RU2775891C1 - Solid-fuel rocket engine - Google Patents

Abstract

FIELD: rocket science.

SUBSTANCE: solid-fuel rocket engine designed for the removal of separable parts of a launch vehicle contains a case, a solid fuel charge, an initiation system, and a nozzle path located at an angle to the longitudinal axis of the launch vehicle and closed with a plug. The plug is made of thin deformable material, and it has conical flanging, the outer surface of which contacts with the inner surface of the nozzle path through a sealing layer providing the engagement of the plug with the surface of the nozzle path. The end of the plug is additionally supported to the surface of the nozzle path from the side maximally remote from the launch vehicle along an arc S with a length from 0.5 to 1.5 R, where R is a radius of the end of the plug, wherein a distance L from the end of the nozzle to the end of the plug does not exceed 2R. Support of the plug can be made in the form of a deformable bracket, which is the extension of the conical part of the plug, which completely embraces the inner surface of the nozzle path, and which is attached to its outer surface.

EFFECT: invention will allow for the provision of plug release in a set direction, thereby eliminating the collision of the plug with a reentry vehicle and a launch vehicle.

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Description

The invention relates to the field of rocket and space technology and can be used in the design of solid fuel engines.

Known emergency rescue system (SAS), designed to rescue the crew in the event of an accident of manned spacecraft of the Soyuz type. For this system, a number of solid propellant engines are used, with the help of which the return vehicle with the crew is withdrawn and separated. The nozzle blocks of these engines are located on the outer surface of the launch vehicle body in such a way that the exit sections of the nozzles are facing the return vehicle (see the SOYUZ Federal Center for Dual Technologies, pp. 5, 8. Weapons and Technologies Publishing House, 2012. )

These engines, in addition to the general requirements, are subject to requirements regarding the inadmissibility of hitting (collision) of any separable elements with the return vehicle and launch vehicle. Thus, the Commission for the investigation of the crash of the spacecraft "Columbia" found that the cause of the disaster was the collision of a separated element (thermal protection tiles) on the carbon fiber panel of the return vehicle during takeoff. From the impact, a scratch was formed, which was the concentrator of its destruction during the descent, which led to the catastrophe of the ship.

One of the structural elements of solid propellant engines, which is separated from the engine, is the nozzle plug. On the one hand, the plug is an element of sealing the nozzle path of the engine, ensuring the safety of the charge during storage and transportation, and on the other hand, it ensures the reliability of the ignition of the charge and the stability of the output to the engine mode.

The design of nozzle plugs and the mounting method are very diverse (see V.V. Kalinin, Yu.N. Kovalev, A.M. Lipanov “Non-stationary processes and methods for designing solid propellant rocket engines” M. Mashinostroenie, 1986, p. 15; Yu.S. Solomonov et al. “Solid propellant controlled propulsion systems” M. Mashinostroenie, 2011, pp. 92, 94, 95, 105), as well as methods for confirming the parameters of their opening (see I.M. Gladkov et al. “Experimental methods determining the parameters of special-purpose engines "M. STC "Informtekhnika", 1993, pp. 6, 8, 9, 14, 87, 88, 92, 94, 95). The design of the engine is known (see the collection “Proceedings of MIT”, volume 8, part 1, p. 236) - taken as a prototype. In this engine, the plug is made of a thin deformable material and has a conical flare, the outer surface of which is in contact with the inner surface of the nozzle duct through a sealing layer that ensures the adhesion of the plug to the surface of the nozzle duct.

The disadvantage of using such engines in SAS is that the direction of the plug departure cannot be accurately predicted, since the adhesion of the plug to the nozzle tract is uneven, and to evaluate the trajectory of the plug departure, which depends exactly on which side the plug will begin to detach from the nozzle when exposed to product pressure. combustion of SDS is impossible.

The technical objective of the claimed invention is to ensure the departure of the plug in a given direction and the exclusion of the collision of the plug with the return vehicle and the launch vehicle.

The problem is solved due to the fact that a solid propellant rocket engine designed to remove the detachable parts of the launch vehicle, containing a body, a solid propellant charge, an initiation system and a nozzle path located at an angle to the longitudinal axis of the launch vehicle and closed with a plug, which is made of a thin deformable material and has a conical flanging, the outer surface of which is in contact with the inner surface of the nozzle tract through a sealing layer that ensures adhesion of the plug to the surface of the nozzle tract, and the end of the plug is additionally reinforced to the surface of the nozzle tract from the side as far as possible from the launcher along the arc S with a length of 0.5 to 1.5 R, where R is the radius of the end of the plug, and the distance L from the end of the nozzle to the end of the plug does not exceed 2R. In addition, the reinforcement of the plug is made in the form of a deformable bracket, which is a continuation of the conical part of the plug, which completely covers the inner surface of the nozzle path and is attached to its outer surface.

This allows you to accurately set the sector in which, due to additional reinforcement, a delay in the separation of the plug will be created, which will determine the trajectory of its flight.

The proposed design of a solid propellant rocket engine is illustrated by drawings:

Fig. 1 - General view of the engine;

Fig. 2 - Nozzle plug according to claim 1 of the formula;

Fig. 3 - Nozzle plug according to claim 2 of the formula.

A solid propellant rocket engine works as follows:

When the squib (1) is triggered, its combustion products ignite the igniter (2), which in turn ignites the solid propellant charge (3), the combustion products of which flow through the nozzle path (4). Under the pressure of the combustion products, the plug (5) is separated, and the separation of the plug in the additionally reinforced sector (6) occurs with a delay, as a result of which there is a short-term bending effect on the plug (5) and a deviation of the plug (5) departure trajectory in the direction of its additional reinforcement (6).

This invention makes it possible to ensure the flight of the plug in a given direction, and thereby exclude the collision of the plug with the return vehicle and the launch vehicle.

The engine of this design is planned to be used as part of advanced missile systems and SAS.

Claims (2)

1. A solid propellant rocket engine designed to remove detachable parts of a launch vehicle, containing a housing, a solid propellant charge, an initiation system and a nozzle path located at an angle to the longitudinal axis of the launch vehicle and closed with a plug, which is made of a thin deformable material and has a conical flare, external the surface of which is in contact with the inner surface of the nozzle tract through a sealing layer that ensures adhesion of the plug to the surface of the nozzle tract, characterized in that the end of the plug is additionally reinforced to the surface of the nozzle tract from the side as far as possible from the launch vehicle along an arc S with a length of 0.5 to 1.5 R, where R is the radius of the end of the plug, and the distance L from the end of the nozzle to the end of the plug does not exceed 2R. 2. A solid propellant rocket engine according to claim 1, characterized in that the reinforcement of the plug is made in the form of a deformable bracket, which is a continuation of the conical part of the plug, which completely covers the inner surface of the nozzle path and is attached to its outer surface.

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