RU2831436C1 - Single-stage, annular, reusable lv for launching payload into space - Google Patents

Abstract

FIELD: cosmonautics.

SUBSTANCE: invention relates to means of launching a payload into space. Annular reusable launch vehicle (LV) contains landing supports, grid rudders, annular frame made of vertical rods with bent upper part and stiffness rings. To the lower stiffness ring of the LV, a power frame unit of the launching unit of the turbojet engine with a common fuel tank coated with a fire-retardant composition is attached by means of pylons. In the upper sealed compartment of the common fuel tank there is a parachute. Front surfaces of LV and stiffness rings are coated with ceramic fire protection. Inside each of the head parts of the annular assembly of the LV there are inhabited modules for the crew, connected by transient vestibules with the annular sluice placed inside the upper stiffness ring, having transition chambers with docking assemblies located in the rear part of each habitable module.

EFFECT: possibility is achieved by means of one annular arrangement to put an annular manned space station into orbit, as well as to create artificial gravity inside the space station.

7 cl, 4 dwg

Description

The invention relates to aerospace vehicles and flight methods using direct-flow ejector thrust of these vehicles.

An analogue of the proposed technical solution may be the patent of the Russian Federation RU 218184 C "Straight-through ejector rocket launcher" by the author N.V. Zemlyakov. The analogue pertains to the field of tactical jet munitions. The straight-through ejector rocket launcher contains a central rocket with control means, around which a tubular afterburning chamber is placed on pylons in the tail section. Peripheral rockets are placed along the inner perimeter of the chamber, forming a tubular cavity, on the heads of which a hollow annular cone is installed, connected by one diameter of the outer and inner rings. The inner ring is connected by the upper pylons to the central rocket, the tail section of which is placed in the mounting socket connected to the lower pylons. The inner ring is made in the form of a confuser, a narrow neck and a conical diffuser, successively and smoothly connected to each other. With equal diameters of the missile bodies, the number of peripheral missiles is from 7 to 25, and the ratio of the diameter of the straight-through channel to the diameter of the central missile is from 1.2 to 6.4. The invention allows to reduce the aerodynamic drag of the launch vehicle at supersonic flight speeds and to increase its speed. The invention - an analogue, as well as the proposed technical solution, uses ejection occurring in the ring assembly to accelerate the ring assembly of tactical missiles. In the proposed analogue, according to the Russian Federation patent RU 218185 C, the possibilities of ejection and its properties for launching a payload into orbit are not used and are not fully disclosed.

An analogue of the proposed technical solution may be the patent of the Russian Federation RU 02053168 C "Reusable Rocket Block" by V.P. Mishin. The invention relates to the field of rocket technology, namely to reusable rocket blocks, in particular to blocks of the first stages of reusable "earth-orbit" space transport systems, and can be used for launch vehicles of almost any class, but the use of this invention is especially effective for reusable launch vehicles implementing programs for the injection of large "earth-orbit" cargo flows. The technical task of the invention is to create a reusable rocket block capable of returning significant distances to the launch site and performing a vertical landing on a small-sized site. The proposed technical solution allows for a stable and controlled flight of the rocket block in supersonic and subsonic flight modes, returning to the launch site area and landing at a low horizontal and vertical speed on a site of limited size. The reusable rocket unit comprises a body with fuel tanks, a rocket propulsion system, aerodynamic surfaces, turbojet engines (TRE), and a landing device. The unit has a combined arrangement of TREs by placing them in the nose section of the unit (cruisers) and in the area of the center of mass (landing) with an offset towards the stern section relative to the center of mass. The TREs are equipped with devices for controlling the position of the thrust vector in space. The axes of the cruising TREs are installed in the direction of the longitudinal axis of the unit, the axes of the landing TREs are installed in the direction close to the transverse axis of the unit. The aerodynamic surfaces are designed as monoplane consoles located in the area of the center of mass and stabilizers in the stern section. The stabilizers are designed as folding lattice panels equipped with turning devices. Each of the stabilizer panels is designed in such a way that in the folded position it follows the shape of the surface of the stern section of the unit. The landing device is made in the form of a single-strut retractable ski with a shock absorber in the aft part of the block. Two retractable parking supports are installed on the monoplane consoles symmetrically relative to the longitudinal axis of the block, and a retractable support for the rotary nozzles is installed in the nose part of the block. The contact surface of the ski has a friction coating and a strut with a shock absorber. The landing turbojet engines are located inside the monoplane consoles. The analogue assumes a short-term stay in space, does not have a device that creates artificial gravity inside the habitable compartment, and does not have an acceptable internal volume for a long-term stay of a crew of more than 10 cosmonauts.

