SU580696A1 - Reusable aircraft system - Google Patents

Abstract

MULTI-PROPOSAL AIR-SPACE SYSTEM, containing first and second stages and transport spacecraft, equipped with main and auxiliary propulsion systems, control systems, aerodynamic surfaces and air rudders for stabilization and control in the atmosphere, crew cabins, chassis and flaps, t It is obvious that, in order to improve the aerodynamic, flight-tactical and operational characteristics, the stages of the reusable space system and the transport and space The device is made in the form of a half-disk and a disk, respectively, with the upper flat surface of the first-wing casing joined to the lower flat surface of the second-wing casing, and the transport spacecraft is installed in the center of the second-wing casing on the discharged suspended from it fuel tanks, which are installed on a sliding platform, the surface of which is identical to the upper outer contour of the wing-wing of the second stage "2. The system in accordance with clause 1, that is, with the fact that, in the cases of the steps and the spacecraft, there are cuts in which the main engines are installed, while the output sections of the nozzles of the main engines of the first and second steps and auxiliary engines of the second stage are profiled with an oblique cut along the external surfaces of the steps-. 'WEL00 OU th iUtrArIt refers to aerospace engineering, in particular to aerospace systems (aerospace systems) ^. and is intended for launching space objects (payloads) of various purposes into the reference near-earth orbit, as well as returning space objects from the orbit to the Earth with the help of a spacecraft transport, which is part of a reusable aerospace system (MVKS) „Martin's Astrorocket project is known

