RU2342288C1 - Method of servicing cosmic articles and shuttle aerospace system for its implementation - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: method of servicing cosmic articles with shuttle aerospace system includes preparation of system for flight installation of aerospaceplane on carrier-plane, take-off, delivery of aerospaceplane to destination spot, take-off of aerospaceplane from carrier-plane, injection into orbit, orbital flight, deorbitting, controlled reentry, landing on carrier-plane, landing of carrier-plane; delivery of aerospaceplane to destination spot is performed in maintenance compartment of carrier-plane. Carrier-plane is made with wing containing center wing section and arrow-shaped arms. Aerospaceplane plane is made with wing containing center wing section and arrow-shaped arms and vertical empennage. Center wing section of carrier-plane has takeoff and landing strip on its upper surface.

EFFECT: improvement of efficiency of shuttle aerospace system.

4 cl, 14 dwg

Description

Technical field

The invention relates to aerospace technology, namely to reusable aerospace complexes, and can be used in systems for servicing space objects: transporting and delivering payload into orbit, removing spent space elements and delivering them to the ground; to increase their effectiveness.

State of the art

Known aerospace system, which contains an accelerator and its vertical cryogenic container with liquid oxygen, a space launch vehicle with a liquid rocket propulsion system (patent RU 2165869 C1, IPC B64G 1/14, 2000). The system is designed to deliver payload into orbit, but has insufficient efficiency due to a single use of the launch vehicle.

A known method of transporting payloads (patent RU2120397 C1, IPC B64G 1/14, 1996) of a reusable aerospace system, including the docking and joint flight of aircraft: aerospace aircraft (VKS) and ground-based transport aircraft (TS), their undocking, as well as the exchange of goods transported between the Earth and the orbital station, through the VKS. At the same time, VKS are based on the orbital station, docking and joint flight of VKS and TS are carried out in the Earth’s atmosphere, and the exchange of payloads is performed between the VKS and TS during their joint flight, and upon completion of the exchange of payloads and undocking, these aircraft are sent to basing points .

The known method is characterized in that the VKS after exchanging cargo with a transport aircraft must return to the ground for maintenance and fueling, which reduces the efficiency of the system.

Also known is the launch and transportation system of the payload (patent RU 2233772 C2, IPC B64G 1/14, 1999). The system includes an aircraft-spacecraft of an airplane circuit with ejector direct-flow jet engines, a returnable spacecraft with a rocket engine as a second stage and, if necessary, an interorbital transport device as a third stage.

The aerospace apparatus contains a fuselage, two wings with several control surfaces, a tail unit with a rudder and an engine nacelle. In this case, the fuselage is made with a maximum cross section at the base of the leading edge of the wings, sufficient to accommodate a payload compartment, access to which is formed by two flaps extending from the nose towards the tail and forming a cover and ramp of the payload compartment, which can open for receiving or unloading the payload and closing during the flight, while these wings are attached to the fuselage at its center line, the front edge of each wing is tilted back from the point of connection eniya with plating belt and forms an arrow shape.

A catapult and two guide rails for the payload are installed in the payload compartment, and the apparatus contains a returnable spacecraft (VKA), which can be installed in the payload compartment on the guide rails and includes a rocket engine in communication with the tanks of liquid hydrogen and liquid oxygen equipped with tanks with helium boost system, equipment compartment, main body, rear equipment compartment, tail section with engine hood and swiveling nose.

At the same time, the RCA is equipped with a nose landing gear, two main landing gears and several travel rollers that are open in the folded position of the wings and can be supported by guiding rails for the payload, an orientation control system containing jet control engines for spatial orientation, guidance, navigation and control equipment and primary power plants.

The system is also designed to allow the RCA to return to the ground after cargo has been delivered into orbit for maintenance and fueling, which reduces its effectiveness.

Known aerospace system for launching and landing reusable spacecraft using ekranoplanes ("Bulletin of Aviation and Cosmonautics No. 4, 2001" www.testpilot.ru/review/ws/.htm.).

