RU2458830C1 - Spaceship return apparatus - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to rocketry. Return apparatus comprises capsule 1, solid-propellant rocket engine 2 with nozzles 2 aligned with said capsule. Said nozzles are arranged at definite angle to lengthwise axis. It includes also adapter 4 to joint said engine 2 with capsule 1. Spaceship systems 5 are arranged on capsule 1 under adapter 4. Adapter 4 consists of two sections (6) and (7) interconnected by shift device (9) and retainer (8). Shift device (9) is equipped with power drive (10). Section (6) jointed with engine (2) is provided engine shifted position retainer (11). Go-devil inserts (12) may be fitted in throats of engine nozzles (3). Section (6) may be arranged to shift in position corresponding to engine axis crossing with return apparatus center of inertia. Power drive (10) and retainer (8) represent one-way-action mechanisms. Extra nozzle with pyro plug (17) may be arranged on engine (2) between nozzles (3).

EFFECT: decreased launching weight.

4 cl, 5 dwg

Description

The invention relates to rocket technology and can be used to create a returned apparatus (VA) equipped with a solid fuel emergency rescue system (CAC) and a brake propulsion system.

It is known to use a solid propellant rocket engine (RDTT) as a propulsion system (DU) for the SAS of the return vehicle of the Soyuz-TM spacecraft [On the life and work of Academician B. P. Zhukov. - Tula: Grif and K, 2008. - 304 p., Ill., Pages 79, 80]. The solid propellant rocket motor is connected to the VA capsule via an adapter (resettable head fairing). The solid-state solid-propellant solid-propellant alloys together with the adapter are discharged in a certain part of the active trajectory. The disadvantage of this scheme is that in the absence of an emergency, the solid propellant is a passive cargo. Effective emergency rescue of a spacecraft after the rejection of a solid-propellant solid-propellant CAC is problematic. The layout of the specified spacecraft requires a special braking engine for the return of the spacecraft to Earth.

The closest in technical essence and the achieved positive effect to the invention is the returned apparatus (VA) [Federal State Unitary Enterprise “NPO Mashinostroyenie” 60 years of dedicated work in the name of peace. -Moscow: Arms and Technologies, 2004. - 332 pp., Ill., Page 246], containing a capsule, a solid fuel rocket engine aligned with it, an adapter by means of which a solid fuel rocket engine is connected to the capsule. The solid propellant rocket engine of this VA acts as a brake engine for braking the VA when it leaves the orbit. At the same time, the specified solid propellant rocket motor can be used as a CAC engine. One of the drawbacks of this design is the location of QC systems (docking station) on the bottom of the VA, i.e. in its heat-stressed zone. A further drawback of the scheme under consideration is that the requirements for the ballistic characteristics of the CAC engine and the braking engine are different. The CAC engine must provide maximum overload (maximum traction) for guaranteed salvation of VA. VA overload during its braking before its return to Earth should be significantly less to reduce the negative impact on the crew.

The technical task of the present invention is to reduce the starting mass of the returned spacecraft apparatus and expand its functionality.

The essence of the invention lies in the fact that in the returned spacecraft apparatus containing the capsule, a solid fuel rocket engine coaxial with nozzles located at an angle to the longitudinal axis, an adapter by means of which a solid fuel rocket engine is connected to the capsule, systems are located on the capsule under the adapter spacecraft, and the adapter is made of two sections connected to each other by a displacement unit and a locking-fixing device. The bias unit is equipped with a power drive. The section connected to the solid fuel rocket engine is equipped with a device for fixing it in an offset position. The nozzles of a rocket engine of solid fuel in its critical section can be equipped with resettable liners. An adapter section connected to the solid fuel rocket engine can be biased to a position corresponding to the axis of the solid fuel rocket engine passing through the center of mass of the returned vehicle. In this case, the power drive and the locking-fixing device are unidirectional mechanisms. On the rocket engine of solid fuel between the nozzles can be placed an additional nozzle with a pyrotechnic plug.

The technical result is achieved through the use of the same solid propellant rocket motor as a CAC engine and a braking engine, and by placing QC systems in the most convenient place for the capsule. This, in turn, is achieved by leading the engine through a displacement unit and a power drive from the longitudinal axis of the VA to access the elements of the spacecraft (docking station, antenna), which is necessary to ensure unhindered docking. For braking the VA axis of the solid propellant rocket must pass through the center of mass of the VA. It is possible to ensure that the solid propellant is returned to its original position by means of a power drive. To reduce the VA overload at the time of its braking, the thrust of the solid propellant can be reduced by increasing the critical section area of the nozzles. Accordingly, the nozzles in their critical section can be equipped with resettable liners.

If the axis of the solid propellant rocket in a deflected state was aligned with the center of mass of the VA (third claim), then a return to its original position is not required. From the point of view of the locking-fixing device and the power drive, this option is simpler, since the power drive and the locking-locking device are single-use elements. If at the same time an additional nozzle with a pyrotechnic plug is placed between the nozzles on the solid propellant rocket (fourth claim), then the total critical section area changes only due to the reset of the pyrotechnic plug. The design of the nozzles does not require complication (the second claim).

This technical solution is not known from the patent and technical literature.

The invention is illustrated by the following graphic material.

Figure 1 shows the VA QC with solid propellant rocket motors in the initial position.

Figure 2 shows the VA QC with a dedicated solid propellant, opening access to the ship's systems.

Figure 3 shows the VA QC with a variant (according to the third claim) of the solid propellant rocket motor in the initial position.

