阅读说明：本技术 一种固体姿控发动机 (Solid attitude control engine ) 是由 余明敏 赵启扬 周子翔 王善金 丁杰 卢迪 胡胜云 胡保朝 张周周 于 2019-10-31 设计创作，主要内容包括：本发明公开了一种固体姿控发动机,涉及航天动力技术领域,包括：燃烧室,其用于固定在舱段上；盖体,其设于燃烧室的端部,用于密封燃烧室并固定在舱段上,且盖体上设有第一管路；以及阀门推力器,其上设有第二管路,且第二管路通过波纹管与第一管路相连。本发明中的固体姿控发动机能适应工作热变形,保证固体姿控发动机推力方向精确,以及燃烧室和阀门推力器之间的高精度固定连接。(The invention discloses a solid attitude control engine, which relates to the technical field of aerospace power and comprises the following components: a combustion chamber for securing to the nacelle section; the cover body is arranged at the end part of the combustion chamber, is used for sealing the combustion chamber and is fixed on the cabin section, and is provided with a first pipeline; and the valve thruster is provided with a second pipeline, and the second pipeline is connected with the first pipeline through a corrugated pipe. The solid attitude control engine can adapt to the working thermal deformation, the accurate thrust direction of the solid attitude control engine is ensured, and the high-precision fixed connection between the combustion chamber and the valve thruster is also ensured.)

1. A solid attitude control engine, comprising:

a combustion chamber (1) for fastening to a cabin section (5);

the cover body (2) is arranged at the end part of the combustion chamber (1), is used for sealing the combustion chamber (1) and is fixed on the cabin section (5), and a first pipeline (21) is arranged on the cover body (2); and

and the valve thruster (3) is provided with a second pipeline (31), and the second pipeline (31) is connected with the first pipeline (21) through a corrugated pipe (4).

2. A solid attitude control engine according to claim 1, characterized in that: the combustion chamber (1) is provided with an installation support lug (11), and the installation support lug (11) is fixed on the cabin section (5) through a first bolt (12).

3. A solid attitude control engine according to claim 2, characterized in that: and a gasket (13) is arranged between the first bolt (12) and the mounting lug (11).

4. A solid attitude control engine according to claim 2, characterized in that: the combustion chamber (1) comprises a plurality of mounting lugs (11) which are arranged at intervals along the circumferential direction of the outer wall of the combustion chamber.

5. A solid attitude control engine according to claim 1, characterized in that: the cover body (2) is further provided with a mounting bracket (22), and the cover body (2) is fixed on the cabin section (5) through the mounting bracket (22).

6. A solid attitude control engine according to claim 5, characterized in that: one end of the mounting bracket (22) is connected with the cover body (2) through threads, and the other end of the mounting bracket is connected with the cabin section (5) through a second bolt (23).

7. A solid attitude control engine according to claim 1, characterized in that: the cover body (2) is of a circular plate structure.

8. A solid attitude control engine according to claim 1, characterized in that: and two ends of the corrugated pipe (4) are respectively welded on the first pipeline (21) and the second pipeline (31).

9. A solid attitude control engine according to claim 1, characterized in that: the first pipeline (21) and the second pipeline (31) are both of a 3D printing structure.

10. A solid attitude control engine according to claim 1, characterized in that: and the valve thruster (3) is provided with a threaded hole and a pin hole for transmitting thrust.

Technical Field

The invention relates to the technical field of aerospace power, in particular to a solid attitude control engine.

Background

The solid attitude control power system is mainly used for attitude control of the spacecraft, and controlling pitching, yawing and rolling of the spacecraft so as to enable the spacecraft to fly along a set track. In order to ensure the accurate thrust direction of the attitude control engine, the charging combustion chamber and the valve thruster need to be fixedly connected with high precision, and due to the fact that the working temperature of the solid attitude control engine is high, the thermal deformation of a pipeline and a valve is large, if the rigidity of the connection between the valve thruster and the charging combustion chamber is too large, the attitude control engine is installed and over-restrained, and the stress of the pipeline is concentrated, and further damage is caused.