The system includes an ekranoplan-accelerator - receiver and a two-stage VKS. The spent stage of the VKS lands on a flying ekranoplan. Similarly, landing on a flying ekranoplan and the orbital stage itself is performed upon its return, after which it can be launched again. The docking of the VKS and the ekranoplan is carried out when their speeds are aligned with the help of special docking nodes-catchers.

The ekranoplan is made according to the “composite wing” scheme with two body-fuselages, engines are located in its bow.

The VKS is located on the central wing, and the tail part of the winged wing is split, with double vertical tail.

WIG capabilities in height and time spent at the selected height are limited. In addition, the system does not provide for the maintenance of the VKS and the orbital stage on board. Therefore, the effectiveness of the space facilities maintenance system is limited.

SUMMARY OF THE INVENTION

The objective of the invention is to develop a method of servicing space objects and a reusable aerospace system for its implementation, which would have increased efficiency due to the repeated use of the aerospace system in orbit without landing on the ground and ensuring its short-term operation without ground-based facilities.

In addition, the system should provide an increase in the mass of delivered goods into orbit and the delivery of spent space objects from orbit while reducing the cost of operations.

The problem is achieved in that in the method of servicing space objects using an aerospace system, including a carrier transport aircraft (SN) and a reusable returning orbital aerospace aircraft (VKS), which includes preparing the system for flight with the installation of the VKS on the SN, take-off , delivery of the aerospace helicopter to the desired location, take-off of the aerospace helicopter from the SN, orbital launch, orbital flight, descent from the orbit, controlled descent in the atmosphere, landing on the SN and ground landing of the SN; At the start point, the VKS is transferred to the take-off and landing pad and take off, and after landing and fixing the VKS it is placed in the maintenance compartment of the SN, after-sales service is carried out, followed by the subsequent launch of the VKS into orbit, and reusable aerospace the system for servicing space objects comprises a transport carrier aircraft (SN) made with a wing containing a center section and arrow-shaped consoles, and a reusable orbiting aerospace An airplane (VKS), made with a wing containing a center section and swept consoles, and a vertical tail, while the center section of the aircraft is made with a take-off and landing platform on its upper surface, equipped with nodes for connecting the aircraft between the aircraft and the aircraft; the system is equipped with means to ensure landing of the aircraft; CH made with the wing center section containing an internal maintenance compartment, made with dimensions sufficient to accommodate the air-conditons made with folding wing consoles and vertical tail unit, and is equipped with means for moving the VKS into the compartment.

In addition, the maintenance compartment is made with a hatch on the upper surface of the center wing over the entire size of the compartment, closed by two-sided retractable telescopic flaps, and is equipped with a take-off and landing platform that extends to the level of the upper surface of the center wing during take-off and take-off, and the take-off and landing platform consists of the power frame of the platform, moving along the guides with the help of creepers and double-acting telescopic hydraulic cylinders, rigidly connected with the lower power frame of the compartment, frame platform and the platform itself, the platform there are seats with VCS fixation devices and wedge abutments limiting the movement of the platform in the longitudinal and transverse directions in the extreme positions.

This embodiment of the method of servicing space objects and a reusable aerospace system can increase their efficiency, increase the mass of goods delivered into orbit while reducing the cost of their delivery.

The list of figures in the drawings.

The invention is illustrated by drawings, in which:

Figure 1 - shows a General view of the MAX-OKO (side view).

Figure 2 - shows a General view of the MAX-OKO (view in plan).

Figure 3 - shows a General view of the MAX-OKO (front view).

Figure 4 - shows a section aa of figure 2.

Figure 5 - shows a section bB of figure 2.

6 - shows a General view of the landing platform.

7 - shows a General view of the module of the fixing device of the VKS (before landing VKS).

Fig. 8 shows a general view of a module of a VKS fixation device (after landing of an VKS).

