SU811679A1 - Reusable aircraft system - Google Patents

Abstract

REUSABLE AIR-SPACE- 'CHEMICAL SIS' ^ EMA, containing a transport spacecraft with a fuel tank, mounted on a retractable platform, and an accelerating unit including the first stage, while the first stage 'and the transport spacecraft are equipped with the main and auxiliary propulsion systems, means control, aerodynamic surfaces and air wheels, crew cabins and chassis, characterized in that, in order to increase the system’s versatility, by ensuring that personal in terms of weight, design and purpose of transport and spacecraft with a useful Hai-lock and improvement of system performance, the upper stage is made in one stage in the form of a disk, in the central part of which there is a shaft, equipped with fixing points of the sliding platform, while the surfaces of the sliding platform and the bottom of the accelerating stage are connected by a cola-flexible flexible sealed wall, and the chamber formed is connected to an on-board source of compressed gas with an automatic control system lining its pressure and flow rate o2. A reusable aerospace system in accordance with claim 1, which means that the transport spacecraft is installed directly on a retractable platform. 3. A reusable aerospace system pop „ 1, which differs in that the transport spacecraft is made in the form of a tank-disco glider, on the outer upper surface of which, along the longitudinal axis, a recess-niche is made under the payload.

Description

The invention relates to aerospace engineering, namely, to aerospace systems and is intended for launching space objects (payloads) for various purposes into orbit and returning them from orbit to Earth.