The prototype for the proposed technical solution of the proposed invention: “Annular, reusable launch vehicle for launching a payload into space” (ARLV) is the “Method for launching a payload into orbit and a reusable ejector stage of a launch vehicle for its implementation” (ESRV) according to Russian patent No. 2734965. The prototype in relation to the proposed technical solution is the main invention, in the composition of all its features and contains: annular landing supports of the booster stages of the launch vehicle and maneuvering rocket engines (RM) installed under the head fairings of these stages, as well as lattice rudders on the RM stages, wherein the annular frame is made of vertical rods, the number of which is equal to the number of booster stages of the launch vehicle, with a curved outer part and stiffening rings, wherein the curved parts of the rods are inserted inside the head fairings as their supporting frame, and the fairings have bevels in the direction of the central axis of the launch vehicle ES, wherein the nozzles of the cruise RMs are directed at a small angle away from the vertical axis of the ESRN, the annular landing supports are made in the form of vertically located rings of fire-resistant metal, covered with a fire-protective ceramic coating, with a diameter greater than the diameter of the launch vehicle stages, and with a support edge along the lower cut of spread apart wavy teeth, with vertical cutouts made in the side walls of the annular supports, and the supports are attached to the disc-shaped thrust bearings using rods made of fire-resistant metal, and containers with fire-resistant energy-absorbing material are installed with compression between the disc-shaped thrust bearings and the bottom of the booster stage of the launch vehicle, which make it possible to vertically move the thrust bearings relative to the bottom of the stage, while the ejectable joint assemblies of the ES with the upper stage of the launch vehicle are attached to the upper stiffening ring of the annular frame with an equal pitch, and the rods of the launch supports, which have horizontal contact surfaces with the launch pad, are attached to the lower stiffening ring as continuations of the vertical rods.

The prototype does not provide for the launch of a payload into orbit using an annular rocket stage or a single LV. It does not provide for the activation of a vertical air flow through a channel formed by the annular assembly of the URM of the Angara type. Somehow it is implemented in the technical solution of the proposed invention using a parachuted, no less than 15-25 seconds immediately after the fuel has been exhausted, separate launch block of the turbojet engine. There is no annular airlock for moving astronauts and cargo through the habitable compartments, nor are the habitable compartments themselves, which in the prototype were launched into space using the second stage. The prototype does not provide for emergency undocking and landing of each of the habitable compartments, as well as undocking from the frame with stiffening rings, part of the symmetrically located blocks of the URM of the Angara type, after the fuel has been exhausted in them. The prototype did not use ceramic fire protection, because its technical solution did not provide for the launch into space and entry into the dense layers of the atmosphere at the first cosmic velocity of the entire ESRN (ejector stage of the launch vehicle) ring assembly for the purpose of soft landing, including on an unprepared site, which is provided for in the prototype. The prototype does not provide for the creation of acceptable artificial gravity after the launch of the reusable launch vehicle ring assembly into orbit. The second stage of the prototype is located above the ESRN, in the line of air drawn into the rocket engine ring assembly and creates additional aerodynamic resistance, which does not allow the full implementation of the capabilities of the ejection of the launch vehicle booster ring assembly for the purpose of launching the payload into orbit.

The technical result of the proposed invention, "Annular, reusable launch vehicle for launching payloads into space" (ARLV), is the ability to launch an annular habitable space station into orbit using a single annular arrangement, the habitable modules of which are connected by an inhabited annular gateway for the movement of cargo and astronauts, and also to create acceptable artificial gravity inside the space station using maneuvering engines.