Fig.9 - shows a General view of a reusable manned VKS (side view).

Figure 10 - shows a General view of a reusable manned VKS (plan view).

11 - shows a General view of a reusable manned VKS (front view).

Fig - shows a General view of the block of fuel tanks (front view).

Fig - shows a General view of the Central fuel tank (side view).

Fig. 14 shows a general view of a side fuel tank (side view).

The implementation of the invention

Maintenance of space objects in accordance with the invention is as follows.

The method of servicing space objects is performed using an aerospace system including a carrier transport vehicle (SN) and a reusable orbiting aerospace aircraft (VKS). At the same time, the MV is made with a runway on the upper surface of the wing center section and with an internal maintenance compartment located inside the wing center section, and is equipped with means for moving the aircraft to the runway platform from the compartment and vice versa - from the runway platform to the axle. Such means can serve as lifting and transport mechanisms.

The reusable manned VKS includes a wing, a fuselage, a vertical tail, a propulsion system, a three-leg landing gear and other known systems and equipment necessary for a safe flight. The VKS propulsion system includes orbital maneuvering engines and atmospheric maneuvering engines. The aerodynamic configuration of the VKS is made with aerodynamic quality sufficient for a controlled flight in the atmosphere.

During ground preparation for the mission, the SN is refueled and loaded with the necessary equipment for the flight. VKS is installed on the runway, with the help of a lifting device VKS are moved to the maintenance compartment. Refueling of fuel tanks and VKS systems from ground sources is carried out, preflight preparation of VKS is carried out.

After the takeoff of SN from the VKS on board and the flight along the route to the launch site, the VKS is moved to the runway.

SN at an altitude of 8-9 km and a speed of V = 0.65-0.7 M performs a slide, and at the upper point take off the aerospace forces with separation from the SN and then launch the cruise rocket engine VKS and continue its acceleration in autonomous mode with subsequent exit into orbit. CH returns to the airfield.

The VKS performs an orbital flight, and after completing the flight mission, the VKS performs its descent from orbit and controlled descent in the atmosphere.

After taking off, the CH flies along the route to the point of docking with the orbital plane.

The carrier aircraft is displayed at a predetermined course, altitude and flight speed, and the orbital plane approaches the carrier aircraft and, after reaching zero relative speed, makes a docking with the take-off and landing platform using the landing gear and docking nodes-catchers. After docking and fixing on the take-off and landing platform, the VKS using a lifting device is moved and placed in the maintenance compartment of the SN, where it is serviced. If necessary, carry out the subsequent launch of the VKS into orbit. CH can be returned to the airfield or wait for the return of the aerospace forces for subsequent maintenance.

A reusable aerospace system for servicing space objects (MAKS-OKO) includes (see Fig. 1) a heavy subsonic carrier aircraft 1, a reusable manned aerospace aircraft 2 and a partially reusable block of fuel tanks 3.

The heavy subsonic carrier aircraft 1 is made according to a two-fuselage scheme with a highly located wing and includes a wing 4, a fuselage 5, a V-shaped tail unit 6, a power unit 7, a landing gear consisting of a front strut 8 and rear main struts 9, and others Known systems and equipment necessary for a safe flight. The wing 3 includes (see figure 2) the center section 10, the right and left swept consoles of the wing 11, 12; connected with the center section 10 of the right and left transition compartments 13, 14.

The right and left wing consoles 11, 12 are equipped with ailerons 19, 20, flaps 21, 22, spoilers 23, 24, slats 25, 26 and brake flaps 27, 28. The transition compartments 13, 14 are equipped with brake flaps 29, 30 and spoilers 31, 32.

The center section 10 is made with an average sweep along its leading edge and a relatively large thickness of its aerodynamic profile, which allows it to accommodate a maintenance compartment with a take-off and landing platform. The center wing has in the central part a hatch 33 with telescopic flaps 34.

