RU2436715C2 - Aerospace aircraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering and may be used, in particular, for research of near and far space, destruction or recovery of off-control satellites, etc. Proposed aircraft comprises body shaped as biconvex lens closed by semi-spheres of titanium fairings on top and bottom. Body is stiffened by bearing steel frame to support power plant. The later comprises three groups of engines: four lift-thrust turbojet double-flow engines (with exhaust nozzles of horizontal and vertical thrust 18a and 18b, respectively), two rocket sustainers (with deflecting nozzles 19a) and four vertical thrust rocket engines (with exhaust nozzle 24). Body incorporates tanks 20 with hydrogen four rocket engines. Spaceship is equipped with LH and RH top and bottom aerodynamic pitch control surfaces 33 and 33a, respectively, as well as LH and RH gas vanes 21. It comprises also four undercarriage legs while with undercarriage retracted into domes, landing may be performed on landing skis. Parachute container 5 with cover 5a is provided for landing. For docking with interplanetary probe, tight airlock hatch 8 is used. There are headlights 28a to illuminate rear semi-sphere and onboard navigation lights 22.

EFFECT: multifunctional aerospace aircraft for research of near and far space, destruction or recovery of off-control satellites.

7 cl, 7 dwg

Description

The invention relates to the field of aerospace vehicles and can be used, in particular, for research in near and deep space, for the destruction or restoration of automatic satellites and other artificial space objects that have lost control, and also for changing the trajectories of small celestial bodies (for example, asteroids) in order to exclude their collision with the Earth.

The aerospace aircraft (AKLA) includes a welded hull in the form of a power supporting frame, consisting of steel struts, supported by steel runners, transverse and longitudinal beams, rigidly connected spars to them, to which titanium sheet cowls in the form of two "bowls" are attached ”, Overturned one upon another. The edges of the "bowls" are in contact with the fastening steel ring rigidly connected to the power bearing frame. The ring has threaded holes and three centering pins, allowing you to correctly install and fasten the edges of the lower and upper "bowls" to the steel ring.

The steel ring is attached to the power supporting frame from the side of the lower "bowl" with the help of inclined supports, the ends of which are welded to the frame and to the ring by means of corner amplifiers.

The lodgements and fasteners of the engines of the power plant are mounted on the power supporting frame. In the lower lateral part of the supporting frame there are twelve suspension units of four landing gears that retract into the dome through cutouts in the surface of the lower “bowl”. Two front landing gears of a rotary type provide an ACL turn when taxiing. All landing gears have two wheels with braking and brake release devices.

The racks of the wheel chassis are mounted so that their reference points are at equal distances from the projection of the center of mass point on the supporting surface, taking into account the overturning moment from the impact of the thrust when the engines of the power plant are operating at the time of take-off. In case of landing with retracted wheeled chassis steel rails with pneumatic-hydraulic shock absorbers are provided.

The “bowls” bonded together from one another form a closed volume, which is divided into sectors and segments, in which a pressurized cabin for the crew and scientific personnel, AKLA and power plant control systems, fuel tanks (cylinders), and other equipment are located.

Under the horizontal plane of symmetry of the ACLA body, the engines of the power plant are placed and fixed on the power supporting frame. The AKLA power plant includes: four lift-marching double-circuit turbojet engines, left and right march rocket engines are installed and fastened next to them, and four lift rocket engines are symmetrically placed and attached to the power carrier frame, the nozzles of which are deflected to the outside by an estimated angle.

Marching and lifting rocket engines are powered by hydrogen (helium) from airborne cylinders.

Airborne cylinders are connected in parallel and in series to the rocket engine power system.

The power unit compartment is equipped with a forced ventilation system to ensure the operation of the engines in the design mode and a fire-fighting system that is automatically activated repeatedly.

The control system in the direction of flight provides for the use of extreme (first and fourth) turbofan engines with a change in their thrust, or left and right taxiways when flying in space.

The elevation angle control (height) is controlled by the deviating nozzles of the exhaust nozzles of four turbofan engines or two propulsion engines of the power plant, as well as two pairs (upper and lower) of trapezoidal pitch rudders, the axis of rotation of which coincides with the upper and lower edges of the ACL skin.

With the vertical position of the upper and lower pitch rudders at the same time, they play the role of brake flaps (air brakes) when flying in airspace.

