselage, oriented substantially perpendicular to the trajectory. The fourth step is provided by aerodynamic flight and landing after bringing the aircraft into position on the merits in the direction of the trajectory between the third phase of flight and the fourth stage of the flight.
EFFECT: reduced fuel consumption.
14 cl, 3 dwg
SUBSTANCE: invention relates to aircraft engineering. Proposed flight vehicle comprises payload compartment and ejection-type accelerator including nozzles, tightly intercommunicated, and vacuum chamber communicated with tank. Nozzle of said ejection-type accelerator is introduced inside said chamber to allow gas dynamic flow, coming out of the nozzle, to collide in said chamber.
EFFECT: power saving, higher maneuverability, expanded applications.
19 cl, 9 dwg
SUBSTANCE: invention relates to aircraft engineering. Proposed aircraft features opposed arrangement of propellers with their rotational axes arranged at fuselage front and rear ends. Fuselage sidewalls are formed by concave surfaces in fuselage midplane under T-shaped wing with lowered tips that allow controlled turn within 90 degrees. Fuselage front part accommodates aerodynamic surfaces of horizontal tail and low vertical tail unit. Fuselage tail accommodates aerodynamic surfaces in the form of inversed V with controlled tailplane flaps and read-drive wheels of non-retractable landing gear. Tail reversible constant-pitch propeller and front propeller may be coupled with common drive shaft via reversing reduction gear, variator and clutch.
EFFECT: higher stability of VTOL, safe gliding with propellers cut off, increased range and horizontal flight speed.
5 cl, 3 dwg
SUBSTANCE: electric steam balloon comprises gas bag coated with outer heat insulation and inner water repellant shell. Bag bottom section accommodates tubular electric heater filled with water confined by surface equidistant to bag surface and horizontal plate. Steam temperature is maintained and heater is protected in response to signals of temperature gages while the level is kept inside said bag by electric heater controller.
EFFECT: decreased weight of heating system.