RU2657400C1 - Liquid rocket engine with a nozzle of carbon-carbon composite material (cccm) - Google Patents

Abstract

FIELD: motors and pumps.

SUBSTANCE: invention relates to the thrust vector control of liquid rocket engines (LRE). LRE contains a chamber with a cooled supersonic part of a nozzle, an uncooled nozzle of a carbon-carbon composite material interconnected by a detachable joint, steering assemblies and a frame, in accordance with the invention, on the cooled part of the nozzle and the uncooled nozzle there are made round-shaped beads and having equidistant surfaces with a graphite coating, between which in two mutually perpendicular-disposed planes four round-shaped deflectors of carbon-carbon composite material are installed, the internal and external surfaces of which are identical in shape to the surfaces of the beads with the axis of rotation, located on the axis of the cooled part of the nozzle, and with the end surface of the deflector, which is a continuation of the profiled surface of the nozzle when they are in their original position.

EFFECT: invention provides a reduction in the weight of the structure, increase the efficiency of control and reduction in the effort on the steering units.

1 cl, 5 dwg

Description

The invention relates to rocket engines in which to control the thrust vector in flight, various controls are used located at the nozzle exit or inside it.

It is known that at the dawn of the development of liquid-propellant rocket engines (LRE) in the German FAU-2 rocket, gas rudders made of graphite and located at the nozzle exit were used to control the thrust vector. When these rudders rotate around the axis with increasing leakage area, a lateral force is created. The development of rocketry required the creation of more reliable and efficient thrust vector controls.

Known gas rudders according to US patent No. 3251555 and from the book "Design of solid propellant rocket engines" edited by L.N. Lavrov. - M.: Mechanical Engineering, 1993, p. 145, which are located in the cavity of the expiring jet.

The disadvantage is the working condition of these gas rudders:

- thermal and erosive effects of high-temperature gas flow during the entire time the engine is running;

- the presence of mechanical loads from supersonic flow during the entire time the engine is running.

Known gas steering wheel of a rocket engine containing a pen, a plate with a cylindrical protrusion, a shaft, the shank of which, with the help of an annular groove through a spacer ring, is mounted on the protrusion of the plate. In this design, the plate and pen are made of different parts (RF patent No. 2251013, F02K 9/80, 2003).

The disadvantage of this design is:

- low reliability of the controls, since they are always in the high-temperature gas stream, which leads to their erosion and rapid burnout;

- the presence of gas rudders all the time in the stream is accompanied by the presence of their drag, which reduces the specific energy characteristics;

- the impossibility of obtaining a large amount of lateral control effort due to the small working surface of the controls;

- significant effort on the steering organs;

- the need to have at the nozzle exit four gas rudders and four drives for turning them into a gas stream.

Known liquid rocket engine with a deflector at the nozzle exit, selected for the prototype, containing a chamber with a cooled supersonic part of the nozzle, uncooled nozzles made of carbon-carbon composite material (CCCM), steering units, a frame and a deflector made of CCCM, consisting of two parts interconnected by flange connection with thermally expanded graphite seal.

The inner surface of the deflector has a spherical shape equidistant to the spherical surface of the uncooled nozzle, and the eyes are made on the outer surface for fastening to the steering units (RF patent No. 2579294, F02K 9/80, 2015).

The disadvantage of this design is:

- increased mass due to the need to perform a spherical surface for installing the deflector and the location of the deflector on the nozzle exit of the uncooled nozzle;

- low efficiency of the control effort when the deflector is located on the nozzle exit. In this case, the bulk of the effort is realized by increasing the pressure on the surface of the deflector, and in the nozzle area in front of the deflector, the pressure increase is insignificant, which requires more effort on the steering units.

The present invention eliminates these disadvantages of the prototype and solves the technical problem of reducing the mass of the structure, increasing the efficiency of the control effort and reducing the effort on the steering units.