On lateral diametrically opposite sides along the horizontal axis of symmetry, rotary nozzles of gas rudders and rolls are mounted (respectively: “horizontal position”, “vertical position” of gas rudders).

Analogs of the claimed aerospace aircraft - the ship are: the space shuttle "Shuttle" (USA); the Buran spacecraft manned spacecraft (USSR - Russia) and the Phoenix spacecraft commercial spacecraft (USA, 2007-2008).

All these spacecraft are built like an airplane - a spaceship, i.e. they have a fuselage, a wing with controls, a keel with a rudder, a cockpit for crew with control devices and controls, a three-post chassis, a power plant consisting of main rocket engines and RD corrections, and brake parachutes.

These analogues have one common drawback: they are not intended to visit other planets or satellites, they cannot even land on the moon. Having overcome the stratosphere, these spaceships can only spend some time in space and return back to Earth. Their use is very limited.

The closest analogue of the claimed aerospace aircraft can probably be considered "flying saucers", which are also called UFOs ("unidentified flying objects"). However, we earthlings know little about these aircraft. We can only assume that such a geometric shape as the “flying saucers” has is most suitable for flight in the atmosphere and in space, namely, for high cosmic flight speeds in horizontal and inclined planes, and in the vertical plane during take-off, the upper part of the skin is not creates significant air resistance. But the lower skin of the ACLA case of this type can be flatter, or even concave, creates a certain parachuting effect when lowering (during landing), reducing the rate of decrease in the atmosphere, which is important during a regular vertical landing and during emergency landing using a parachute-reactive system. According to the available informative data, choosing a close analogue is not possible.

Therefore, it was decided to develop an aerospace aircraft (hereinafter ACLA), which would have the properties of an airplane flying in airspace and in the stratosphere, and the properties of a rocket plane flying in space and capable of making a vertical landing on the surface of the Earth, another planet or satellite.

This invention proposes the design of a universal type of aerospace aircraft, because It is designed for flight in both airplane mode and rocket mode. For this purpose, a combined power plant is proposed, consisting of 4 double-circuit aircraft turbofan engines used for vertical take-off aircraft with nozzles deflecting the thrust vector (for example, such as for the Yak-141 aircraft), and 2 liquefied hydrogen engines from side cylinders.

Field tests and reconnaissance flights in the stratosphere and in space would allow us to obtain confirmation of scientific data and obtain the necessary and more detailed information about the properties of near space, and in the long term, as well as about the properties of the atmospheres of nearby planets and their satellites.

This is also an argument in favor of creating an aerospace aircraft of the claimed design.

The claimed design will allow the creation of a universal aerospace aircraft, which can also be used to solve urgent ground tasks in atmospheric conditions (for example, to conduct urgent reconnaissance in a particular area of the earth, ocean, to take urgent appropriate measures to organize large-scale fire fighting or to protect transport ships from sea pirates, or to find places in distress of ships, as well as for space flights for the purpose of space research, space reconnaissance, with the aim of yu care to astronauts or replacement of ISS - interplanetary space stations).

Moreover, all of the flights and actions listed will be faster in time and significantly less expensive, less expensive than using other means.

With the introduction of interplanetary space stations (further inhabited) sequentially farther and farther away from the Earth and making their successive visits to the ACL, we will get a real opportunity to make more distant space flights and carry out deeper reconnaissance of space interplanetary space, also at the lowest cost.

All of the above is another argument in favor of the need to create an ACL.

Closest to the claimed invention in appearance is the so-called "flying saucer" of the type "Disk Belonets", which was created in Germany (February 1945).

Visually presented on the first page of the cover of the weekly UFO magazine No. 36 (405) dated September 5, 2005, and the Kaleidoscope Publishing House - a prototype.

The magazine reports on several meetings of the U.S. aircraft carrier Franklin D. Roosevelt (his crew) with a UFO and shows a photograph of a military photojournalist, Volans Litvin, who shot a NATO squadron in marching formations from an aircraft carrier at the Mainbrace naval exercises in the North Sea.

The UFO in the picture is presented in the form of a disk-shaped aircraft with running engines. The nozzle is clearly visible in the image, corresponding in appearance to the nozzles of modern spacecraft (the nozzle of the main lifting engine and four nozzles of the correction engines).

On page 5 is a photocopy of the photograph indicated in the text.