The closest of the known technical solutions is a reusable aerospace system comprising a two-stage accelerating unit and a transport spacecraft (TKK), where the wing-housing of the steps and the transport spacecraft in the plan are in the shape of a circle, and the profile is made respectively in the form of a trapezoid and a truncated rhombus, the upper flat surface of the first-stage body-wing is docked with the lower flat surface of the second-stage body, and the transport spacecraft suspended from It has fuel tanks installed in the center of the second-stage hull on a sliding platform, while the first stage and the transport spacecraft are equipped with main and auxiliary propulsion systems, controls, aerodynamic surfaces and air rudders, crew cabins and chassis. The systems consist in the fact that, firstly, it does not provide output by the upper stage, the earth orbits of different weights.  Constructions and purpose of tran- i ,, sport spacecraft (orbi-.  tal steps) with a payload of various purposes, weight and dimensions; secondly, the complexity of the operation of this system with.  The aim of the proposal is to increase the system's versatility by providing the upper stage with different weight, design and destination transport spacecraft with payload and improving system performance. This goal is achieved by the fact that in the reusable aerospace transport system the upper stage is made in one step disk-shaped, in the central part of which a shaft is made, equipped with fixing units for a sliding platform, while the internal surfaces of the platform The chambers and bottoms of the accelerating stage are connected by an annular flexible hermetic wall, and the sealed, closed hermetic chamber is connected to an onboard source of compressed gas with a system for automatically controlling its pressure and flow.  In addition, in order to increase the mobility and efficiency of the transfer of the transport spacecraft into orbit, it is installed directly on a retractable platform, In addition, in order to be installed in the second non-returnable stage, the utility; disposable goods; G-1 large weights and -size, it is made in the form of a tank-discoplane, on the outer upper surface of which, along the longitudinal axis, a notch is made - a niche for the payload Figure 1 shows a schematic reusable aerospace system, top view; Fig 2 - the same, bottom view; in fig.  3 - the same, rear view; in fig, k is the same side view; FIG. 5 is the same, front view. FIG.  6 - the constructive-power scheme of arrangements of the upper stage (first stage) with a transport spacecraft (second stage) is shown; FIG. 7 is a section along A-L in FIG.  6; in fig.  8 is a view along arrow B in FIG.  6; in fig.  9 is a view along arrow C of FIG 6; in fig.  10 is a section taken along side A-A in FIG.  6 (option 1a - the second stage includes a transport spacecraft and a discharged fuel tank suspended from it); in fig.  11 - section A-A in FIGURE 6 (option 1b — the second stage is a transport spacecraft directly mounted on a sliding platform); FIG. 6 is a section along the line A-A in FIG. 6 (option 1c — the second stage is a disposable fuel discooplan tank with a propulsion unit); in Fig. 13, a view along arrow L on FIG 12 (top view of a disposable fuel disco-tank with a disposable payload located on it) Fig. Il - schematically shows a structural diagram of the first-stage shaft MVKS-U; in FIG. 15, a section along the AND in FIG.   The reusable aerospace system (MVKS-U) shown in FIG.  1-15 includes the first unified stage 1 representing c.  The plan is a view of a circular disk in the central part of which a shaft 2 is made, inside which a sliding platform 3 is installed, on which the installation, centering and mounting of various variants of space objects 4 (different versions of second stages with a payload) are performed, which as shown in Figs 10-12, three fundamentally different structural-layout schemes of the second stages can be used: - version Ta - orbital stage, space transport, 5 ai spacecraft (TKK), made in the form of a discoplane and installed on a retractable platform with the top tank 5 suspended from it; Option 16 - the orbital stage (TKK) has the same shape as for option 1a, but has large internal tanks (tanks) for the fuel components on board and is mounted directly on the sliding platform; Option 1c - the second stage is a large diameter fuel tank-disc 6 and is constant high to the shell of which the 7 ° taper fairing is attached. For all the options, the first stage is basic, unified.  the reusable stage and together with the above-described variants of the second stage represents the universal reusable aerospace system (MVKS-U); the orbital stage (TAC) in variants 1a and 16 is also unified and applied many times (disposable suspension tank 5, at the calculated point of the active hatch section it is separated from the TAC, enters the dense layers of the atmosphere and burns out); In the second stage version 1c, the tank 6 is also single-use and after a payload of large weight and size is brought into Earth orbit, according to the program it enters the dense layers of the atmosphere and burns out.  In both the first and second stages, the body and wing in a structurally structural plan are organically a single whole — the body-wing, which represents a circle in plan, and a truncated rhombus in cross section. Up until the separation of the steps, the upper surface of the second wing is organically fits into the upper contour of MVKS-U; After separation of the second stage from the first, platform 3 occupies the uppermost position (single for all variants of the second stages), becomes locked and forms (supplements) the upper outer contour of the first stage.  In the center of the second stage, along its longitudinal axis, there is a payload compartment 8 (for option 1c in the fuel tank 6, along the longitudinal axis, a recess-niche is made for this purpose, where the payload 5) is installed, which is closed from above by sashes 10 (FIG.  1.0-13) i On the upper surface of the first stage.  in the rear hemisphere, two kilos with twelve turn wheels 12 are installed and spaced symmetrically with respect to the split axis; in the TKK (variants of the second stage 1a and 1b) on the upper surface in the rear hemisphere, along the longitudinal axis, one keel 13 is installed with the steering wheel in order to protect the construction of the keels 11 and 13 from the gas jets of the main (sustainer) engines when they deviate in cardan suspensions, the bottom surface of the above keels has profiled cutouts (FIG.  1-5).  