A low temperature attitude control engine propellant supply pipeline system

A technology of attitude control and supply pipeline, which is applied in the direction of machine/engine, rocket engine device, jet propulsion device, etc., which can solve the problems such as the inability to propel the service life of the system and the inability of the cooling structure to adjust the pre-cooling under multiple working conditions.

Active Publication Date: 2021-07-06
SHANGHAI INST OF SPACE PROPULSION
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The cooling structure of the engine cannot perform multi-working condition pre-cooling adjustment capabilities, and cannot promote the service life of the system

Method used

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  • A low temperature attitude control engine propellant supply pipeline system
  • A low temperature attitude control engine propellant supply pipeline system
  • A low temperature attitude control engine propellant supply pipeline system

Examples

Experimental program
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Embodiment 1

[0029] A low-temperature attitude control engine propellant supply pipeline system, including a low-temperature fuel annular pipeline 1, a low-temperature oxidant annular pipeline 2, a low-temperature heat insulation bracket 3, a low-temperature attitude control engine 4, a control valve 5, and a throttle orifice 6. The low-temperature fuel annular pipeline 1 and the low-temperature oxidant annular pipeline 2 are connected and fixed to the propulsion system assembly structure through the low-temperature heat insulation bracket 3, and the low-temperature attitude control engine 4 is connected to the low-temperature fuel annular pipeline through the low-temperature fuel control valve 41. The pipeline 1 is connected to the low-temperature oxidant annular pipeline 2 through the low-temperature oxidant control valve 42. The end of the low-temperature fuel annular pipeline 1 is provided with multiple bifurcated branches, and each bifurcated branch is provided with a control valve. 5....

Embodiment 2

[0033] Embodiment 2 is a preferred example of embodiment 1:

[0034] In Example 2, the surfaces of the low-temperature fuel annular pipeline 1 and the low-temperature oxidant annular pipeline 2 are covered with foam material 8 and multi-layer heat insulating material 9 . The foam material 8 can be polyurethane foam or airgel foam, and the multi-layer insulation material 9 is generally composed of high-reflectivity materials (usually double-sided aluminized film) and polyester nets laid alternately.

[0035] The low temperature heat insulation bracket 3 is composed of parts using different materials, including the pipeline fixing part 31 and the assembly connecting part 32. The pipeline fixing part 31 is a waist-shaped structure with a through hole in the middle, and the pipeline fixing part 31 is made of low temperature resistant materials. The assembly connection part 32 is an I-shaped structure with a vertical waist-shaped hole in the middle, the bottom of the assembly conne...

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Abstract

The invention provides a low-temperature attitude control engine propellant supply pipeline system, including a low-temperature fuel annular pipeline, a low-temperature oxidant annular pipeline, a low-temperature heat insulation bracket, a low-temperature attitude control engine, a control valve group, and a throttle orifice group; the low-temperature fuel annular pipeline and the low-temperature oxidant annular pipeline are fixed to the general assembly structure of the propulsion system through a low-temperature heat-insulating bracket, and the top of the low-temperature attitude control engine is connected to the low-temperature fuel annular pipeline through a low-temperature fuel control valve. The oxidant control valve is connected with the low-temperature oxidant annular pipeline, and the ends of the low-temperature fuel annular pipeline and the low-temperature oxidant annular pipeline are equipped with bifurcated branches. Control valves are set on the bifurcated branches, and different apertures are connected in series behind the control valves. throttle orifice. The supply pipeline system of the present invention can solve the problems of large heat leakage of low-temperature propellant during pipeline transportation, control of low-temperature attitude control engine inlet conditions, and adjustment of propellant pre-cooling consumption under multiple working conditions.

Description

technical field [0001] The invention relates to the technical field of liquid rocket engines, in particular to a low-temperature attitude control engine propellant supply pipeline system. Background technique [0002] With the development of aerospace science and technology, large-scale space missions such as manned moon landing and manned Mars landing have been put on the agenda, which also puts forward higher requirements for space propulsion systems. Low-temperature propellant combinations such as liquid oxygen / liquid hydrogen and liquid oxygen / methane have been widely used in launch vehicles and upper stages due to their high specific impulse performance, non-toxic and non-polluting, potential for in-situ resource utilization, and low cost. . Cryogenic propellants are considered to be the most economical and efficient chemical propellants for space entry and orbital transfer. For the attitude control engine or its unit, the temperature of the low-temperature propellant...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/56F02K9/58F02K9/44
CPCF02K9/44F02K9/56F02K9/58
Inventor 程诚田桂熊靖宇郭曼丽刘国权周国峰周海清
Owner SHANGHAI INST OF SPACE PROPULSION
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