Description

358 lotted). Both stages of the aircraft scheme, of which the first stage has a wing installed above the Fusell (high-profile scheme), the upper surface of the wing and the body of the first stage are flat, the lower surface of the wings is profiled, and at the ends of the wing the keels with steering wheels are installed (the keels are directed down from the surface of the wing) in the salvage of the first stage hull (fuselage) there is an engine installation, which consists of the main engine - LRE with an axisymmetric nozzle and auxiliary TRL engines, designed to return Penetration and landing of the turbofan engines are located on pylons on both sides of the fuselage. The second stage has a wing installed under the fuselage (low-wing type scheme), the lower surface of the wing and the second stage body are flat, which allows docking of the stages in a horizontal position, top The wing's surface is shaped: on the ends of the wing, the keels are installed with a turning circle (or directed upwards from the surface of the wing); In the rear part of the second stage casing there is an engine installation, which consists of the main engine -) RD and auxiliary engines - TRD, which are located at the junction of the wing and fusher, above. In the front part of the hull of both stages, there are cabins for crews. For landing steps and taxiing serve chassis retractable in the fuselage. For pitch control. and roll in dense layers of the atmosphere when returning and landing steps on both of their steps there are elevons. Assembly and installation of the system is done in a horizontal position, then it is towed to the starting position, set vertically, refuel, check and. start with the drawbacks of the structural layout of such a system: the first stage structural layout with lower hull and keel location will result in the need to land at low angles of attack and, therefore, at high speeds, which will significantly complicate operation and reduce the likelihood of a trouble-free landing. ; -for this structural layout of both stages of the chassis have a small base, which will lead to yawing of the steps on the landing, and, possibly, increasing the size of the chassis | or their bases are limited both by the volume of the hull I and the small thickness of the wing, which also significantly complicates the operation and reduces the likelihood of a trouble-free landing; - a structural-layout v scheme with sequential operation of the steps will lead to the fact that, firstly, at the first stage of acceleration, the aerodynamic resistance will additionally increase due to the bottom resistance of the tail section of the second stage, where the main engine, the rocket engine, is installed will work until the steps are separated; secondly, the sequential operation of the stages and, accordingly, the sequential development of fuel from the tanks of the stages will reduce the energy efficiency; thirdly, the two-stage LKS scheme with sequential operation of the steps, where the second stage is also orbital, will result in the orbit being transported the weight of the structure as ballast, which will significantly reduce the maneuverability of the orbital stage both in near-earth space and when going out of orbit for returning to Earth and landing; -the difficulty of working out for the first stage of the main multi-chamber URD of a large pull rod, the nozzle of which has a central body; - for a vertical start such an ACS requires a large amount of labor, which, in turn, requires powerful rocket engines for multiple use, a complex and expensive starting complex. The Space Shuttle project is a friend and friend of the reusable transport space system (MKTS). including two high-power rocket (solid fuel) units, and a second stage, including a fuel and oxidizer tank and an orbital stage (transport ship), whose main engines operate on it fuel from the moment of launch to the launch of the transport ship into orbit; the large fuel tank (for storing liquid hydrogen and oxygen), after separation from the orbital stage, enters the dense layers of the atmosphere and erasheth. Solid fuel blocks fixed to the central fuel tank symmetrically on both sides, after the completion of work are dropped and descend on parachutes into the ocean, where they are picked up and towed by ships. The transport ship (orbital stage) is installed on the upper surface of the aft central tank. The propulsion system of the transport ship, in addition to the cruising LRE, also includes a liquid propellant for maneuvering in space and an stabilization engine and two solid propellant engines for emergency rescue of the crew at the start and in the active section trajectory withdrawal. The transport ship has a low wing of small elongation, deltoid in plan. The control system is located on board the transport ship, and the pitch, roll and yaw control of the fITKC at the active withdrawal site is carried out using the transport ship installed in the CGD suspension. To control the transport ship in dense layers of the atmosphere, the elevons and yaw are used to control the transport ship in dense layers of the atmosphere. keel with steering wheel. A crew cabin is located in the front part of the transport ship's hull, between the cockpit and the keel on the upper surface of the hull there is a payload compartment. For landing the transport ship there is a three-support chassis. This system is the most: close to; proposed by the technical essence and the achieved result. The disadvantages of the structural layout of the system are: - the use of solid-fuel engines at the first stage facilitates the task of saving spent blocks in the ocean, however, this reduces the momentum of the propulsion system and the energy efficiency of the system; - the complexity of the search and rescue of solid fuel blocks in the ocean in complex conditions (fog, snowfall, storm, etc.); - MTKS starts can be made only in a limited range of azimuth start; , since the central fuel tank in flight is loaded with large concentrations of 6 dosed forces (force of heavy power rocket solid propellant engines, mass inertial loads, etc.), then powerful enough power elements will also be included in the design scheme of the tank: the likelihood of combustion which, together with the shell of the tank at the entrance to the dense layers of the atmosphere, is small and, therefore, it is possible that the remains of the unburnt structure of the power elements fall to the Earth, which represents a serious danger; - due to the large size and weight of the design of solid-fuel engines and the central, fuel tank, it is difficult to transport them to the landfill from factories and todo; —for vertical start-up such an MKTS requires a great deal of laboriousness, which requires the development of powerful rocket engines and the creation of a complex, cumbersome and expensive starting complex, which increases the development costs and development time; - the difficulty of obtaining for the adopted layout of a transport ship of high aerodynamic quality at hypersonic flight speeds (to 1, .5-1.5) will result in the transport ship having a limited aerodynamic maneuver and will not be able to descend from any orbit with landing on its territory; - The prototype MTKS is not fully reusable, it is partially partial, for example, a central large-sized disposable fuel tank, and solid fuel blocks also have a limited resource (pip 10-15), which increases the cost of operating the system and complicates operation; “The prototype MTKS reflects the concept of minimal technical and financial risk at this stage and does not have a satisfactory constructive continuity considering the future development of aviation and space technology. The purpose of this invention is to eliminate these drawbacks and improve the aerodynamic, flight performance of the TKS. This goal is achieved by the fact that the steps of the reusable aerospace system and TKK are made 75 in the form of half-disks and a disk, respectively, while the upper flat surface of the first-wing wing casing is joined to the lower flat surface of the second-wing wing-casing, and the wings of the second stage are suspended to him discharged fuel tanks, which are mounted on a sliding-plate form, the surface of which is identical to the upper outer contour of the wing of the second stage And in the body TAC steps and cutouts, which are installed in the main engines and the output section of the nozzle main engines. the first and second stages and the auxiliary engines of the second stage are profiled with an oblique cut along the external surfaces of the stages. Fig. 1 schematically shows the proposed aerospace system, a general view; in fig. 2 - the same top view; Fig. 3 is the same, view from below; in fig. - the same, side view; in fig. 5 - the same, front view. FIGS B shows a constructive-loop scheme of first-stage arrangements with a transport spacecraft; in Figs 7 is a section along the AL on fig 6; in fig. B — node I in FIG. 7 in FIG. 9 is a section along BB in FIG. 6 “FIG. 10 shows a constructive-force scheme for arrangements of the second stage with a transport spacecraft; in fig. 11 is a section along BB in FIG. ten; in Fig „12 - a section along G-D on figo 11 o. The reusable aerospace system (MVCS) shown in FIG. 1-12 includes the first stage 1, the second stage 2 and the transport spacecraft (TKK) 3, both stations and the reusable space TKK. The body (phgozel :) and the wing of the steps and the TKK in a structurally-integrated plan are organically a single whole body-shell, the profile of which is a half-disk for the steps and a disk for the TKK. Both planes and TKK in the plan represent a circle (or ellipse), First Stage 1 has a flat upper surface. (FIG 5), with which the bottom surface 5 of the second stage 2 is joined; the docking of steps and their centering is carried out using unified docking stations and centering elements 6 (Fig. 6). The transport spacecraft 3 is installed in the center of the second stage 2 and fixed with torus fuel tanks, which are themselves installed on the sliding profiled platform 7 second steps (figo 12). In extended position. platform 7 forms from above a smooth outer contour of the layout of the second stage | (| after separating from it mcc) „R the compartment 8 is located in the center of the TKK for the payload (Fig. 1l) o Two kilo are installed and spaced symmetrically relative to the longitudinal axis of the first stage 1 9 with steering wheels 10; respectively, on the upper surface of the second stage 2, keels 11 with steering wheels 12 are installed and separated (symmetrically to the first stage kil); in the TKK, the keels 13 with the turn wheels 1f are also spaced symmetrically relative to the longitudinal axis and mounted on the upper surface (FIG. O O. The aerodynamic surfaces 15, 16, 17 serve as a continuation of the keels on the first and second steps and TKK; As a result, over the greater part of the wing-hull area (both in the MVKS assembly and in individual elements), bounded above by kili with aerodynamic surfaces, the lateral overflow of air jets will be significantly reduced, which will lead to a decrease in drag and, in particular, on the component is inductive resistance, and also will lead to an increase in the number M (length of flight) about the front of both stages and the TAC on the upper and lower surfaces of the wing body are double-sided elevators 18,19,20 and, respectively, double-sided ailerons 21 , 22,23 (i.e., the rudders and ailerons located on the upper surface of the wing hull deviate only upwards, and those located on the lower surface only (down), the rudders and ailerons are spaced symmetrically relative to the longitudinal axis (Fig. 2.3) About Both stages and the trans-port spacecraft manned The first-stage crew cabin 24 and the TAC space cabin 25 are located along the longitudinal axis and do not extend beyond the contours of the wing-wing body, respectively, of the first stage and TAC. The cabin 26 of the crew of the second stage for the best, review in flight and especially on takeoff and landing brought forward; For the same purpose, first-stage crew cabins and TACs can be deflected downwards. First, second-stage cabins and TKKs have heat-resistant glazing, respectively, 27.28.29. A hatch 30 is installed on the lower cab surface for landing crews on the first and second cabins , the crew of the second stage gets into its cabin through the cabin of the first stage, the upper hatch 31 (fig. 6) of the first cabin and the corresponding hatch on the lower surface of the hull of the second stage. The first and second stages have, respectively, the main propulsion system 32, 33 (for example, GRL) and the auxiliary engine installation, respectively, 35 (for example, TRL); the transport spacecraft has a main (sustainer) propulsion unit Zb (for example, ZRL.); the main KRLs of the first and second stages are located inside the rear part of the corresponding hull-wing, the output sections of the nozzles 37 and 38 of the main rocket engines are profiled along the contour of the corresponding surface of the hull-wing (nozzles with an oblique cut). Major LPRE, first and second