The stated technical problem is solved in that in an LRE containing a chamber with a cooled supersonic part of the nozzle, uncooled nozzles made of carbon-carbon composite material interconnected by a detachable connection, steering units and a frame, according to the statement, on the cooled part of the nozzle and uncooled nozzle round shoulders are made and have equidistant surfaces with a graphite coating, between which four deflectors are installed in two mutually perpendicular planes round shape of carbon-carbon composite material, the inner and outer surfaces which are identical in shape turners surfaces, with an axis of rotation situated on the axis of the cooled portion of the nozzle and the end surface of the deflector, which is a continuation of the profiled surface of the nozzle when in a rest position.

This performance of the rocket engine allows you to implement the following processes:

- when a lateral control force is not required, the deflector sectors are in the initial position and only the end surface flush with the gas is flush with the part of the nozzle surface;

- if it is necessary to obtain lateral force in a certain plane, a command is sent to the corresponding steering units. The steering unit of the deflector sector is immersed in the gas stream. Lateral control effort will be realized from two components: efforts from pressure distribution on the deflector surface and efforts from pressure increase in the nozzle area in front of the deflector.

When the deflector is located between the cooled supersonic part of the nozzle and the uncooled nozzle from the CCM, the proportion of the force from increasing the pressure in the nozzle zone in front of the deflector will be significantly higher than if the deflector is placed on the nozzle exit of the uncooled nozzle. In addition, the increased pressure on the surface of the deflector allows you to immerse it in the gas stream at a smaller angle, which reduces the distance of application of the total control force and thereby reduces the control force in the steering units.

The essence of the invention is illustrated by the circuits shown in FIG. 1, 2, 3, 4, 5.

The liquid propellant rocket engine (Fig. 1) contains a chamber with a cooled part of the nozzle 1, a round collar on the nozzle 2, a round collar 3 on the nozzle 4, a deflector 5 located between the equidistant surfaces of the collars with graphite coating of these surfaces, eyes (brackets) 6, steering units 7 engine frame 8.

In FIG. 2 shows the connection between the chamber and the cooled part of the nozzle 1 with the uncooled nozzle 4 by means of a bolted connection 9.

In FIG. 3 shows the location of four deflectors 5 in two mutually perpendicularly-located planes relative to the chamber with the cooled part of the nozzle 1.

In FIG. 4 shows a physical picture of lateral force production. When the deflector 5 is immersed in a gas stream behind the shock wave A on the surface of the cooled part of the nozzle of the chamber 1 adjacent to the deflector 5, a zone with an increased pressure Pi is formed. In this case, the pressure Pg acts on the surface of the deflector 5.

In FIG. 5 shows a zone B with increased pressure in front of the deflector 5.

LRE with thrust vector controls (deflector) works as follows.

On command from the control system of the PH, a signal is sent to the corresponding steering units 7, which through the eye 6 turn the deflector 5 around the axis of the cooled part of the nozzle of the chamber 1. The corresponding deflector 5 is immersed in a stream of gas flowing from the nozzle of the chamber 1. As a result of immersion of the deflector 5 in the gas the jet on the surface of the deflector and the nozzle part adjacent to the deflector increases the static pressure, which is significantly higher than the pressure on the opposite part of the nozzle, resulting in a lateral control force.

Thus, the use of a CCM deflector located between the cooled supersonic part of the nozzle and the uncooled CCM nozzle makes it possible to obtain an increased control force, reduce axial thrust losses when receiving lateral force, reduce the force on the steering units and reduce the weight of the structure by changing the location of the deflector relatively uncooled nozzle.

Claims (1)

A liquid-propellant rocket engine comprising a chamber with a supersonic cooled nozzle part, uncooled nozzles made of carbon-carbon composite material interconnected by a detachable connection, steering units and a frame, characterized in that rounded collars are made on the cooled part of the nozzle and the uncooled nozzle and having equidistant graphite-coated surfaces between which four carbon-shaped round deflectors are installed in two mutually perpendicularly spaced planes d-carbon composite material, the inner and outer surfaces of which are identical in shape to the surfaces of the shoulders, with the axis of rotation located on the axis of the cooled part of the nozzle, and with the end surface of the deflector, which is a continuation of the profiled surface of the nozzle when they are in the initial position.

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