RU2053936C1 - Non-expendable re-entry winged rocket pod - Google Patents

Abstract

FIELD: rocketry. SUBSTANCE: rocket pod has propulsion plant 6, glider 1 with aerodynamic surfaces, tail fins 3 and wings 4. Propulsion plant of rocket pod and glider are made in form of separate monoblock units combined by load-bearing units; glider wings have axes of turn located in transverse plane relative to longitudinal axis of rocket pod passing in area of center of masses of structure of non-expendable re-entry rocket pod. EFFECT: multiple re-entry of winged rocket pod, reduction of time and expenditured required for preventive maintenance and repair jobs between launches. 8 dwg

Description

 The invention relates to rocket technology, in particular to reusable rocket blocks using aerodynamic surfaces.

Known rocket units equipped with aerodynamic surfaces in the form of wings of various shapes for implementation after the operation of the main engines and separation of the unit from the launch vehicle and entering the atmosphere of flight in the atmosphere and landing on the airfield. Such missile blocks are used, for example, in Arian projects [1]
Known reusable returning winged missile block containing the propulsion system of the rocket block and a glider with folding aerodynamic surfaces, tail and landing devices, power communication units [2]. A wing is known in which part of it with the tail unit in the form of end washers is made folding. The axis of rotation of the wings are located outside along the block body. Due to the fact that in the folded state the washers go one after another, the wings are made of different lengths. In the prototype, the wings open before entering the atmosphere and form a triangular wing of double sweep. The implementation of the specified missile unit according to the traditional aircraft scheme leads to the fact that the power structure of the wing penetrates the fuel tanks, which are most often cryogenic (for example, liquid oxygen or liquid hydrogen). In this case, the wing design worsens the dynamics of fuel supply to rocket engines, complicates the control of fuel consumption, and most importantly makes it very difficult to make a tight connection at the intersection of the wing structure with the walls of the cryogenic tank.

 In addition, a missile unit with such wings, when flying at speeds from hypersonic (M> 20) to subsonic, is little adapted to them. More precisely, such a wing provides fairly normal flight conditions at hypersonic speeds, and at subsonic speeds it is of too low quality to provide long-term planning. Therefore, in order to ensure the return of the missile unit to the airfield near the start of the rocket, engines, such as the WFD, with a large fuel supply for them (to ensure a flight of several hundred kilometers) are required. Thus, the mass of the block is increased, necessary to ensure its reusable use.

 It is also significant that the technology of after-flight maintenance and repair work of the missile and aircraft parts of such a missile unit has differences and may not always be carried out in parallel. Hence the increase in time and cost in preparing the unit for subsequent start-up.

 This invention provides a solution to the problem of the multiple return of the cruise missile block, optimization of the design of the cruise missile block, reduction of time and costs for preventive and repair work between missile launches, provides the return of the cruise missile block with minimal mass to the airfield near the rocket launch site.

 The solution to these problems is ensured by the fact that in a reusable returned winged missile block containing a propulsion system of a rocket block and a glider with folding aerodynamic surfaces, tail unit and landing devices, power communication units, in accordance with the invention, the rocket engine propulsion unit and glider are made in the form individual monoblocks connected by power link nodes, while the wings of the airframe have rotation axes located in the transverse plane with respect to the longitudinal axis and a reusable returning winged missile block passing in the region of the center of mass of the structure of the reusable returning winged rocket block, and the wings themselves are folded forward along the glider fuselage and placed by the edges in the grooves of the fuselage, forming a triangular wing of small elongation with the possibility of forming a wing of large elongation in the open position.

 In FIG. 1-3 shows a reusable returning winged missile block with folded wings and an extended aerodynamic shield (in Fig. 1 is a side view, Fig. 2 is a front view, Fig. 3 is a bottom view); in FIG. Figures 4-6 show a reusable returning winged missile block with spread wings and retracted aerodynamic shields (Fig. 4 is a bottom view in flight; Figs. 5 and 6 are a side view and a front view of a landing gear on an aerodrome); in FIG. 7 reusable return winged missile unit with folding tail unit; in FIG. 8 reusable returning cruise missile unit equipped with an air-jet engine.

 The reusable return winged missile unit is assembled from a monoblock glider 1 with a retractable aerodynamic shield 2, tail unit 3 and wings 4, a rocket monoblock 5 with a marching engine 6 and orientation engines 7. The nose of the rocket monoblock 5 is closed by a fairing 8. Landing device, for example, a bicycle chassis type, consists of the main support 9, the front support 10 and auxiliary underwing supports 11. The axis of rotation 12 of the wings 4 are located in the vicinity of the center of mass of the “dry” structure of the reusable return winged p ketnogo block. The folding tail unit 13 is rotated around the axes 14. The air-jet engine 15 for “pulling” the reusable returning winged missile unit to the airfield near the start is fixed in this example on the folding tail unit 13. The wings 4 are folded with the edges in the grooves 16 when folded.

 Reusable return winged missile unit operates as follows. As part of the rocket, it is connected in a package with a launch vehicle, while the wings 4 and the aerodynamic shield 2 are folded.

 If, under the terms of the layout of the missile, the winged missile unit has a folding tail unit 13, then it is also folded.