This photograph does not give an idea of the marching engine (s), if this aircraft has the prototype.

The claimed invention is aimed at solving the technical problem of creating an aerospace aircraft to ensure continued research in the near and far space using interplanetary space stations (hereinafter - MKS).

The solution to the technical problem is achieved:

1. The creation of the body (bearing frame of a welded structure made of high strength steel).

2. The creation, alignment and fastening of the outer steel ring to the supporting frame and fastening the upper and lower "fairing bowls" to it.

3. The creation of lodges for the installation and fastening of four dual-circuit aircraft engines, such as the engines of the Yak-141 aircraft.

4. The installation of four lift-marching double-circuit aircraft engines, such as the engines of the Yak - 141 aircraft of vertical take-off and landing and fuel tanks for them.

5. Installation and fastening of two mid-flight rocket engines.

6. Installation and fastening of cylinders of liquefied fuel for them.

7. Installation and fastening of devices for liquefying, regenerating and supplying hydrogen fuel to rocket engines.

8. Installation and fastening of four lifting rocket engines of adjustable thrust to ensure vertical take-off, hovering, lowering and landing.

9. Installation and fastening of cylinders of liquefied hydrogen - fuel for lifting rocket engines.

10. Fastening to the middle and lower beams of the supporting frame of the four-post chassis retractable in the dome.

11. Equipping each of the four chassis racks with two wheels of increased strength and the necessary devices and devices.

12. The equipment of the pressurized crew cabin, equipped with everything necessary for flying in the Earth’s atmosphere, as well as for flying and working in outer space.

13. The creation of reliable protection of the cabin from small particles found in space.

14. The equipment of pressurized hatches for entry into the ACLA and into the cockpit.

15. The equipment of the hatch and docking gateway for docking the ACL with the ISS or with another spacecraft.

16. Equipping ACLA container for brake and exhaust parachutes.

17. Equipment sealed upper hatch for emergency escape from the cockpit.

18. Equipment ACLA necessary life support systems, communications, signaling and towing devices.

19. The implementation of the take-off of the ACLA, overcoming the Earth’s atmosphere and entering outer space.

20. By docking with the ISS, refueling hydrogen from the ISS cylinders (where hydrogen is delivered by cargo spacecraft) and separation from the ISS.

21. Landing on the planet (satellite).

22. Take-off from the planet and return with landing on Earth.

Note: it is possible that the launch of the ACLA will be carried out both from the launch pad of the cosmodrome and from the fuselage of the carrier aircraft.

Since information about the prototype is not enough, then comparative analysis with the prototype does not make sense.

The inventive aerospace aircraft is designed as universal, because it can fly in atmospheric conditions and fly in space for the purpose of space research, space reconnaissance, as well as to provide medical assistance to astronauts or to replace ISS crews and spacecraft. This ACL will allow to continue further development of the device of spacecraft and flights to them, to continue research in near space, as well as in deep space, using interplanetary space stations (farther and farther away) farther from the Earth, which can supply ACL with liquefied hydrogen - fuel for its taxiway, where this fuel can be delivered by cargo spacecraft.

The proposed device is presented in figures 1-7.

Figure 1 is a front view of the AKLA.

The main parts of which the case is assembled:

- power bearing frame - 1 welded construction;

- vertical beams - 2;

- horizontal and radial beams - 3;

- mowing with corner amplifiers (not shown in figure 1);

- stiffening rings: 4a, 4b, 4c;

- the upper - 4a frames the parachute container - 5 with a lid - 5a and emergency emergency hatch - 7;

- average - 4b is used to connect and fasten the AKLA titanium sheathing in the form of 2 (lower and upper) “bowls” around the circumference;

- lower - 4c frames the pressurized hatch - 8 of the gateway, which serves to dock with the ISS and transfer astronauts to the ISS or to the spacecraft;

the lower ring - 4c also serves to protect against damage to docking devices (not shown in Fig. 1) and nozzles - 18b of vertical thrust of 4 AKL turbojet engines;

- side members - 9 two-shelves (together with a ring 4b) serve for fastening the lower and upper fairings - “bowls”, which are made of two-layer (external and internal casing);

- casing - fairings: upper - 10 and lower - 10a;

vertical beams - 2 of the power bearing frame - 1 are supported by runners - 11 and connected to them by means of hydropneumatic and spring shock absorbers (not shown in Fig. 1);

