CN109162830B

CN109162830B - Novel rotating shaft structure of rocket engine capable of swinging

Info

Publication number: CN109162830B
Application number: CN201810776770.3A
Authority: CN
Inventors: 陈明亮; 刘超; 殷艳媚; 韩冲; 陈师; 刘淑群
Original assignee: Shanghai Institute of Space Propulsion
Current assignee: Shanghai Institute of Space Propulsion
Priority date: 2018-07-13
Filing date: 2018-07-13
Publication date: 2020-07-28
Anticipated expiration: 2038-07-13
Also published as: CN109162830A

Abstract

The invention discloses a novel rotating shaft structure of a rocket engine capable of swinging, which comprises a rotating shaft, a shaft cover plate and a shaft tube nozzle, wherein the lower end of the rotating shaft and the shaft cover plate are welded to form a propellant liquid collection cavity channel in the rotating shaft; the upper end of the rotating shaft is provided with a key interface for connecting a motor for providing torque, a bearing interface is arranged below the upper key interface, two sections of sealing surfaces are arranged below the bearing interface, the two sections of sealing surfaces are connected with the dynamic sealing structure, and a plurality of propellant inlets are arranged between the two sections of sealing surfaces; the rotating shaft is welded with the shaft tube mouth, and the propellant flows into the propellant liquid collecting cavity channel from the propellant inlet and flows out from the shaft tube mouth. The joint degree of the rotating shaft structure and the convergence section of the engine combustion chamber is high, and the welding quality is favorably improved; the rotating shaft structure of the invention has the function of a propellant flow channel, so that the engine has compact structure and attractive appearance; for the engine, the swinging hose can be eliminated, and a metal hard pipe is adopted, so that the arrangement of a thermal control device for the engine is facilitated.

Description

Novel rotating shaft structure of rocket engine capable of swinging

Technical Field

The invention relates to the technical field of spacecraft propulsion systems, in particular to a novel rotating shaft structure of a rocket engine capable of swinging.

Background

With the continuous development of the aerospace industry, the development requirements of spacecrafts such as carrier rockets, satellites and the like on multifunctional rocket engines are increasing day by day, and the swinging engine is an important development direction of the multifunctional rocket engines. According to the requirements of track transfer or attitude control, the swinging engine can swing in the corresponding direction, so that the thrust vector deflects to generate the required control force.

The rocket engines at the initial stage are all in fixed structural layout and do not have the swinging function. With the progress of engine technology, the swing engine with the surrounding type metal hose layout is widely applied, the swing hose is arranged on the propellant supply pipeline to keep continuous propellant supply during the swing work of the engine, and the layout of the swing engine has the advantages of simple structural layout and easy engineering realization, but has larger outline size, loose layout and higher requirement on the reliability of the swing hose, and cannot fundamentally solve the problem of thermal control implementation of the hose. Based on the rotating shaft dynamic sealing technology, a layout method of a swinging engine with a shaft sleeve type metal hard pipe layout is provided, the swinging function of the engine is realized by integrating a propellant flow channel and an engine swinging structure, the problem of thermal control implementation is solved, the pipeline structure is further simplified, and the swinging working reliability is improved.

In view of the technical current situation at home and abroad, the rotating shaft of the swinging rocket engine only has the functions of structural support and swinging torque transmission, is mainly applied to the swinging engine with the surrounding metal hose layout, and cannot be applied to the swinging engine with the shaft sleeve type metal hard pipe layout.

Disclosure of Invention

In view of the above requirements, the invention provides a novel rotating shaft structure of a rocket engine capable of swinging, which can be welded and fixed with a convergent section of an engine combustion chamber, and can integrate the functions of torque transmission of a servo motor and a propellant flow channel.

The invention is realized by the following technical scheme:

a novel rotating shaft structure of a rocket engine capable of swinging comprises a rotating shaft, a shaft cover plate and a shaft tube nozzle, wherein the lower end of the rotating shaft and the shaft cover plate are welded to form a propellant liquid collecting cavity channel in the rotating shaft; the upper end of the rotating shaft is provided with a key interface for connecting a motor for providing torque, a bearing interface is arranged below the key interface, two sections of sealing surfaces are arranged below the bearing interface, the two sections of sealing surfaces are connected with a dynamic sealing structure, and a plurality of propellant inlets are arranged between the two sections of sealing surfaces; the rotating shaft is welded with the shaft tube mouth, and the propellant flows into the propellant liquid collecting cavity channel from the propellant inlet and flows out from the shaft tube mouth.

Further, the types of key interfaces include spline, flat key, and wedge key.

Furthermore, the bearing interface is an outer cylindrical surface, and the outer cylindrical range phi of the bearing interface is 10-phi 50 mm.

Furthermore, the excircle range of the two sections of sealing surfaces is phi 15-phi 55mm, and the roughness precision of the sealing surfaces is Ra0.1-1.6.

Further, the welding interface is arranged below the rotating shaft and attached to a convergence section of the engine combustion chamber, the welding interface is a revolution surface, and the ranges of the revolution radius R2 and the revolution radius R3 are 30-150 mm.

Furthermore, the propellant inlet is provided with a plurality of radial holes, the number of the holes ranges from 3 to 9, and the diameter of the holes ranges from phi 3 to phi 9 mm; the aperture range of the propellant outlet is phi 5-phi 20 mm.