 At the end of the first stage of the launch vehicle after turning off the marching engines 6, the winged rocket unit is separated from the launch vehicle and continues to autonomously fly along the ballistic trajectory, while during the ballistic flight the aerodynamic shield 2 is extended and the tail unit 13 opens (if it is folding) . On a downward trajectory of ballistic flight, the winged missile block is oriented using orientation engines 7 and enters the fairing into the dense layers of the atmosphere forward.

 After the speed drop, the aerodynamic shield 2 is retracted, the winged missile block, having made a turn to the side of the landing aerodrome, opens wings 4. If necessary (depending on the distance from the landing aerodrome), specially installed for this case air-propelled engines 15. When approaching the winged missile block goes to the landing glide path and lands on the released supports 9, 10, 11.

 In some cases, when the trajectory of the active section of the launch vehicle’s flight is such that the cruise missile unit enters the atmosphere at the farthest distance from the launch site, it is necessary to equip the cruise missile unit with engines, for example, the WFD, in order to ensure that they reach the aerodrome near rocket launch sites. Moreover, due to the high quality of the wings, to maintain the planning flight, the required engine power and, accordingly, fuel consumption is less than in the prototype. In these cases, you can do without the engines, "reaching out" at startup. At the same time, the reusable returning winged missile block lands automatically at the 1st class airfield, where it is equipped with engines, refuel and in a controlled pilot mode flies to the rocket launch site.

 This difference is also due to the fact that a triangular wing of small elongation, compared with a wing of large elongation at the same wing area, requires more significant flight speeds. Usually the triangular wing of small elongation (3) is used on supersonic aircraft. And at subsonic speeds, the plane is forced to fly with a large angle of attack. In all cases, this increases the engine thrust and specific fuel consumption, or the planning length decreases sharply.

 Sometimes it is necessary, according to the conditions of the layout of the launch vehicle or for other reasons, for example, to the restrictions on the dimensions due to the starting structures, the tail unit to be folded. In these cases, the tail unit is revealed after separation of the winged missile unit from the launch vehicle while moving along a ballistic trajectory before entering dense atmospheric layers.

 At the end of the flight, the cruise missile unit undergoes a defect, preventive and repair work and prepares for the next launch. It should be noted that, firstly, the glider monoblock can actually withstand more than 100 launches (just as, for example, the Buran orbiter is designed for 50 launches), and the missile monoblock, including its most complex and expensive part rocket engine, not more than 10 starts; secondly, while repairing and preventing a glider monoblock (replacing a part with a heat-shielding one, replacing the chassis wheels, inspection), the time will not exceed 3-5 days, then in a rocket monoblock repair of only a rocket engine (including fire technological launches) will not take less than 2 months.

 Therefore, it is technically and economically advantageous to have several rocket monoblocks per monoblock glider. This ensures a more complete use of each component, and on the other hand, reduces the time for prevention and repair.

 Economically, as well as environmentally friendly, the absence of land alienation zones (their area is hundreds of square kilometers) for the fall of the spent first stages of the rocket.

 In world practice, only Space Shuttle boosters, parachuting into the ocean, were saved, where they were caught. After repair and refinement, only the booster case was used.

 Design and development work is underway to create a reusable returnable cruise missile block using the rocket part of the first stage block of the Energia launch vehicle.

 By blowing in the wind tunnel, the correctness of the chosen aerodynamic forms was confirmed, their optimization was carried out, and the possibility of entering the atmosphere at speeds up to M-26, as well as the high quality of the elongated wing at subsonic speed, were confirmed.

 The existing industrial base of the leading rocket and space and aviation plants will provide for the manufacture of the designed reusable returnable missile block.

 A flight test program is being developed in automatic and manned modes.

 There are materials, including thermal protective materials, tested on the Buran orbiter, which are necessary for the design of the cruise missile unit.

 The landing and landing control system worked out on the Buran orbiter will also be used on this reusable returning cruise missile unit.

 The rest of the rocket, space and aircraft systems (motion control, command and measurement, power supply, fuel supply, pressurization of tanks, etc.) are widely used on rockets, spacecraft and airplanes, have a large elemental base in technology and therefore do not represent technical complexity in application.

 The reusable returnable missile unit, in addition to the above technical result, provides another one. This additional technical result is due to the fact that usually the number of possible uses of the glider itself is greater than the number of reuse of the rocket unit by one or two orders of magnitude, and the time of preparation of the rocket block for subsequent launch is longer than the time of the same preparation of the glider.

 Therefore, the technical solution of the reusable returning cruise missile block according to this invention provides, on the one hand, parallel maintenance and repair work, and on the other hand allows you to install on the monoblock glider any other similar rocket monoblock ready for this time. And thus, the number of glider monoblocks will be at least an order of magnitude smaller than rocket monoblocks.

Claims (1)

 REUSABLE RETURN WINGED ROCKET BLOCK, comprising a propulsion system of a rocket block and a glider with folding aerodynamic surfaces, tail unit and landing devices, power communication units, characterized in that the rocket engine and glider propulsion system are made in the form of separate monoblocks connected by power communication units, the glider wings have rotation axes located in the transverse plane with respect to the longitudinal axis of the reusable returning winged missile unit a, passing in the region of the center of mass of the design of the reusable returning winged missile unit, and the wings themselves are folded forward along the fuselage of the airframe and placed by the edges in the grooves of the fuselage, forming a triangular wing of small elongation with the possibility of forming a wing of large elongation in the open position.

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