At the trailing edge of the first stage of the MVCS-U, symmetrically relative to the longitudinal axis, elevons 15 are installed to control roll and pitch in dense layers of the atmosphere; For the same purpose, elevons 16 are installed on the TAC (variants of the second stage Ta and 1b), which are located similarly (Fig. 1-2). For the second stage of a single use (option C, Fig. 12-13), the above air handlebars are not installed stage and TKK (variants of the second stage 1a, 1b, Aigo 10-11) manned, In the forward hemisphere of the first stage, along the longitudinal axis, is the crew 17, which does not go beyond the dimensions of the wing-hull o Similarly, the cockpit TKK 18 and includes two compartments (fig. 10-11): single-storey compartment Pilots 19 osmonauts and a two-storey compartment for cosmonaut exploration and rest of crew 20, which is connected through a transition tunnel 21 with a payload compartment A docking station 22 is located on the upper surface of the second stages (Fig) between the crew cabin and the payload compartment (for docking in orbit with other space objects), which through the lock chamber 23 is connected with the transition tunnel 21 The first-stage cabins and the transport spacecraft have heat-resistant glazing, respectively 2 and 25 s. and cabin crew in the first n second stages are respectively hatches 26 and 27.  In the case-wing of the first and second stages, at the trailing edge, cuts are made symmetrically with respect to the longitudinal axis, where the main (cruise) motor drives 28 are installed in cardan suspensions, for example, the CCD on the components is liquid hydrogen + liquid sour.  811 genus, here is also installed a unit of auxiliary thrusters for orientation and stabilization of the first stage in the upper layers of the atmosphere (where it comes after separation of the stages), respectively, in pitch - 29, in yawning - 30 (Fig. 9); in order to increase the efficiency of orientation and stabilization of the first and second stages. in terms of roll and decrease in fuel consumption, engines of small traction are separated relative to the longitudinal axis to the periphery of the first and second stages of the wing housing and marked 31 and 32, respectively (FIG.  b, fig.  13) "The above principles of locomotor placement. installation in the first stage, in cent {n x. to maximize the effectiveness of the apparatus during its operation, applied for the second stages, where the following designations are accepted: main (sustainer) engines 33, for example, the MWP on components liquid hydrogen + liquid oxygen, engines -. for maneuver TKK in space and in the upper layers of the atmosphere 3, as well as two sets of auxiliary thrusters (for the purpose of increasing TKK reliability, they are duplicated and spaced symmetrically relative to the longitudinal axis); For orientation and stabilization of the second Steps in space and in the upper atmosphere, low-thrust engines were installed, respectively, in pitch - 35, in the yaw - 36, and also low-thrust vernier engines 37, to adjust trajectory parameters (FIG. 8).  To ensure reliable return of the first stage to the cosmodrome, launch and launch (or to another planned base), as well as for autonomous transportation of MVKS-U from the manufacturing plant to the cosmodrome, when relocating to another cosmodrome, as well as to work out the first stage of the flight tests of MVKS-U at subsonic speeds, are auxiliary turbojet engines (TRD) 38, which are installed under the central bottom of the first stage, in the rear hemisphere, symmetrically relative to the longitudinal axis (FIG. 2-5, FIG. 10 stabilization of the center, in-flight gravity, as well as for convenient placement of equipment, equipment, systems and communications, tanks for the first stage fuel components, and orbital stages are made in the form of torus parts and arranged symmetrically relative to the vertical axis, fuel tanks, respectively, 39 and t tanks the oxidizing agent is respectively il and 2 (FIG.  6-7); To supply the first and second stage engines with fuel for the low and thrust units, tanks 3 and IC / | are used respectively. To increase the energy output of MVKS-U (second stage version 1a, with a hanging tank (on the active part of the extraction trajectory, after separation of stages, fuel for LREs of the second stage (from the moment of their launch and until reaching the calculated point of the trajectory) comes from the tank 5 suspended on the Corbital stage (TKK), and after producing fuel from it, the automatics switches its intake from the side tanks 40 and iZ.  .  I.  .  The first stage has a four-bearing chassis 5, the orbital stages of multiple use have the same chassis. The design and power circuits of the first and orbital stages are essentially identical (Fig.  6-7, figs. 10-11) and enlargedly include the longitudinal and transverse strength set, which includes, respectively, radial stringers 6 and transverse strength elements (frames) of the cylindrical type, W and D, respectively, in order to increase the rigidity of the structure and reduce its weight cylindrical frames are made cuts.  In the section of the structure, where large concentrated forces act (for example, the thrust force of the main propulsion system, mass-inertial forces acting on the elements of the chassis sections, etc. ) on the cylindrical frames supported by spacer elements 50, which work well for stretching and compression (figo 6, figs, 10-12) “For cleaning the chassis carts in the first stage wing and orbital stages (TKK), niches 51 and 52 were made respectively (FIG.  2, FIG.  6) with Va. oriental stage without a hanging tank (FIG.  6, fig. 11), a set of additional tanks is installed on board: cylindrical cylindrical fuel tanks 53 and spherical oxidizer tanks 54 у у81167 In order to qualitatively improve the aerodynamic characteristics of MVKS-U, a considerable part of the design of the second stages is closed in the mine, and the upper part of these stages fits into the general circuit of the MVKS-U to form smooth outlines "Mine 5 is made in the central part of the first stage, where the wing-hull profile has a maximum and constant thickness; The outer diameter / shaft is the power ring 55 (FIG.  ), which, being the main force element of the first stage, includes, respectively, the internal power wall 5b and the external 57, which are interconnected by stiffness elements 58, for example, a truss type.  From the bottom, the shaft is closed by a hermetic bottom 59, which is attached along the contour to the power RING. 55. .  In platform 5, platform 3, extends from above. which is installed in the mine in one of.  positions (positions) corresponding to the second stage variant (Fig. 10-14). The inner surface of the extendable platform 3 is connected to the inner surface of the bottom of the first stage 59 by means of a flexible sealed annular.  