the steps are installed in swinging (in pitch) suspensions; Kaniyu can be carried out by changing the supply of fuel components. in LRE, spaced apart relative to the 35 longitudinal axis of the hull-wing Main LREs of the transport spacecraft are installed in cardan suspensions, which ensures control of the TAC on the cruising mode Auxiliary TRD. 40 in the first stage are arranged symmetrically and spaced relative to the longitudinal axis, which provides for both yaw control in flight and return and taxiing maneuvers during the 5th landing; at the same time, the first-stage turbofan engines are mounted on pylons and fastened to the lower, rear surface of the wing housing; TRDs of the second stage are installed inside the hull of a wing-wing part, air-50 intakes 39 (fig. 10) of these TRDs emerge on the upper surface of the wing, and the exit sections of their nozzles 0 are profiled along the contour of the upper surface of the wing-wing,. 55

For orientation and stabilization of the second stage and TKK in the upper layers of at-. the rocket and the space in the cosmos serve 58

removal paths of the fuel components for the main) {RD, second stage, working from the moment of start and until the stages are divided in parallel with the main rocket engines of the first stage, are supplied from the fuel tanks of the oxidizer 52 and fuel 53 of the first stage (fig 7), 5 5 53 are connected by fuel communications We also have a central spherical fuel tank 5 (through intake points), fuel valves 55 and oxidizer 5b (Fig. 6), located on the upper flat surface of the first stage, and fuel communications of the second stage, in the torus tanks of fuel 57 and oks merged 58 second stage.