The technical result is achieved by using a turbojet engine launch unit, which is connected to the lower rigidity belt and the KMRN frame according to the main invention using a power frame unit and pylons with pyropatrons and is equipped with a parachute system triggered at 15-25 seconds of the RN flight, as well as the ability of a part of the symmetrically located UMRs, like the "Angara", to undock from the ring frame assembly at an altitude of 80-120 km using pyropatrons, after the fuel in them runs out, while all the main parts, elements and units of non-heat-stressed structures, unlike the main invention, are made of carbon fiber, and heat-stressed ones are covered with ceramic heat-protective tiles.

Fig. 1 shows the "Ring-shaped, reusable launch vehicle for launching a payload into space" with the turbojet engine launch assembly shown in Fig. 1 in dashed-dotted lines. Fig. 2 shows the same top view of the turbojet engine launch unit and its connecting links with the main frame of the KMRN. Fig. 3 shows the units and parts of the habitable module. Fig. 4 shows the KMRN launch into a suborbital trajectory.

“Annular, reusable launch vehicle for launching a payload into space” item 26 (Fig. 1), in the lower central part contains a power frame unit 1 to which the turbojet engine launch unit is rigidly attached, item 2 Fig. 1,2, along the vertical axis of which, in the upper part, using rigid connections 3, a fuel tank 4 is attached, in the upper part of which a sealed compartment covered with fire protection with a landing parachute 5, the launch unit of the turbojet engine 2 is located. The power frame unit 1, with the launch unit of the turbojet engine 2, is connected at least at four points to the inner part of the lower stiffening ring 6 and vertical rods 7, using connecting pylons 8, destroyed by pyropatrons 9. The volume of the fuel tank 4 is designed for the operation of all turbojet engines of the power frame unit 1, in a forced mode for at least 15-25 sec., and the release of the parachute from the upper sealed compartment 5, the common fuel tank 4, covered with fire protection, occurs at least 5 sec after the jettisoning of the power frame unit 1, the launch assembly of the turbojet engine 2, from the vertical frame rods 7. Destruction of connecting pylons 8, from the impact of pyropatrons 9 and the ejection of the power frame unit 1, with the starting block of the turbojet engine 2, from the vertical rods of the KMRN frame 7, occurs vertically downwards, after cutting off the fuel supply to all turbojet engines, power frame unit 1, with a minimum fuel reserve in the tank. Inside the middle stiffening ring 10, along the circumference and the center of mass of the URM blocks (universal rocket modules of the Angara hangar type 11, with the remains of fuel for landing, maneuvering rocket engines with a controlled low-thrust vector 12 are placed. In each of the head parts of the blocks, similar to the URM "Angara" 11, habitable modules 13 are equipped, connected by transitional sealed vestibules 14, with a sealed annular gateway 15, for moving astronauts and cargo between the habitable modules 13. The sealed annular gateway 15 is located in the inner space of the upper stiffening ring 16. The URM blocks of the Angara 11 type, suspended on the vertical rods of the frame 7, and the rods of the frame 7 themselves, are made of carbon fiber, of the "black wing" type, due to which the mass of the URM blocks 11 is lightened, and the amount of fuel in them increases. Including, the main part of non-heat-loaded elements and units located inside the KMRN, pos. 26 Fig. 1, is made of high-strength carbon fiber. Heat-loaded elements: head parts of the Angara-type blocks 11, frontal surfaces: upper 16, middle 10 and lower 6, stiffening rings are covered with ceramic fire-protective tiles 17. Pyrocartridges 18 are installed between the living compartment 13 and the curved part 27, vertical rods of the frame 7 and are intended for emergency undocking, if necessary, of each living module 13 from the KMRN. Fig. 3 Lattice rudders with drive mechanisms 20 are located above the upper end of the URM block 11. Emergency landing parachute 21 of habitable modules 13 and soft landing PRD 22 are installed in each habitable module 13. For moving cosmonauts and cargo inside the annular gateway 15, an annular, cable conveyor 23 is mounted. In each habitable compartment 13, digital screens-portholes 24 are installed, with an online image of non-rotating views of the Earth and stars of the Universe from the habitable modules 13 of the KMRN. The lower and upper pyropatrons 25 are installed at the junction of the URM block 11 with the lower ring 6 and the upper ring 16, stiffness and vertical rods of the frame 7, and are intended for detaching, if necessary and after the fuel has been spent, each URM block of the Angara type 11. (Fig. 3) The splashdown of the spent URM blocks 11 of the Angara type, in order to preserve the RD, Fig. 4, occurs with the warheads forward, the orientation in this case is provided by the landing ring supports (pos. 12 of Fig. 1 main element), ensuring the safety of the starting blocks of the TRD 2. Fig. 1 Known attachment points 28, with the URM blocks 11 of the Angara type, to the rods of the vertical frame 7, are installed in the area of the upper 16 and lower 6 stiffness rings. The docking unit 29, with the airlock 30 and the entrance hatch to the habitable module 31, is located at the rear of the habitable module 13. The automatic artificial gravity control system is mounted in the command habitable module 13 and sets the required rotation of the CMRN and the orientation of its axis by sending commands to the low-thrust shunting RDs, which process abnormal gravitational deviations that affect the crew's performance and life activities. The general assembly of the "Ring-shaped, reusable LV" is shown in Fig. 1, pos. 26.