- crew cabin - 12;

- window - 13 cabins with armored curtain - 14, periscope - 15;

- a sealed hatch - 16 for entering the ACLA;

- a sealed door - 17 for entry into the cockpit;

- input devices - 18 bypass turbofan nozzles - 18b vertical thrust turbofan engines;

- input devices - 19 compressors used to study the composition and concentration of gases in space;

- cylinders - 20 liquefied gas for rocket engines;

- gas rudders - 21 directions and banks;

- airborne navigation lights - 22;

- antenna - 23 radio communication station, antenna - 23a recognition system;

- nozzles - 24 rocket engines of vertical thrust;

- forward rotary rack of the chassis - 25;

- headlights - 26, fog lights - 27;

- onboard identification lights - 28;

- alarm lights - 29;

- pyromechanism - 6 shots of the cover of the parachute container;

- radar - 30 with a phased array;

- heat direction finder - 31; chassis domes - 36.

Features of the design of the skin of AKLA

Painting of the outer surface of AKLA

Sheathing should probably be multi-layered. This invention provides a three-layer cladding. The outer layer is heat-protective (provides protection against heating, ventilation between the outer and middle layers). Between these layers, for fastening the outer to the middle layer, movable supports are attached taking into account the thermal expansion of the material of the outer layer. The middle layer, the sealed layer of the cladding, followed by the inner sealed layer. Between the middle and inner layers, the free space is filled with high-strength and heat-resistant rubber or material that replaces it according to the specified characteristics, and provides noise insulation. The shock absorbing trim of the ACLA cab is attached to the inner layer.

The pressure in the closed volume of the ACLA is provided by a barostat.

Engineering calculations of the three layers of sheathing are carried out by specialists in aviation materials, specialists in the strength of the ACLA body, specialists in thermal protection and ventilation, on protection against atmospheric electricity, on protection against cosmic and galactic radiation, on protection against meteorites and meteor shower; specialists in instruments and various sensors placed on all three layers of skin.

I suggest painting the surface of the upper hemisphere in white or silver, and the lower hemisphere in gray in light or dark colors.

Figure 2 (side view of the ACLA):

- stiffening rings: 4a, 4b, 4c;

- pyromechanism - 6;

- a pressurized hatch - 8 locks for astronauts to transition to the ISS;

- fairings: upper - 10, lower - 10a;

- crew cabin - 12;

- a sealed hatch - 16 for entering the ACLA;

- a sealed door - 17 for entry into the cockpit;

- input devices - 18 turbofan engines,

- exhaust nozzles - 18a turbofan engine;

- input devices - 19 RD compressors;

- exhaust nozzles - 19a taxiway;

- cylinders - 20 liquefied gas (not shown in figure 2);

- gas steering wheel - 21;

- antenna - 23;

- nozzles - 24 RD vertical thrust;

- headlight - 26;

- onboard identification lights - 28;

- alarm lights - 29;

- left upper pitch steering wheel - 33.

Figure 3 is a rear view of the ACLA:

- parachute container (compartment) - 5;

- cover - 5a of the parachute container;

- a pressurized hatch - 8 locks for docking with the ISS;

- left ski runners - 11;

- window - 13a rear view with armored curtain;

- exhaust nozzles - 18a turbofan engine with nozzles deflecting the thrust vector;

- exhaust nozzles - 18b vertical thrust turbofan;

- exhaust nozzles - 19a marching taxiways with deflecting nozzles;

- cylinders - 20 with hydrogen (fuel) for taxiways;

- gas rudders - 21;

- exhaust nozzles - 24 RD vertical thrust;

- landing gear - 25;

- two lights - 26a lighting the rear hemisphere;

- airborne navigation lights - 22;

- left and right upper pitch steering wheels - 33;

- left and right lower pitch wheels - 33a (not shown in FIG. 3);

- external sensor - 34 ambient temperatures.

Figure 4 is a top view of the ACLA (in plan):

- stiffening ring - 4a (upper);

- cover - 5a of the parachute container;

- pyromechanism - 6 shots of the cover of the parachute container;

- emergency pressurized hatch - 7;

- upper fairing - 10;

- window - 13 cabins, armored curtain - 14, armored shield - 14a;

- periscope - 15;

- a pressurized hatch - 16 entrances to the ACLA;

- gas rudders - 21;

- airborne navigation lights - 22;

- antenna - 23A of the ACLA recognition system;

- onboard identification lights - 28;

- alarm lights - 29;

- pitch steering wheels - 33 (upper) - can work separately: upper - lower, left - right;

- air pressure receivers - 35 (LDPE), for indicators of flight speeds and flight altitude.