At present, a common solid attitude control engine is low in temperature, small in flow of the diameter of a pipeline, small in overall thermal deformation of the engine and free of considering the deformation matching problem during the operation of the engine.

At the present stage, the working temperature and the pressure of the solid attitude control engine are higher and higher, even exceed 1000 ℃, and the integral deformation is large, so that a solid attitude control engine mounting structure needs to be developed, the working thermal deformation can be adapted, the thrust precision of the attitude control engine is not influenced, and the mounting requirement of an aircraft is met.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a solid attitude control engine which can adapt to the working thermal deformation, ensure the thrust direction accuracy of the solid attitude control engine and realize the high-accuracy fixed connection between a combustion chamber and a valve thruster.

In order to achieve the above purposes, the technical scheme adopted by the invention is as follows:

a solid attitude control engine comprising:

a combustion chamber for securing to the nacelle section;

the cover body is arranged at the end part of the combustion chamber, is used for sealing the combustion chamber and is fixed on the cabin section, and is provided with a first pipeline; and

and the valve thruster is provided with a second pipeline, and the second pipeline is connected with the first pipeline through a corrugated pipe.

On the basis of the technical scheme, the combustion chamber is provided with an installation lug which is fixed on the cabin section through a first bolt.

On the basis of the technical scheme, a gasket is further arranged between the first bolt and the mounting support lug.

On the basis of the technical scheme, the combustion chamber comprises a plurality of installation lugs which are arranged along the circumferential direction of the outer wall of the combustion chamber at intervals.

On the basis of the technical scheme, the cover body is further provided with an installation support, and the cover body is fixed on the cabin section through the installation support.

On the basis of the technical scheme, one end of the mounting bracket is connected with the cover body through threads, and the other end of the mounting bracket is connected with the cabin section through a second bolt.

On the basis of the technical scheme, the cover body is of a circular plate structure.

On the basis of the technical scheme, two ends of the corrugated pipe are respectively welded on the first pipeline and the second pipeline.

On the basis of the technical scheme, the first pipeline and the second pipeline are both of a 3D printing structure.

On the basis of the technical scheme, the valve thruster is provided with a threaded hole and a pin hole for transmitting thrust.

Compared with the prior art, the invention has the advantages that:

according to the solid attitude control engine, the corrugated pipe is welded between the first pipeline and the second pipeline, so that the connection rigidity between the valve thruster and the combustion chamber can be ensured not to be overlarge. And the working deformation of the solid attitude control engine can be coordinated, and the safe and firm installation of the solid attitude control engine in the aircraft is realized. Meanwhile, the moment of the mounting support lug and the mounting support can be adjusted, so that the deformation of the combustion chamber in the direction of the mounting support lug can be controlled, the pressure of the metal corrugated pipe for adjusting the deformation is reduced, the thrust direction accuracy of the solid attitude control engine is further ensured, and the high-precision fixed connection between the combustion chamber and the valve thruster is also ensured.

Drawings

FIG. 1 is a schematic structural diagram of a solid attitude control engine according to an embodiment of the present invention;

fig. 2 is a schematic mounting diagram of a mounting lug and a cabin section in the embodiment of the invention.

In the figure: 1-combustion chamber, 11-mounting support lug, 12-first bolt, 13-gasket, 2-cover body, 21-first pipeline, 22-mounting support, 23-second bolt, 3-valve thruster, 31-second pipeline, 4-corrugated pipe and 5-cabin section.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and examples.

Referring to fig. 1, an embodiment of the present invention provides a solid attitude control engine, which includes a combustion chamber 1, a cover 2, a valve thruster 3, and a bellows 4.

Therein, a combustion chamber 1 for fastening to a cabin section 5.

The cover body 2 is arranged at the end part of the combustion chamber 1, is used for sealing the combustion chamber 1 and is fixed on the cabin section 5, and the cover body 2 is provided with a first pipeline 21. The cover body 2 is mainly used for sealing the combustion chamber 1 and realizing ignition, pressure measurement and pipeline connection of the solid attitude control engine.