The launch, flight, entry into orbit, flight in orbit, deorbiting and soft landing of the “Ring-shaped, reusable launch vehicle for launching payloads into orbit” (RHPR) occurs as follows.

In the KMRN prepared for launch, the engines of the TRD 2 launch block are started, warmed up and brought to afterburner. Simultaneous operation of all engines of the TRD 2 launch block causes movement and capture of air mass in the vertical channel between the URM 11 blocks, its pumping from the upper hemisphere above the launch vehicle ring assembly downwards into the channel for removing gases from the operation of the TRD launch block. After the launch block of the TRD has achieved stable operation in afterburner mode and the total weight of the launch vehicle has been reduced by the value of the thrust force of the launch assembly of the TRD 2, all KMRN RDs are started and brought to maximum thrust. In this case, air is captured by the RDs of the KMRN ring assembly, previously accelerated to supersonic speeds by the TRD launch assembly, pos. 2, Fig. 1. Above the launch site of the ring KMRN, pos. 26, Fig. 1, a local area of supersonic low-pressure air flow is formed and continuously maintained. Atmospheric air enters the vertical annular channel between the URM 11 blocks and, during the first seconds of the KMRN launch and ascent, enters the jam of the rocket jets from the operation of the KMRN RDs located along the ring and into them, is additionally accelerated by the action of friction against the rocket jets and expands from their high temperature. Under the action of the vacuum (implosion) arising in front of the frontal surface of the jointly operating TJD and RD, which is continuously maintained by the RD and TJD, the operation of the "open thermal rocket engine (OTRE)" is activated under the starting KMRN, based on the difference in atmospheric air pressure above and below the KMRN.

The open thermal rocket engine uses the air pumped by the RD into the jam of the rocket jets as a working fluid. With the continuing standard acceleration of the KMRN, under the influence of the OTRD, the fuel consumption of the RD decreases, while the EKRN continues to gain speed and altitude in a standard manner. After gaining an altitude of (5-10) km and working off the fuel in the engines of the launch assembly of the TRD, pos. 2 Fig. 1, 3, the pyropatrons 9 are triggered, the launch block of the TRD 2 is ejected, and the joints of the pylons 8 with the vertical rods of the KMRN frame 7 are destroyed. The launch assembly of the turbojet engine 2 lands on a parachute 5. To put massive loads into orbit, part of the URM 11, placed symmetrically on the vertical rods of the frame 7, are switched to the afterburner mode at the start and after the fuel in them runs out, they are fired off on command using pyropatrons 25. The aerodynamic perfection of the annular assembly of the URM of the Angara type, when gaining speed at altitudes from (0-100) km to the first cosmic is maintained at the level of known, sequentially located stages of the LV and possibly exceeds it. The reason is obvious and lies in the fact that in the frontal volume of the KMRN, a local core of compacted atmospheric air is not formed. During the flight, the KMRN rocket engines continuously throw air particles from the front hemisphere through a cylindrical channel formed by the vertical rods 7 and the housings of the blocks of the URM 11 type, into the rear hemisphere of the KMRN. The atmospheric resistance to the motion of the KMRN rocket from the Earth to orbit is minimal and critical heating of the frontal surfaces of the KMRN during flight to near-Earth orbit is unlikely. If the function of the propulsion in the water and air environment is performed by screws, water jet pumps, turbojet compressor blades, fuel combustion in the pinched working chambers of ramjet engines, then, in an open thermal rocket engine (OTRE), the function of the working chambers is performed by supersonic high-temperature jets from the operation of the RD, located along the circumference, with high-temperature heating and the formation of a pinched superheated air of the atmosphere, throwing it back with the formation of additional reactive force. During acceleration in the Earth's atmosphere, the KMRN continuously forms, maintains and moves with acceleration into the rear hemisphere, a core of superheated atmospheric air, which with its pressure acts both on the rocket jets and through them on the bottom of the RD chambers, and on the rear projections of the KMRN.