Figure 5 is a bottom view of the ACLA:

- ring - 46 stiffness;

- pressurized hatch - 8 for docking and transition of the crew to the ISS;

- nozzles 18b vertical thrust turbofan;

- Marching taxiway - 19a with controlled nozzles;

- nozzles 18a turbofan engine with thrust vector deflecting nozzles;

- nozzles - 24 RD vertical thrust;

- compressors - 19 marching taxiways (vertical thrust taxiway compressors are not shown in FIG. 5);

- Sashes - 36 chassis domes;

- compartments - 37 for transportation and release of inflatable bags (which are used when landing on water).

Figure 6 - take-off ACLA;

In Fig.7 - landing AKLA on the planet.

In a static state, all ACLA systems are turned off, the controls (switches and switches) on the take-off and take-off control panels are turned off, closed by special keys and turned off by electronic means of protection against unauthorized switching on.

These remotes and other AKLA controls are located in cockpit places convenient for the crew near the seats of astronaut pilots.

Access to devices and assemblies located in the zone of the hermetic volume of the ACLA is possible only after passing through the entrance hatches-doors of the ACLA and the cab.

Access to devices and assemblies located outside the zone of the sealed volume of the AKLA for their maintenance is carried out through the corresponding hatches, which are indicated on the outer skin of the AKLA. Upon receipt of a command for preparation for take-off, all crew members occupy their jobs in the ACLA cabin and begin preparation for take-off, in accordance with their duties: all ship systems are checked for operability in the corresponding modes, some systems are checked for their serviceability, and the completeness of refueling is checked by all types of fuel, gases (oxygen, nitrogen, etc.) and liquids (including water), the computer-computer complex, autopilot, and the power plant are checked.

Upon completion of preparation for take-off, the crew commander reports to the MCC.

Upon receipt of the “Take-off!” Command, the AKLA crew takes off according to the “Instruction”.

Full-time AKLA take-off with runway

It is carried out similarly to the take-off of an aircraft with double-circuit turbojet engines. Taxiing is performed on the runway, at the start of the nozzle the turbojet engines are installed at an angle of 30 * up, the upper pitch wheels are rejected at the maximum angle. All four turbojet engines are brought to the maximum mode or afterburner is turned on and take-off with run on the runway is performed, followed by the use of controls, set the ACL to the appropriate take-off angle, direction and roll angle.

Note: the value of the required angle of the thrust vector during take-off is determined (initially) on a movable test bench, and is specified during full-scale flight tests of the ACL.

Regular takeoff from the runway can be performed with four working turbofan engines, and with two working turbofan engines, taking into account the necessary flight modes at low altitudes near the Earth and depending on the load.

Vertical take-off from a separate site or runway

AKLA, equipped with dual-circuit turbojet engines for vertical take-off aircraft, equipped with a nozzle unit of vertical thrust, can perform vertical take-off from a separate concrete or unprepared site. For vertical take-off, the vertical thrust contour of all four turbofan engines is switched to the “vertical take-off” mode. In this case, the gas flow from the secondary circuits through the vertical gas ducts is ejected by the vertical exhaust nozzles into the space under the ACL. The second circuits of the first and fourth double-circuit turbojet engines are connected by pipelines to the nozzles of the onboard gas rudders of the direction and bank, respectively, of the left and right. With vertical take-off, the nozzles of the gas rudders must be tilted down. When one of them is blocked by an electro-pneumatic valve, an ACLA roll will be created in one direction or another.

Under the influence of vertical thrust, the ACL rises above the base platform and is then controlled by the pilot-cosmonaut in the same way as with horizontal flight, taking into account the requirements for the power plant mode, level and direction of flight.

During horizontal flight, the gas rudders unfold to a horizontal position when turned on with two buttons on the control stick of the ACLA, perform the function of the rudder, providing rotation of the ACLA relative to the vertical axis.

Note: if a decision is made to take off an ACLA from a carrier aircraft, which will raise it to the maximum achievable flight altitude of the carrier, it will be necessary to develop appropriate devices for attaching the ACLA to the carrier aircraft and a device for uncoupling from it.