Similarly, in order to increase the energy output of MVCS at the final stage of the active part of the trajectory, the output (and the fuel components for the sustainer LRE of the transport spacecraft operating from the moment of separation of the TKK and up to the moment of expelling of the TKK into the reference orbit is fed from tanks 59 and 60 through the intake points ) the oxidizer tank 61 and the fuel tank 62 (fig „12), located on torus tanks 59 and 60, and engines (nozzles) of small thrust; 1 and 12, respectively, on tanga, 3, respectively, on roll, and t5 and ii6 respectively , ЖР. P are also intended for maneuvering, respectively, the second stage in the upper atmosphere and TKK in the upper atmosphere and space.For takeoff with a short run-up and to reduce the landing speed and path length on the lower surface of the wing housing (at the rear edge) the first and second stages are installed, respectively, jet flaps (7 and B, the selection of gases for which is carried out, respectively, for the turbines of the turbofan engines through channels JS and 50; TKK for this purpose has mechanical flaps 51 (Fig, 10). To stabilize the center of gravity in flight, as well as for the convenience of placing the payload, equipment, equipment, systems and communications, the tanks for the first and second stage fuel components and the TAC are respectively made in the shape of a torus and are located symmetrically relative to the respective vertical axes. To increase the energy output of MVKS at the first stage of the active site, the fuel communications of the TKK to the torus tanks of fuel 63 and the oxidizer of 6 TKK. The transfer of astronauts from the cockpit of the TKK crew to the payload compartment 8 serves as a transitional compartment B5, in which the equipment, equipment and communications are also located. The first stage has four-foot landing gear 66 (Fig. H), the second landing gear and TAC are equipped with the same landing gear. To prevent the rear part of the first stage hull from coming into contact with the ground on its lower surface along the longitudinal axis, YakTan presents the false 67. The design and power circuits of the first and second steps and TAC are identical and enlarged in the longitudinal and transverse power set, which includes respectively (for the first, second stages and TKK) beam stringers 68,69,70 and transverse strength elements (frames) 71,72,73, respectively, which consist of shelves and walls 75 (Fig. 8) "The upper surface of the shelves 7 is adapted For connection with stringers (or spars) and with 76 "plating, racks 77 were attached to both sheets to increase the rigidity of the walls of the inner walls. In order to increase the rigidity of the structure and reduce its weight, cutouts 78" were made in sections of the structure, where there are large concentrated forces (for example, the propulsion forces of the propulsion system or forces acting on the elements of the chassis compartments, etc.); e-compression; they are fastened to the shelves of the frames with the help of plates 80 "For cleaning the carriages of the chassis in the housing-wing of the first, second stages and TKK, niches 81,82,83 are made, respectively, such as the layout of the MVKS assembly, and the layout of its individual elements (steps and TKK) . provide high aerodynamic and flight characteristics of the whole system as it moves along the active part of the trajectory, as well as its steps and TKK in a wide range of flight speeds, especially at supersonic and hypersonic speeds of 12. Compared with the prototype, the pre-laid structure has several advantages: firstly, due to the high structural bearing properties combined with the use of jet flaps in most of the effective area of the wing hull, the takeoff run-down speed, landing speed and run length are significantly reduced that will allow to take off on an aircraft heavy and even super heavy aircraft of such a system; secondly, due to the use of both fuel and TACs as main engines of rocket engines on liquid fuel, as well as the parallel use of components of the second stage engines from the first stage tanks and sustainer TKK engines from outboard torus tanks at the final stage of the trajectory When launching a TKK into orbit, in combination with a hot stage separation and TKK, the energy output of the MVKS compared to the prototype increases in terms of the payload with the same starting weight and thirdly, the overall arrangement MFCS and arrangement of steps and the TAC provides stability and a good controllability MFCS and its elements in the entire range of flight velocities in the atmosphere; fourth, the relatively high load-bearing properties of the structure (both the MVKS assembly, and its individual elements, steps and TKK) allow the second steps, after completing their work, to perform a broad maneuver in the atmosphere using auxiliary TRL for returning and reliable soft the landing on the base, from where the launch of the fifth, the TAC, had a high aerodynamic quality at hypersonic flight speed in the upper atmosphere, 0 and a large amount of fuel on board, is capable of producing a wide maneuver in the upper layers s atmosphere, and also to make the descent from orbit of any round of a robust soft landing almost anywhere in the country. j7 j7 m

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Claims (1)

A REVERSIBLE AIR-SPACE SYSTEM containing the first and second stages and the transport spacecraft equipped with the main auxiliary propulsion systems, control systems, aerodynamic surfaces and air rudders for stabilization and control in the atmosphere, crew cabins, landing gear and flaps, lt and due to the fact that, in order to improve the aerodynamic, flight tactical and operational characteristics