After the KMRN enters orbit, the crew depressurizes the transition vestibules 14 and combines the volumes of the living compartments 13 using the annular airlock 15. They turn on the low-thrust maneuvering engines 12 and impart rotation to the vertical rods of the frame 7 and through it the KMRN 26 around the central axis, causing acceptable artificial gravity. To compensate for the physiological reaction of the astronauts to the effect of the KMRN rotation around its axis, the crew turns on digital screens 24 with a non-rotating view of the Earth and the stars of space on the porthole screens from television cameras 32 located outside and in the center of the porthole. Each habitable module has its own functional purpose. For example, a command module, a dining module, a medical module, a personal hygiene module, a module for rest and physical exercise, modules for conducting experiments and other modules for performing the main mission of the annular KMRN. For orientation of the KMRN rotation axis in space, an automatic artificial gravity control system 32 is provided. The main purpose of the artificial gravity control system is to compensate for gravitational nonlinear effects on the KMRN crew. The system automatically counteracts deviation of the KMRN rotation axis from the standard one by operating the shunting RDs with a controlled thrust vector 12 installed in the middle stiffening ring 10. In the event of an emergency in any of the habitable modules 13, the automation warns the crew, activates the undocking system of the emergency habitable module 13 and its separation from the KMRN with subsequent entry into the dense layers of the atmosphere and soft landing using parachutes 20 and PRD 21. The KMRN provides for the docking of cargo spacecraft to the docking unit 29 and through the airlock 30 and the entrance hatch to the habitable compartment 31, it is possible to deliver cargo and replace the crew. In case of normal operation of the KMRN and the execution of the space flight mission, the crew, using the shunting RDs 12, deploys the KMRN, brakes the main RDs and directs the KMRN using automation or independently to the landing point. At the same time, in cases of unforeseen circumstances, the KMRN can land on an unprepared flat surface, the angle of inclination of the landing site should not exceed 10-15 degrees. The ring assembly of habitable modules 13, the URM blocks of the Angara type 11, are removed from the vertical rods of the ring frame 7, using a lifting mechanism and together with the empty ring frame 7, are taken to the refueling site and the next launch.

The economic efficiency of using the KMRN could amount to hundreds of billions of rubles and would allow the Russian cosmonautics to return to the forefront in the shortest possible time, a level unattainable for competitors.

TERMS

1. Power frame unit.

2. Launch block of the turbojet engine.

3. Rigid connections to the fuel tank.

4. Fuel tank.

5. The landing parachute of the turbojet engine assembly, located in the compartment of the head part of the fuel tank. Fig. 1.