As you know, before the stratosphere, aerodynamic rudders are effective, but in the upper layers of the stratosphere and in space, these rudders lose their effectiveness and there is a need to replace them with gas rudders. Therefore, the design of the ACLA provides for the connection of pipelines of gas generators of the left and right rocket engines with gas rudders. The gas rudders are rotated from horizontal to vertical by electromechanical actuators, and gas rudders are controlled by electro-pneumatic valves installed inside the ACLA body in front of the gas rudder nozzles.

Fuel is produced from AKLA tanks so that it starts from hanging tanks, and then from onboard fuel tanks symmetrically located in the AKLA body. At the same time, power is supplied from the left tank to the first and third turbojet engines, and fuel is supplied from the right tank to the second and fourth engines. In the same order are provided with fuel and two mid-flight rocket engines. Lastly, fuel is generated from the central tanks, which are located closer to the center of gravity of the ACL.

Note: after fuel has been generated from the overhead tanks that can be used, the latter are dumped in a safe area along the flight route.

Docking with the interplanetary space station (ISS-1)

It is carried out using well-known knots-mechanisms for docking spacecraft with the ISS. Reciprocal parts of the docking mechanisms are in the lower domed part of the ACLA. There is also a sealed airlock hatch for transition from AKLA to the ISS. Docking and transition technology is known to those skilled in the art. In addition, it is necessary to take into account the following features of ACLA: in order to reduce the take-off weight of ACLA, it is proposed to refuel fuel for turbojet engines not 100%, but only 50% of the total volume required for flight to ISS 1 and vice versa; to ISS 2 or to another planet (or its satellite) and to return to ISS 2, and so it repeats in the reverse order. At the last stage of the flight to the Earth, refueling is performed after docking with the ISS 1, which leaves the fuel reserve necessary for the flight from the ISS 1 to the Earth. If during field tests it will be confirmed that there is enough hydrogen in space to pump it into onboard reserve cylinders, then the need for refueling on the ISS will disappear.

Docking from the ISS

If the ACLA and the crew are ready to perform the next phase of the flight, then after checking the amount of fuel in the ACLA tanks, it is necessary to perform:

- sealing of the ISS and AKLA,

- undocking of the ACL from the ISS,

- inclusion of vertical thrust rocket engines,

- after separation from the ISS, turn on route taxiways and continue the flight along the route.

Landing on another planet or on the moon

When approaching the landing or inspection object, they reduce the flight speed, and at the calculated time they switch to vertical thrust taxiways, lower and select the landing site, reduce vertical thrust, tracking the approach speed, release a parachute, which ensures a safe landing-landing speed without chassis, i.e. on shock absorbing skids. After landing, they verify radio communications with the ISS or from the MCC on Earth. Note: the position of the ACLA on runners (when landing on an uneven surface) allows you to turn on rocket engines and carry out vertical take-off from the landing site with the subsequent inclusion of mid-flight rocket engines.

Take-off from the surface of the planet, satellite of the planet

After determining the actual environmental data on the planet (satellite), after taking samples and obtaining as much information as possible about the planet under study, the crew proceeds to prepare for take-off and takes off from the planet's surface, for which they include lifting rocket engines. Under the influence of vertical thrust, the ACL rises above the planet’s surface, the astronauts switch the lifting engines to the marching taxiways, and then control the ACL in the same way as in normal horizontal flight, acting on the controls taking into account the flight mode. Next, they fly to the nearest ISS from the planet, followed by docking with a space station, refuel on it, or fly to Earth. In this case, the landing can be performed on the runway of the cosmodrome or on a separate platform using a parachute-reactive braking system.

Native landing of an ACLA on a runway (to the ground) is performed in the same way as a landing of a fighter aircraft as follows:

when they return to Earth, after passing through the stratosphere, they launch four turbofan engines (maybe only two thrusters will be enough for landing), they will show full-scale tests, and, controlling the power plant and ACL, go to the area of the cosmodrome or airfield, release a 4-post chassis run on the runway according to the instructions.

If a full-time landing on a runway cannot be performed for any reason, then using the capabilities of 4 turbofan engines for vertical take-off and landing, a full-time landing is performed on a separate platform, on an unprepared landing site or on water using controlled vertical traction.