walls 60 (for example, in the form of furs. harmonics), which is fixed to both of the above surfaces, for example, by means of glue, which results in the formation of a closed cylindrical sealed chamber B1, to which compressed air is supplied to move the platform to a predetermined position.  mine.  In the center of the bottom of the first stage there is a sealed hatch B2 for the purpose of accessing the inside of the chamber 61 during operation between the innermost power annular wall 56, the flexible hermetic annular wall 60 on one side, the peripheral part of the inner surface of the bottom of the first stage 59 and the peripheral part of the inner surface of the retractable platform 3 on the other hand, an annular volume 63 is formed, where fuel tanks are installed for auxiliary turbojet engines 3 of the first stage (FIG.  1), while the standard set of tanks b ensures the return of the first stage after the separation by the steps; Additional sets of warming tanks 65 and 66 are installed when MVKS-U is autonomously transported (or separately in the first stage), depending on the flight range.  All tanks are commuted to the standard set of bpc b, and they, through the b7 fuel lines, pump the fuel pumps 68 with them and the 69 fuel line pipelines with the TRR GP (lego. 15).  The direction of movement of the platform, in the mine, along its inner perimeter, is set to direction 70 (for example, two along the x-x axis and two along the axis 2-7. ) o Extendable platform in outer diameter (for example, axes xx and z-g) has elements of the platyma / 1 locking mechanism, and along rails 70, inside the power ring 55, for each position of the platform, with an appropriate second stage version , the locks of the platform fixation mechanism 72 are installed, which together with the elements 71 represent a single mechanism for fixing the platform in a predetermined position, Ll improve the lateral (lateral) stability of the first stage at a subsonic flight speed, its end surfaces 73 deflect downwards ( for landing / those for landing) / The layout of MVKS-U was chosen, as well as the layout of its individual elements provides it with high aerodynamic, energy, flight and performance characteristics, which, in combination with other design solutions used in this proposal, allowed. um to qualitatively improve the most important tactical and technical characteristics: - firstly, due to the release of the surface of the first-wing and second-wing hull from the depth of the rupe and the ailerons of the two-sided circuit embedded in it, which turbulizes the air flow when it is deflected over the most of the effective wing surface, replacing them with elevons and placing them at the rear edge, the aerodynamic characteristics are significantly improved (the drag decreases, the hull-wing and aerodynamic amicheskoe quality and efficiency is improved rudders); - conditions are significantly improved.  entering the first stage (after separation of the steps) into the dense layers of the atmosphere in order to make a spatial maneuver and exit to the launch pad area, since the moment of separation of the TKK from the first stage will be characterized by the following parameters: separation speed Vpaj 1600 m / s, separation height 53 km, the separation distance is 125 kio, whereas for the prototype, these parameters at the time of separation of the TAC from the second stage will be respectively: 500 m / s, 130 km and 1000 km. ,; taking into account the conditions for the entry of steps into the dense layers of the atmosphere and performing a spatial turn to return to the starting and landing base, the range to the base will be, respectively,} Q km „and 3300 km. Therefore, the return of the first stage to the start-landing base, unlike the prototype, will be qualitatively simpler and easier both because of the softer separation parameters of the stages and there is no need to leave on board large reserves of fuel for return and landing, which are commensurate for the prototype with a dry weight of the second stage; - a relatively low speed of separation of the first stage from the TAC (in this proposal) leads to setting less stringent requirements for the design and systems of this stage, unlike the second stage of the prototype, and especially for temperature conditions, which reduces the development costs of the proposed IVKS-U according to comparing with the prototype by approximately 30%, since the construction here can be used alloys that are widely used in the aviation industry without thermal protection, with the exception of the leading edge; - the operating conditions of the proposed MVKS81 are significantly improved due to both a decrease in the number of stages and the absence of the need for the first stage of MVKS-U to have airfields along the launch routes or specially prepared landing sites suitable for their characteristics and equipment for receiving such objects as the second stage of the prototype, staffing their respective staffs of specialists and the provision of fuel components; - in accordance with the above, the operating costs of the proposed IVKS-U are significantly reduced. The proposed MVKS-U as a whole and its elements (stages) are implemented in terms of unified tactical-technical and production-technological concepts.  - Development of the project will largely unify the KOHCTDVK assembly and power circuit, motor installations, equipment, equipment and communications of both stages, which will lead to the unification of the experimental testing and production and technological base, and this will reduce the development time and development costs of MVKS- W.  When developing MVKS-U, it will be possible to use existing models of engines, equipment and equipment that are well-proven in operation, which will further reduce the time and cost of development. The proposal has good structural and technological continuity, taking into account the prospect of aerospace engineering, atomic energy and the latest energy.

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Claims (1)

Reusable AIR-cosmic 'Ceska ICI ^T EMA, comprising a transport spacecraft with a fuel tank mounted on a sliding platform and the upper stage comprising a first stage, the first stage and the transport spacecraft provided with main and auxiliary propulsion control means, aerodynamic surfaces and air rudders, cabins for crews and chassis, characterized in that, in order to increase the versatility of the system, by ensuring the output of the acceleration unit ra different in weight, design and purpose of transport