The rear edge of the center wing is straight, with the upper surface of the center wing raised upward relative to the upper surfaces of the fuselage 15, 16 (see FIG. 3), and the lower surface of the center wing together with the lower surfaces of the fuselage forms a “supporting fuselage” pattern.

The transition compartments 13, 14 are made with medium sweep along their leading edges with an aerodynamic profile that is variable in thickness and are designed to ensure a smooth transition of surfaces between the center wing 10 and wing consoles 11, 12. The trailing edges of the transition compartments are made straight.

The fuselage 5 is made in the form of two - right and left - fuselages 15, 16. The swept V-shaped tail unit 6 is made in the form of two symmetrical bearing surfaces - the right and left 17, 18 with an angle of 90 ° between them and mounted on the tail sections of the right and left fuselage 15, 16.

The power plant 7 is made in the form of six turbojet engines. 4 engines are mounted on pylons on the lower surfaces of the wing consoles 11, 12, 2 engines are mounted on pylons on the lower surfaces of the transition compartments 13, 14.

The center section 10 contains an internal compartment maintenance 110 (see figure 4). The compartment 110 is formed by the upper (see Fig. 4), lower power frame 36 connected by the front and rear transverse walls 37, 38, the left and right longitudinal walls 39, 40. The lower power frame 36 is made of power beams and external panels forming the lower the surface of the center section, rigidly connected with the lower surfaces of the fuselage 15, 16 (see figure 5). From above, the compartment is hermetically closed by telescopic sliding wings 24. The compartment is equipped with a take-off and landing platform 25.

The power frame 35 is made with a hatch 33, made across the entire dimension of the maintenance compartment 110 and provided with sashes 34.

The left and right longitudinal walls 39, 40 have guides (not shown) along which the lifting mechanism 42 moves. The upper power frame 35 has guides (not shown) along which two two-sided telescopic shutters 34 are moved using electric drive trolleys with driving wheels ( not shown). In the open position, the flaps are retracted into the tidal recesses 43 of the outer skin of the center section; in the closed position, the flaps hermetically close the inner volume of the center section. On the lower power frame 36, cylindrical guides 44 are installed, which are connected with their upper parts to the longitudinal walls 39, 40. The take-off and landing platform 45 moves along the cylindrical guides, and in the retracted position the surface of the platform 45 forms a single surface with the cargo floors of the fuselages 15, 16. The front and rear transverse walls 37, 38 are rigidly connected with the frames of the fuselages 15, 16 and the side members 47, 48 of the transition compartments 15, 16 and together with the upper and lower power frames 35, 36 form a single structure, bearing all weight and aerodynamic loads.

The compartment of the fuel tank unit 26 is made in the form of two - right and left - compartments 27, 28, formed by the frames of the fuselages 29, 30, the lower power set 21 and the upper power set 31, 32.

Cryogenic fuel and an oxidizing agent 33 for the OS are located in the right compartment 27, and an empty block of fuel tanks 3 is located in the left compartment 28.

The lower power kit 21 carries a cargo floor 34, designed to accommodate goods and equipment. Power sets 20, 21 of the center section are made of power beams and form, together with the side ribs 22, 23, a single structure that accepts all weight and aerodynamic loads.

The take-off and landing platform 45 (see Fig. 6) consists of a power frame of the platform 49, which moves along the rails 44 with the help of crawlers and double-acting telescopic hydraulic cylinders, rigidly connected with the lower power frame 36 and the power frame 49 and the platform 52 itself, which moves with using double-acting telescopic hydraulic cylinders 53, rigidly connected with the power frame of platform 49 and platform 52. On platform 52 there are seats with fasteners for fixing devices 54 of VKS and wedge stops restricting emeschenie platform in the longitudinal and transverse directions in the extreme positions.