And the valve thruster 3 is provided with a second pipeline 31, and the second pipeline 31 is connected with the first pipeline 21 through a corrugated pipe 4. In this embodiment, the valve thruster 3 is provided with a threaded hole and a pin hole for transmitting thrust, and the thrust is transmitted to the aircraft through the threaded hole and the pin hole in the valve thruster 3. The first pipeline 21 and the second pipeline 31 are both of a 3D printing structure, and high-temperature fuel gas is communicated to the valve thruster 3 from the combustion chamber 1.

The corrugated pipe 4 in this embodiment is a metal corrugated pipe, which is a special elastic element, and is installed between the first pipeline 21 and the second pipeline 31 by welding, and under the action of temperature and pressure load, the metal corrugated pipe itself can coordinate the deformation of the two ends of the metal corrugated pipe by changing the shape and size.

Referring to fig. 2, in a preferred embodiment, in the present embodiment, the combustion chamber 1 is provided with a mounting lug 11, the mounting lug 11 is fixed on the cabin 5 by a first bolt 12, and the magnitude of the moment of the mounting lug 11 can be adjusted by the first bolt 12. The combustion chamber 1 is fixed by the mounting lugs 11, so that the flying overload and the vibration load of the aircraft can be well resisted. For better effect, the combustion chamber 1 includes a plurality of mounting lugs 11 spaced circumferentially along its outer wall.

Further, a gasket 13 is arranged between the first bolt 12 and the mounting lug 11. The pretightening force of the first bolt 12 in the embodiment is smaller, and the pretightening force is used for controlling the deformation of the combustion chamber 1 and reducing the pressure of the metal corrugated pipe for adjusting the deformation.

In a preferred embodiment, the cover 2 is a circular plate structure, and the cover 2 is further provided with a mounting bracket 22, and the cover 2 is fixed to the cabin 5 by the mounting bracket 22. Specifically, the mounting bracket 22 is connected to the cover 2 at one end thereof by a screw thread and connected to the deck section 5 at the other end thereof by a second bolt 23. And the moment of the mounting bracket 22 can be adjusted by the second bolt 23. In this embodiment, the preload of the second bolt 23 is large. Thus, by controlling the pretightening force of the first bolt 12 and the second bolt 23, the moment of the mounting lug 11 and the mounting bracket 22 can be adjusted, and the deformation of the combustion chamber 1 towards the mounting lug 11 can be controlled, so that the pressure of the adjustment deformation of the metal corrugated pipe is reduced.

The following is a description of the principles of the present invention: after the combustion chamber 1 and the valve thruster 3 are firmly installed, the bellows releases the thermal stress of the solid attitude control engine in the working process through self strong deformation coordination capacity and self shape and size change along with the fact that the working temperature and pressure of the solid attitude control engine are higher and higher. Meanwhile, the pretightening force of the first bolt 12 and the second bolt 23 can be adjusted, so that the moments of the mounting support 11 and the mounting bracket 22 are controlled, the purpose of deforming the combustion chamber 1 towards the mounting support 11 is achieved, and the pressure for adjusting the deformation of the metal corrugated pipe can be reduced. The two components supplement each other, and can better adapt to the working thermal deformation.

In summary, the bellows 4 is welded between the first pipeline 21 and the second pipeline 31 of the solid attitude control engine of the present invention, so that the connection rigidity between the valve thruster 3 and the combustion chamber 1 is not too high. And the working deformation of the solid attitude control engine can be coordinated, and the safe and firm installation of the solid attitude control engine in the aircraft is realized. Meanwhile, the moment of the mounting support 11 and the mounting support 22 can be adjusted, so that the deformation of the combustion chamber 1 towards the mounting support 11 can be controlled, the pressure of the metal corrugated pipe for adjusting the deformation is reduced, the thrust direction accuracy of the solid attitude control engine is further ensured, and the high-precision fixed connection between the combustion chamber 1 and the valve thruster 3 is also ensured.

The present invention is not limited to the above-described embodiments, and it will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements are also considered to be within the scope of the present invention. Those not described in detail in this specification are within the skill of the art.