Figure 4 shows the VA QC with a variant (according to the third claim) of the allotted solid propellant rocket engine, providing access to the ship's systems. In the same FIG. The technical solution according to the fourth claim is presented - an additional nozzle with a resettable pyrotechnic plug.

Figure 5 shows a nozzle with a resettable liner (according to the second claim).

The returned spacecraft apparatus contains a capsule 1, a coaxial solid propellant rocket engine (solid propellant rocket engine) 2 with nozzles 3 located at an angle to the longitudinal axis. The solid propellant rocket engine 2 is connected to the capsule 1 by means of an adapter 4. On the capsule 1, under the adapter 4, spacecraft systems 5 are located. Systems 5 can be a docking station, antenna device, etc. The adapter 4 is made of two sections 6 and 7. Section 6 is connected to the solid propellant rocket engine 2. Section 6 is connected to the capsule 1. Section 6 and section 7 are connected by a locking-fixing device 8 and the displacement unit 9. The displacement unit 9 can be a single-link, two-link hinge, pantograph or other kinematic mechanism. The bias unit 9 is equipped with a power drive 10. The adapter 4 is equipped with a locking device 11 in an offset position. In the embodiment according to the second claim, the nozzles 3 can be equipped with resettable liners 12 (not shown conditionally in FIGS. 1-4), fixed by means of pyro fixators 13 (see FIG. 5). The liner 12 can be attached to the nozzle 3 by means of a flare socket 15. The section 6 of the adapter 5 is installed in the variant according to the third claim of the invention with the possibility of displacement to the position corresponding to the passage of the axis 14 of the solid propellant rocket motor 2 through the center of mass of 16 VA. VA is equipped with orientation and stabilization systems (Figs. 1-5 are not conventionally shown). For the case under consideration, the solid propellant solid propellant rocket can be equipped with a nozzle with a pyrotechnic plug 17.

The device operates as follows. When the spacecraft is in the composition of the launch vehicle on Earth or in flight, an emergency may occur that requires the use of SAS. During the operation of the SAS, the solid propellant rocket engine 2 is launched, which creates traction to divert from the launch vehicle and, accordingly, rescue the capsule 1. The operation of the SAS is possible throughout the entire operation section of the launch vehicle (in the active section of the trajectory). After the spacecraft is put into orbit, it becomes necessary to bring the spacecraft systems 5 (docking station, antennas) into operation, located in the initial state under the adapter 4. To ensure this, the locking and fixing device 8 is released and the solid propellant is displaced 2 along with section 6 from the longitudinal VA axis by means of a power drive 10 and a displacement unit 9. Section 6 is fixed in a deflected state by a locking device 11. CC systems 5 are brought into working position (see, for example, FIG. 4). The spacecraft performs the tasks assigned to it (for example, docking, undocking with other space objects). To return the VA to Earth, he needs to report a braking pulse. The longitudinal axis of the solid propellant rocket motor 2 must coincide with the direction of traction of the brake pulse.

This can be done in one of two ways:

1. (According to the first claim) By means of a power drive 10 and an offset unit 9, the solid propellant motor 2 returns to its original position and is subsequently fixed with a locking-fixing device 8. In this case, it may be necessary to return the 5 QC systems (antennas) to their original folded position.

2. (According to the third paragraph of the claims) The return of the solid propellant rocket engine 2 and 5 QC systems to their original position is not required. Next, the orientation and stabilization systems deploy VA in the desired direction. After that, the solid propellant rocket motor 2 is switched on, creating traction.

If necessary, the traction of the brake pulse can be reduced in comparison with the thrust of the solid propellant rocket motor 2 in the mode of its operation during emergency rescue.

Reducing the traction of the brake pulse can be carried out in one of two ways:

Occurs:

1. The reset liners 12 (in the second paragraph of the claims).

2. Opening an additional nozzle with a pyrotechnic plug 16 (according to the fourth paragraph of the claims). VA makes a landing according to a given program.

Feasibility study of the proposed invention in comparison with the prototype, which is used as the returnable device [Federal State Unitary Enterprise NPO Mashinostroenie 60 years of dedicated work in the name of peace. - Moscow: Arms and Technologies, 2004. - 332 p., Ill., Page 246], consists in reducing the starting mass of the returned spacecraft and expanding its functionality.

Claims (4)

1. A spacecraft return apparatus comprising a capsule, a solid fuel rocket engine coaxial to it with nozzles arranged at an angle to the longitudinal axis, an adapter through which a solid fuel rocket engine is connected to the capsule, characterized in that the spacecraft systems are located on the capsule under the adapter and the adapter is made of two sections connected to each other by a bias unit and a locking-fixing device, and the bias unit is equipped with a power drive, while the section connected to p ketnym solid fuel engine, it is provided with a fixing device in a displaced position. 2. The returned spacecraft apparatus according to claim 1, characterized in that the nozzles of the rocket engine of solid fuel in their critical section are equipped with resettable liners. 3. The spacecraft return apparatus according to claim 1, characterized in that the adapter section connected to the solid fuel rocket engine is mounted with a possibility of displacement to the position corresponding to the axis of the solid fuel rocket engine passing through the center of mass of the returned apparatus, while the power drive and locking and locking device are unidirectional mechanisms. 4. The returned spacecraft apparatus according to claim 3, characterized in that an additional nozzle with a pyrotechnic plug is placed between the nozzles on the solid fuel rocket engine.

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