The fixing device 54 of the videoconferencing device consists of three single-type separate modules 55 (see Fig. 7) installed on the take-off and landing platform in accordance with the parameters of the longitudinal base and track gauge of the aerospace gear. The module consists of a mounting plate 56 and a power-receiving device 57, 2-articulated articulated levers 58, 2-articulated rocker arms 59, a liquid-gas shock absorber 61, 2 locking mechanisms 62, 2 guiding power-receiving devices 63, installed on it 2 front stops 64.

Two steering wheels of the chassis 60 are mounted on the take-off and landing platform in such a way that they form a V-shaped profile with the rocker arms 59 for orienting the position of the wheel during mileage at the time of landing. The installation plate with the rest of the devices is mounted on the take-off and landing platform during its preparation for the reception of the aerospace system.

The operation of the device is as follows.

At the initial moment (see Fig. 7), under the influence of pressure in the gas cavity of the shock absorber 61, the power sensing device 57 along the guides 63 moves to its extreme forward position. The rocker arms 59 are manually moved to the extreme left position against the stop in the guide 60 and the side surface of the device 57. The crank lever 58 is moved to the extreme left position (locking mechanism 62 is removed). The rocker arms 59 and the guides 60 orient the movements of the chassis wheel relative to the power sensing device 57 when landing the VKS. When VKS is landing on the take-off and landing platform, the chassis wheel acts on the device 57, which, moving along the guides 63, acts on the shock absorber 61 and compresses it (Fig. 8), and the rear side surface, acting on the lever arm 58, moves it to the extreme right position. The lever 58 acts on the rocker arm 59, moves it to the extreme right position until it stops against the wheel and makes mechanical contact with the counterpart of the second rocker arm 59. When mechanical contact occurs, the electrical contact closes and the locking mechanism hydraulic actuates 62, fixing the position of the lever 58 with a mechanical stop, which allows fix the videoconferencing on the runway.

The right and left fuselages 15, 16 are made according to the standard scheme and are equipped with cockpits, compartments of cryogenic fuel, cryogenic oxidizer, hydrocarbon fuel, and a block of fuel tanks. The compartments of the fuel tank unit 3 (see Fig. 5) communicate with the center wing through hermetically sealed hatches, allowing free movement of the fuel tanks into the center wing 10 and vice versa. In addition, the compartments have hatches with lids in the lower part that perform the role of loading ramps in the open position.

In the nose upper part of the right fuselage 15, a fueling neck is equipped for refueling in flight, and in its lower rear part there is an in-flight refueling bar for VKS.

The fuselages, on the one hand, are docked with the power skeleton of the center section, and on the other hand, with the transition compartments. In the front of the fuselage is equipped with compartments for accommodating the mounting structures of the front landing gear, and in the central part of the compartments for accommodating the mounting structures of the rear main landing gear.

The reusable manned VKS 2 is made according to the "tailless" scheme and includes (see Fig. 9) a wing 65, a fuselage 66, a vertical tail unit 67, a combined propulsion system 68, a three-leg chassis, consisting of a front strut 69 and rear main struts 70 , and other well-known systems and equipment necessary for a safe flight.

The wing 65 of a triangular shape (see Fig. 10) is made up of a center wing, right and left rotary wing consoles 72, 73 with a sweep angle of ~ 30 °. The right and left wing consoles are equipped with elevons 74, 75, which serve as ailerons and elevators. The vertical tail unit 67 is made up of an arrow-shaped rotary keel 76 (see Fig. 9) installed in the rear part of the fuselage 66. The keel 76 is equipped with a rudder 77, which, “splitting” along the trailing edge, serves as an “air brake”.

The combined propulsion system 68 (see FIG. 10) consists of two marching engines 78, two orbital maneuvering engines 79, two atmospheric maneuvering engines 80 and systems necessary for the smooth operation of the ODE. As marching engines 78, two-mode three-component liquid-propellant rocket engines are used, in the first mode up to an altitude of H = 50 ÷ 60 km and M = 9 ÷ 10, 3 components are used - kerosene + liquid oxygen + liquid hydrogen; in the second mode, 2 components are used - liquid oxygen + liquid hydrogen.