Emergency landing can be performed using a brake rescue parachute with the subsequent inclusion of powder braking engines.

In the upper dome part of the case above the center of gravity of the ACLA there is a hermetic compartment, the lid of which is reset using a pyromechanism. The compartment is designed for laying and transporting a rescue and exhaust parachute brake. The compartment lid is blocked by an exhaust cord with an exhaust parachute, which, when filled, pulls the brake rescue parachute behind it - the ACLA decreases on the brake parachute with the subsequent activation of the powder brake motors, which ensures a soft landing of the ACLA with an estimated impact force not exceeding safe.

Note: The position of the ACLA on the runners allows you to turn on four rocket engines of vertical thrust, for vertical take-off from the landing site, followed by switching to the horizontal thrust of mid-flight rocket engines.

When landing on water, the doors of the hatches of airborne containers open, in which inflatable bags are laid. When opening the locks holding the hatch flaps, 2-4 pneumatic valves are activated, through which gas - nitrogen under pressure of a calculated value from the air cylinders fills inflatable bags - floats that fall out of containers and keep the ACL afloat in water.

The implementation of the claimed device of an aerospace aircraft (LA) is creating a new type of space aircraft that allows you to perform tasks for the further study of both near and far outer space, planets, satellites, the Moon; as well as conducting tests of created spacecraft in the Earth’s atmosphere and in space, carrying out their consistent development, preparing for space flights and research, providing more active systematic development of space science and space technology at the present time, eliminating a significant lag in these areas of knowledge from other countries where similar aircraft are already being created or will be created in the coming years, and there is also a need to provide urgent assistance to the crews of stationary space stations tion or spacecraft.

The possibility of creating and using the ACL of the proposed design is confirmed by the whole course of development of aviation and space technology, existing spacecraft, known and existing power plants, stabilization and control systems for spacecraft, modern scientific data on outer space, as well as the proposed devices and equipment in accordance with the claimed invention.

Claims (7)

1. An aerospace aircraft, comprising a body in the form of a biconvex lens, formed by a power bearing steel frame of a welded structure, consisting of vertical and horizontal beams, slopes and spars, on which engines are mounted and fixed, which provide lifting, launching and movement of the spacecraft in a given direction as well as struts of wheeled chassis and controls, and the specified lens is covered from below and above by hemispheres of fairings made of multilayer of durable material, providing x reliable protection of the crew, power plant, fuel tanks, equipment and premises of the ship, characterized in that the outer layer of the fairings is made of titanium sheet, and the fairings are attached to the power supporting frame using spars and three fixing steel stiffening rings: upper, middle and lower, the power plant consists of three groups of engines: four lift-march turbojet dual-circuit engines, two march rocket engines and four vertical thrust rocket engines. 2. The aerospace aircraft according to claim 1, characterized in that to improve controllability in various flight modes, it is equipped with four aerodynamic pitch rudders and two side (left and right) gas rudders, which allow you to smoothly change horizontal and vertical angles in direction and roll . 3. The aerospace aircraft according to claim 1, characterized in that it is equipped with a four-post chassis having two wheels on each strut, the two front struts being freely oriented or controllable from the cockpit, and when the chassis is retracted into the canopy, the landing of the aerospace airplane can be performed on skids that are attached to the vertical struts of the supporting frame using pneumohydraulic shock absorbers. 4. The aerospace aircraft according to claim 1, characterized in that it has a sealed armored cabin and a space for the astronauts to relax, storage for food and drinking water, which are equipped with all necessary life support equipment, control systems, instruments for monitoring the operation of these systems, duplicating and rescue systems. 5. The aerospace aircraft according to claim 1, characterized in that in the upper dome part, within the upper ring of stiffness, a parachute container and a sealed emergency hatch are placed for the crew to leave the cabin in case of an accident or other need. 6. The aerospace aircraft according to claim 1, characterized in that in the lower dome part, within the lower ring of stiffness, a gateway is mounted with a pressurized hatch for astronauts to transfer to an interplanetary space station, or to another spacecraft, or to the landing site. 7. The aerospace aircraft according to claim 2, characterized in that in the upper upper and lower parts of the hull it has two indicated pitch wheels, the outer side of which repeats the curvature of the casing of the upper and lower fairings, and these wheels can work in pairs (upper or lower ), synchronously (all four) and separately one at a time.

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