RU2459104C1 - Thrust cut-off assembly of solid-propellant rocket engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: thrust cut-out assembly includes reverse thrust nozzle socket equipped with flange and covered with the plug fixed with cams or balls with gate valve contacting them and forming gate valve cavity which is interconnected with pyrocartridge. Gate valve cavity is formed around the flange of section of reverse thrust nozzle socket. Plug together with pusher installed with possibility of longitudinal movement in annular groove is made inside flange. Annular groove is connected as to gas to gate valve cavity, and gate valve is provided with limit stop.

EFFECT: invention allows improving the reliability of thrust cut-off assembly actuation.

2 cl, 4 dwg

Description

The invention relates to rocket technology and can be used to create a node cut-off thrust (FRA) rocket engine of solid fuel (solid propellant rocket engine).

It is known that solid propellant rocket engines may contain traction cutoff nodes [Solid rocket engine designs / Under total. ed. L.N. Lavrova. - M.: Engineering, 1993. - 215 p., Ill., Section 4.2, page 169]. A typical FEP contains a counterbolt nozzle mounted on a solid-propellant rocket engine (for example, on the front bottom of the housing), closed by a plug fixed by a lock, giving a command to operate which causes the plug to be knocked out by chamber pressure.

The closest in technical essence and the achieved positive effect to the proposed invention is a node for cutting off the thrust of a rocket engine of solid fuel [RF patent No. 2403428]. FEP contains a socket mounted on the rocket engine of a solid fuel anti-draft nozzle, equipped with a flange and closed by a plug fixed by cams (or balls) with a shutter in contact with them, forming a shutter cavity that is in communication with the squib. The disadvantage of the present FEP is the need for a relatively high value (tens of atmospheres) of the chamber pressure for reliable knocking out of the plug. If the requirement for its reliable operation at the moment when the value of the intracameral pressure is 3-10 kg / cm ^{2 is} presented to the FEP, then the action on the plug of low intracameral pressure may not be enough to overcome the frictional force of the sealing unit of the plug. Killing of the stub will either not occur, or it will occur with an unacceptable time delay.

An object of the present invention is to increase the reliability of the operation of the traction cutoff assembly.

The essence of the invention lies in the fact that in the node for cutting off the thrust of a rocket engine of solid fuel, containing a bell of the nozzle of the anti-throttle, equipped with a flange and closed by a plug fixed by cams (or balls) with a shutter in contact with them, forming a shutter cavity that is in communication with the igniter, a shutter cavity formed around the flange portion of the flare of the counter-nozzle nozzle, while the plug is connected to a pusher mounted with the possibility of longitudinal movement in the annular groove made oh inside the flange. The annular groove is gas-connected with the shutter cavity. The shutter can be equipped with a travel stop.

The technical result is achieved by forcing the plug out by means of a pusher, which is exerted by the pressure of the combustion products of the same squib from the side of the annular groove, which ensures the release of the shutter when the plug is released.

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 FEP in the initial state;

figure 2 shows the FPS at the beginning of operation, when the shutter reaches the stroke limiter;

figure 3 shows the beginning of the forced ejection of the stub;

figure 4 shows the UOT operating in the mode of cutoff thrust.

The node for cutting off the thrust of the rocket engine of solid fuel contains mounted on the solid propellant solid-propellant rocket engine 1 (for example, on the front bottom of the solid propellant solid propellant rocket engine body 1) a bell 2 of the anti-draft nozzle. The bell 2 of the anti-draft nozzle is provided with a flange 3 made around its slice. The bell 2 of the anti-draft nozzle is closed by a plug 4. The plug 4 is fixed with cams 5 (or balls), mounted with the possibility of radial movement in the windows 6, made in the flange 3 (windows 6 are shown in figure 4). A cam 7 is contacted by a valve 7 enclosing them, axially movable on the flange 3 and the bell 2. A shutter cavity 8 is formed around the portion of the flange 3 of the bell 2 of the counter-nozzle by the shutter 8. The shutter cavity 8 is in communication with the squib 9. The cap 4 is connected with a pusher 10 mounted with the possibility of longitudinal movement in the annular groove 11. In the flange 3, channels 12 are made providing gas connection of the annular groove 11 with the shutter cavity 8. The shutter 7 is equipped with a travel stop 13.

The device operates as follows. When starting the solid propellant rocket motor 1 and increasing the internal chamber pressure, the plug 4 remains in its original state due to the locking of the cams 5 by the shutter 7. At any time during operation of the solid propellant rocket motor (including at low internal chamber pressure), a command can be issued to cut off the thrust. The pressure in the shutter cavity 8 of the combustion products from the squib 9 when it is pressed, presses the shutter 7 until it stops in the travel stop 13 (Fig.2). The cams 5 are unlocked. The pressure in the annular groove 11 also increases, because it is communicated by channels 12 with a shutter cavity 8. The pressure in the annular groove 11 acts on the plunger 10. The plunger 10 pulls the plug 4 out of its original position, regardless of whether or not the chamber pressure acts on the plug 4 (Fig. 3). The cams 5 are thus forced out in the radial direction. As a result, the plug 4 together with the pusher 10 is thrown out, bringing the node cutoff thrust in working condition (figure 4).

The technical and economic efficiency of the present invention, in comparison with the prototype, for which the thrust cut-off unit of the rocket engine of solid fuel [RF patent No. 2403428] is selected, is to increase the reliability of operation of the thrust cut-off node.

Claims (2)

1. The site of cut-off thrust of a rocket engine of solid fuel, containing a bell nozzle anti-throttle, equipped with a flange and closed by a plug fixed by cams (or balls) with a shutter in contact with them, forming a shutter cavity, which is in communication with the squib, characterized in that the shutter cavity is formed around the counter-nozzle socket portion of the nozzle of the flange associated with the flange, wherein the plug is connected to a pusher mounted with the possibility of longitudinal movement in an annular groove made inside the flange, m gazosvyazana annular groove with the gate cavity. 2. Node thrust shutoff rocket engine of solid fuel according to claim 1, characterized in that the shutter is equipped with a travel stop.

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