As engines of orbital maneuvering 79, two-component liquid-propellant rocket engines operating on liquid oxygen and liquid nitrogen are used.

As engines of atmospheric maneuvering 80, turbofan engines operating on kerosene and atmospheric air are used. Marching engines 78 and orbital maneuvering engines 79 with their own THA, gas generators and start and stop systems are located in the engine compartment (see Fig. 11) located in the rear of the fuselage.

The combustion chamber of each rocket engine is fixed in a biaxial gimbal, which allows you to control the thrust vector in flight.

Engines of atmospheric maneuvering (TRDD) 80 are mounted on pylons of the rear fuselage. To protect the flow part of the turbofan engine from the effects of kinetic pressure and high temperatures during the descent of the VKS from the orbit of the compressor, the compressor is equipped with a protective shield 81 (see Fig. 9) in the form of hydraulically controlled shutters. With idle turbofan engines, the flaps open and overlap the cross section of the air intake.

The fuselage 66 is sealed and equipped with an equipment compartment and an insert cockpit located in the nose of the fuselage, a cargo compartment 82 located in the middle of the fuselage, and a fuel compartment located in the rear of the fuselage. The fuselage is docked with the power frame of the center section 50 and ends with a pressurized frame to which the engine compartment is docked. In the lower front part, the fuselage is equipped with compartments for accommodating the mounting structure of the front landing gear 69 and the front assembly of the VKS hitch-uncoupling unit with the fuel tank block 3. The nose of the fuselage is equipped with a filler neck for refueling with hydrocarbon fuel in flight. In the lower middle part, the fuselage is equipped with compartments for accommodating the mounting structure of the rear main struts of the chassis 70 and the rear VKS hitch-release assembly with the fuel tank block 3. The lower parts of the fuselage and wing form a trough-like shape with the lower front part of the fuselage bent up and with large values of the blunt radii wing socks and fuselage.

This design allows you to make a controlled planning descent VKS from orbit. The outer skin of the VKS has a powerful thermal protection from heat-shielding tiles made of quartz fibers and composite material such as carbon-carbon.

The tricycle retractable landing gear provides landing on an “airplane” on the airfield runway or on the takeoff and landing platform 45 of the carrier aircraft 1 with a minimum relative speed.

The fuel tank unit 3 (see Fig. 12) is made up of a central tank 83 and two side tanks 84. The tanks are arranged in a two-stage “package” scheme with their parallel arrangement and sequential generation of steps, the first stage forming two side fuel tanks 84 and the second stage is the central tank 83.

The system for supplying fuel and oxidizer from the tanks is a displacement system by pressurizing the tanks with neutral gas from cylinders located in the fuel compartment of the air-conditioning system. The Central tank 83 (see Fig. 13) is made according to the load-bearing circuit, which accepts all aerodynamic and weight loads from the VKS 2 and the block of fuel tanks 3, is the only element of the disposable system, because it is separated from the aerospace forces at a speed slightly lower than the orbital one, and is destroyed upon entering the atmosphere.

The Central tank 83 is made up of an elongated power case 85 of rectangular cross section with a smooth shell and an upwardly curved nose portion and a large radius of curvature.

The front power unit 86 is installed on the housing 85, on which the front coupling units are located: 87 - with the VKS, 88 - with the tanks of the first stage, 89 - with the take-off and landing platform 45 and the rear power unit 90, on which the rear coupling units are located -disconnection: 91 - with the VKS, 92 - with the tanks of the first stage, 93 - with the take-off and landing platform 45. The internal layout of the housing 85 contains a compartment for accommodating cryogenic oxygen 94, a compartment for accommodating cryogenic hydrogen 95, a compartment for accommodating instrumentation 96, propulsion compartment and in the separation tank with VCS 97. The outer surface of the compartments 94 and 95 has a heat-insulating coating of steklosot filled with foam.