Due to the adoption of the technical scheme, the invention has the following advantages:

1) the joint degree of the rotating shaft structure and the convergence section of the engine combustion chamber is high, and the welding quality is favorably improved; 2) the rotating shaft structure has the function of a propellant flow channel, so that the engine is compact in structure and attractive in appearance; 3) for the engine, the swinging hose can be eliminated, and a metal hard pipe is adopted, so that the arrangement of a thermal control device for the engine is facilitated.

The invention can be applied to a swinging engine with a shaft sleeve type metal hard pipe layout, integrates a propellant flow channel and an engine swinging structure, realizes the swinging function of the engine, solves the problem of thermal control implementation, further simplifies the pipeline structure and improves the reliability of swinging work.

Drawings

Fig. 1 is a schematic structural diagram of an embodiment of the present invention.

Fig. 2 is a functional schematic diagram of parts of the rotating shaft 1 in fig. 1.

Fig. 3 is a schematic view of the surface of revolution of the rotating shaft 1 in fig. 1.

Fig. 4 is a schematic view of fig. 3 taken along direction a.

In the figure: 1-rotating shaft, 2-shaft cover plate, 3-shaft pipe nozzle; a 4-key interface; 5-a bearing interface; 6-sealing surface; 7-propellant inlet; 8-welding an interface; 9-propellant outlet.

Detailed Description

The present invention will be described in detail with reference to specific examples.

The embodiment of the invention provides a novel rotating shaft structure of a rocket engine capable of swinging, and the rotating shaft structure comprises a rotating shaft 1, a shaft cover plate 2 and a shaft tube mouth 3, wherein the lower end of the rotating shaft 1 is welded with the shaft cover plate 2 to form a propellant liquid collection cavity channel in the rotating shaft; the upper end of the rotating shaft 1 is provided with a key interface 4 for connecting a motor for providing torque, a bearing interface 5 is arranged below the key interface, two sections of sealing surfaces 6 are arranged below the bearing interface, the two sections of sealing surfaces are connected with a dynamic sealing structure, and a plurality of propellant inlets 7 are arranged between the two sections of sealing surfaces; the rotating shaft 1 is welded with the shaft tube mouth 3, and the propellant flows into the propellant liquid collection cavity channel from the propellant inlet and flows out from the shaft tube mouth 3.

Referring to fig. 2, the maximum outer diameter of the rotating shaft 1 is 50mm, and the total height is 120mm, and the rotating shaft comprises a key interface, a bearing interface, a sealing surface, a welding interface, a propellant inlet and a propellant outlet. The key interface adopts involute type external splines, and the number of teeth of the splines is 36, so that the clearance between the key interface and the motor interface is favorably reduced, and the accuracy of the swing angle of the engine is improved. The bearing interface is a phi 25mm excircle, and the mounting precision of the bearing is controlled through dimensional tolerance. The sealing surface is two sections of phi 40 outer circular surfaces, the roughness precision requirement of the sealing surface is not lower than Ra0.2, and the sealing surface engine is connected in a dynamic sealing structure. 6 radial holes are uniformly distributed between the two sections of sealing surfaces, the aperture is phi 6, and the propellant flows into a liquid collection cavity channel in the rotating shaft through the radial holes. The propellant outlet is communicated with the shaft nozzle 3.

Referring to fig. 3, the welding interface of the rotating shaft 1 is a revolution surface, which is similar to the excircle surface of a bowl in daily life, and is attached to the convergent section of the combustion chamber of the engine, so that the position precision of the rotating shaft after welding can be improved. In this case R1 is 154mm, R2 is 64mm and R3 is 52 mm.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.

Claims

1. A novel rotating shaft structure of a rocket engine capable of swinging is characterized by comprising a rotating shaft (1), a shaft cover plate (2) and a shaft tube nozzle (3), wherein the lower end of the rotating shaft (1) is welded with the shaft cover plate (2) to form a propellant liquid collection cavity channel inside the rotating shaft; the upper end of the rotating shaft (1) is provided with a key interface for connecting a motor for providing torque, a bearing interface is arranged below the key interface, two sections of sealing surfaces are arranged below the bearing interface, the two sections of sealing surfaces are connected with a dynamic sealing structure, and a plurality of propellant inlets are arranged between the two sections of sealing surfaces; the rotating shaft (1) is welded with the shaft nozzle (3), and propellant flows into the propellant liquid collecting cavity channel from the propellant inlet and flows out from the shaft nozzle (3);

a welding interface is arranged below the rotating shaft (1) and is attached to a convergent section of an engine combustion chamber, the welding interface is a revolution surface, and the ranges of the revolution radiuses R2 and R3 are 30-150 mm;

the bearing interface is an outer cylindrical surface, and the outer cylindrical range phi of the bearing interface is 10-phi 50 mm.

2. The novel shaft structure of a shakable rocket engine as claimed in claim 1, wherein the types of key interfaces include spline, flat key and wedge key.

3. The novel rotating shaft structure of the oscillating rocket engine according to claim 1, wherein the excircle range of the two sections of sealing surfaces is phi 15-phi 55mm, and the roughness precision of the sealing surfaces is Ra0.1-1.6.

4. The novel rotating shaft structure of the oscillating rocket engine according to claim 1, wherein the propellant inlets are a plurality of radial holes, the number of the holes ranges from 3 to 9, and the diameter of the holes ranges from Φ 3 to Φ 9 mm; the aperture range of the propellant outlet is phi 5-phi 20 mm.