6. Lower stiffening ring of the KMRN frame. Fig. 1.

7. Vertical rods of the KMRN frame. Fig. 1.

8. Connecting pylons.

9. Pyrocartridges for ejecting the TRD launcher block.

10. Middle stiffening ring of the KMRN frame. Fig. 1.

11. The URM block of the Angara type. Fig. 1.

12. Maneuvering rocket engines with controlled thrust vector. Fig. 1.

13. Habitable modules.

14. Sealed transition vestibule.

15. Ring lock. Fig. 1.

16. Upper stiffening ring. Fig. 2.

17 Ceramic fire-protective tile coating. Fig. 1.

18. Pyrocartridges for ejection of the habitable compartment.

19. Connection of the habitable compartment with the upper part of the URM. Fig. 1.

20. Lattice rudders of the landing system with drives. Fig. 1.

21. Emergency parachutes of habitable modules. Fig. 1.

22. Blocks of emergency landing PRD of habitable modules. Fig. 1.

23. Cable conveyor mounted in a ring lock. Fig. 1.

24. Digital screens of virtual reality (portholes). Fig. 1.

25. Pyrocartridges for firing the URM of the Angara type. Fig. 1,3.

26. KMRN - annular, reusable launch vehicle. Fig. 1,3.

27. Curved detachable ends of vertical rods. Fig. 3.

28. Angara URM attachment points to the vertical frame rods. Fig. 3.

29. Docking unit. Fig. 3.

30. Transitional airlock chamber. Fig. 3.

31. Entrance hatch to the living compartment. Fig. 3.

32. Automatic control system of artificial gravity. Fig. 3.

33. Television cameras of virtual screens-portholes.

Claims (7)

1. An annular, reusable launch vehicle for launching a payload into space, comprising: landing supports for the universal rocket modules of the launch vehicle (URM) of the Angara type, lattice control surfaces, an annular frame made of vertical rods with a curved upper part and stiffening rings, characterized in that a power frame unit of the turbojet engine launch unit with a common fuel tank coated with a fire-retardant composition and carried out on rigid ties vertically upward above the power frame unit of the launch unit with the turbojet assembly is attached to the lower part of the annular volume along the launch vehicle axis, with the possibility of being shot vertically downwards, to the lower stiffening ring of the launch vehicle by means of pylons, wherein a parachute is placed in the upper sealed compartment of the common fuel tank, and the frontal surfaces of the launch vehicle nose cones and stiffening rings are covered with ceramic fire protection, inside each of the nose cones of the annular assembly of the launch vehicle, above the URM-type blocks, The habitable modules for the crew are located, connected by transition vestibules with a ring gateway located inside the upper rigid ring, having transition chambers with docking units located in the rear part of each habitable module, and an automatic artificial gravity control system. 2. An annular, reusable launch vehicle according to paragraph 1, characterized in that part of the non-heat-loaded elements and units of the launch vehicle are made of high-strength carbon fiber, and its power frame unit of the launch block is connected at no less than four points to the inner part of the lower stiffening ring and vertical rods of the launch vehicle frame using connecting pylons that are destroyed by pyropatrons. 3. An annular, reusable launch vehicle according to paragraph 1, characterized in that the volume of the common fuel tank is designed for the operation of all turbojet engines of the launch unit's power frame assembly in a forced mode for at least 25 seconds, and the release of the parachute from the upper sealed compartment of the common fuel tank occurs at least 5 seconds after the vertical downward firing of the launch unit's power frame assembly with the turbojet engine and the common fuel tank from the launch vehicle's lower stiffening ring. 4. An annular, reusable launch vehicle according to paragraph 1, characterized in that maneuvering rocket engines with a controlled low-thrust vector are placed inside the middle rigidity ring of the launch vehicle, along the circumference and center of mass of the URM blocks of the Angara type, with the remainder of the fuel launched into orbit for landing. 5. An annular, reusable launch vehicle according to paragraph 1, characterized in that each habitable compartment is equipped with digital screens-portholes with a non-rotating view of the Earth and the stars of the Universe from space, the television cameras of which operate according to a program and are located outside the habitable modules. 6. An annular, reusable launch vehicle according to paragraph 1, characterized in that the pyropatrons for undocking the habitable modules are placed between the curved parts of the vertical rods and the body of the habitable modules, while emergency parachutes and PRD units for soft landing are placed inside each habitable module of the launch vehicle. 7. An annular, reusable launch vehicle according to item 1, characterized in that for symmetrical detachment of the URM blocks from the launch vehicle supporting frame, the lower and upper pyropatrons are installed at the junction of the URM blocks with its lower and upper stiffening ring.

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