The side tanks 84 (see Fig. 14) are made in a non-load-bearing pattern consisting of a cylindrical body 98 with a smooth shell, reinforced by the front shell 99, on which the front coupling unit 100 with the central tank 83 and the rear shell 101, on which is located the rear coupling unit 102 with the central tank 83. The head parts of the side tanks are made in the form of resettable spherical fairings 103.

The internal arrangement of the housing 98 contains a compartment for accommodating cryogenic hydrogen 104, a compartment for cryogenic oxygen 105, a compartment for hydrocarbon fuel 106, a compartment for instrumentation 107, a compartment for a parachute system 108, and a compartment for a propulsion system for withdrawing a tank 109 when separated from a central tank 83.

The outer surface of the compartments 104 and 105 has a heat-insulating coating of fiberglass filled with foam.

The functioning of the system during the servicing of space objects in flight conditions at SN.

The system operates as follows. During ground preparation for a flight mission for receiving and servicing, VKS and SN are filled with fuel, oxidizer and other consumable components, the VKS is loaded with an empty fuel tank block, necessary equipment for servicing. Modules of the VKS fixation device are installed on the take-off and landing platform. After takeoff and flight along the route to the point of docking with the orbital plane, telescopic-sliding center-wing flaps open, and the take-off and landing platform with the help of telescopic cylinders of the power frame and its own hydraulic cylinders rises to its highest position and is fixed with mechanical stops. The SN is displayed at a predetermined course, and the videoconferencing system draws closer to the SN using the navigation system, releases landing gear and, with the help of video cameras placed on the take-off and landing platform, occupies the initial position relative to the fixation device modules. Maneuvering the relative speed and height, changing the engine thrust and the position of the aerodynamic control wheels with constant control of the relative position, the VKS makes a planning landing on the takeoff and landing platform with a minimum relative speed, and the VKS, acting on the landing gear wheels on the fixation device modules, thereby makes a mechanical coupling landing gear wheels with a landing platform. VKS engines stop, rotary wing consoles rotate to their highest position, and rotary keel rotates to a horizontal position. The take-off and landing platform lowers to its lowest position, engages with mechanical stops with the center frame power frame. Telescoping-sliding flaps are hermetically sealed, the inner volume of the center wing is inflated with air taken from the second circuit of the dual-circuit engines SU SU, the wings of the fuselage compartments open, communicating the center wing with the fuselage, the wing rotary consoles are in the normal position, maintenance work is carried out on the VKS, on the implementation of which the chassis VKS are released from the fixation device modules, and VKS is moved to the upper position by means of a lifting device. The racks of the VKS chassis are removed, the modules of the locking device are dismantled and transported to the fuselage compartments.

The side and central fuel tanks move to the takeoff and landing platform. The central tank is docked with the takeoff and landing platform, and the side tanks are docked with the central tank. VKS moves to the lower position and joins the central fuel tank. The fuel tanks are refilled with fuel and oxidizer components, and VKS systems with consumable media. A preflight check of VKS systems is carried out, the load-lifting device moves to its highest and rear position, the fuselage compartment doors are hermetically closed, the telescopic-sliding center-wing flaps open, the take-off and landing platform moves to its highest position with mechanical stops with the upper center-frame frame, the rotary keel takes vertical position. At an altitude of H = 8-9 km and a speed of M = 0.65-0.7M SN, the slide is driven, and at the upper point, the central fuel tank is uncoupled and the fuel tank unit with the aerospace system is separated from the SN, with the subsequent launch of the main propelled rocket engine and continued acceleration of the videoconferencing in standalone mode.

The functioning of the system as an accelerating stage of a VKS with a horizontal launch of a VH from a ground aerodrome and an air start of an VKS with a VF is as follows.

During ground preparation for the mission, the SN is loaded with an empty block of fuel tanks, telescopically-sliding center-wing flaps open, and the take-off and landing platform moves to its highest position. VKS with the horizontal position of the keel and the landing gear racks mounted on the take-off and landing platform, which lowers to its lowest position, the telescopic-sliding center-wing flaps are closed. With the help of a lifting device, the VKS moves to the upper position, and the landing gear are retracted. The side and central fuel tanks move to the takeoff and landing platform. The central tank is connected to the takeoff and landing platform, and the side tanks are connected to the central tank. VKS moves to the lower position and joins the central fuel tank. The fuel tanks and VKS systems are refueling from ground sources, and the lifting device moves to the highest and rear positions, preflight preparation of the VKS is performed.

After the takeoff of the SN and flight along the route to the launch site of the VKS, the wings of the fuselage compartments are hermetically closed, and the telescopic-sliding wings open, the take-off and landing platform moves to its highest position, the rotary keel of the VKS occupies a vertical position.

SN at an altitude of 8-9 km and a speed of V = 0.65-0.7 M performs a slide and at the upper point, the central fuel tank is uncoupled and the fuel tank unit with VKS is separated from the SN, with the subsequent launch of the VKS marching rocket engines and its continuation overclocking offline. CH returns to the airfield.

This embodiment of the method of servicing space objects and a reusable aerospace system allows, by re-launching the aerospace system without landing on the ground and servicing it on board the SN, to increase the efficiency of the system, reduce the cost of shipping space objects, and effectively collect and dispose of spent objects.

Claims (4)

1. A method of servicing space objects using an aerospace system, including a transport carrier aircraft and a reusable orbiting aerospace aircraft, comprising preparing the system for flight with the installation of an aerospace aircraft on a carrier aircraft, take-off, delivery of an aerospace aircraft to the desired location, take-off of the aerospace aircraft from the carrier aircraft, exit to orbit, orbital flight, descent from orbit, controlled descent in the atmosphere, landing on the carrier aircraft, and ground landing of the carrier aircraft, characterized in that the delivery of the aerospace aircraft to the desired location is carried out in the maintenance compartment of the carrier aircraft, at the starting point, the aerospace aircraft is moved to the take-off and landing site and take off, and after landing and fixing, airborne -Space aircraft it is placed in the maintenance compartment of the carrier aircraft, provide service, and then carry out the subsequent launch of the aerospace aircraft into orbit itu. 2. A reusable aerospace system for servicing space objects comprising a transport carrier aircraft made with a wing containing a center section and arrow-shaped consoles, and a reusable return orbital aerospace aircraft made with a wing containing a center-section and arrow-shaped consoles, and a vertical tail feathering, while the center section of the carrier aircraft is made with a take-off and landing platform on its upper surface, equipped with docking nodes of the aerospace aircraft a carrier aircraft, and the system is equipped with means to ensure landing of an aerospace aircraft, characterized in that the carrier aircraft is made with a wing center section containing an internal maintenance compartment made with dimensions sufficient to accommodate an aerospace aircraft made with folding wing consoles and vertical tail, and is equipped with means for moving an aerospace plane into the compartment. 3. The reusable aerospace system for servicing space objects according to claim 2, characterized in that the maintenance compartment is made with a hatch on the upper surface of the center section over the entire dimension of the compartment, closed by two-sided retractable telescopic shutters, and is equipped with a take-off and landing platform extended to the level of the upper surface of the center section during landing-take-off of an aerospace aircraft. 4. A reusable aerospace system for servicing space objects according to claim 2 or 3, characterized in that the take-off and landing platform consists of a power frame of the platform moving along the guides with the help of crawlers and double-acting telescopic hydraulic cylinders rigidly connected to the lower power frame compartment, the platform’s power frame and the platform itself, moving with the help of telescopic double-acting hydraulic cylinders rigidly connected to the power frame, while the platform has a landing places with fixation devices for aerospace aircraft, and wedge stops restricting the movement of the platform in the longitudinal and transverse directions in extreme positions.

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