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Attitude and orbit control integrated propelling system pressurized by electric pump and spacecraft

A technology of pressurization system and electric pump, applied in the field of spacecraft, can solve the problems of complex structure and redundancy of the propellant supply system, and achieve the effects of enhancing the ability to deal with emergencies, alleviating the complex structure, and saving weight and space.

Active Publication Date: 2022-03-25
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In view of this, the object of the present invention is to provide an integrated propulsion system and spacecraft with an electric pump pressurization attitude and orbit control, so as to alleviate the technical problems of complex structure and more redundancy in the propellant supply system existing in the prior art

Method used

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  • Attitude and orbit control integrated propelling system pressurized by electric pump and spacecraft
  • Attitude and orbit control integrated propelling system pressurized by electric pump and spacecraft
  • Attitude and orbit control integrated propelling system pressurized by electric pump and spacecraft

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Embodiment 1

[0023] figure 1 It is a schematic diagram of an electric pump supercharged integrated propulsion system with attitude and orbit control provided according to an embodiment of the present invention. Such as figure 1 As shown, the system includes five subsystems, which are: extrusion pressurization system 100 , anhydrous hydrazine supply system 200 , dinitrogen tetroxide supply system 300 , orbit control thrust chamber 400 and attitude control thrust chamber 500 .

[0024] Such as figure 1 As shown, the anhydrous hydrazine supply system 200 and the dinitrogen tetroxide supply system 300 share a squeeze pressurization system 100 .

[0025] Specifically, the extrusion pressurization system 100 is used for extrusion and blowing of the anhydrous hydrazine supply system 200 and the dinitrogen tetroxide supply system 300 .

[0026] The anhydrous hydrazine supply system 200 and the dinitrogen tetroxide supply system 300 respectively supply fuel and oxidant to the orbit control thrus...

Embodiment 2

[0048] image 3 It is a schematic diagram of another electric pump pressurized attitude-orbit control integrated propulsion system provided according to an embodiment of the present invention. Such as image 3 As shown, the system includes 5 subsystems, namely: extrusion pressurization system 100 , hydrogen peroxide supply system 600 , kerosene supply system 700 , orbit control thrust chamber 400 and attitude control thrust chamber 500 .

[0049] Such as image 3 As shown, the hydrogen peroxide supply system 600 and the kerosene supply system 700 share a squeeze pressurization system 100 .

[0050] Specifically, the squeezing pressurization system 100 is used for squeezing and blowing off the hydrogen peroxide supply system 600 and the kerosene supply system 700 .

[0051] The hydrogen peroxide supply system 600 and the kerosene supply system 700 supply oxidant and fuel to the orbit control thrust chamber 400 respectively.

[0052] The hydrogen peroxide supply system 600 i...

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Abstract

The invention provides an attitude and orbit control integrated propelling system pressurized by an electric pump and a spacecraft. The attitude and orbit control integrated propelling system comprises an extrusion type pressurization system, an anhydrous hydrazine supply system, a nitrogen tetroxide supply system, an orbit control thrust chamber and an attitude control thrust chamber, the anhydrous hydrazine supply system and the nitrogen tetroxide supply system share the extrusion type pressurization system; the extrusion type pressurization system is used for extrusion and blowing of the anhydrous hydrazine supply system and the nitrogen tetroxide supply system; the anhydrous hydrazine supply system and the nitrogen tetroxide supply system are used for supplying fuel and an oxidizing agent to the orbit control thrust chamber respectively; and the anhydrous hydrazine supply system is also used for supplying a monopropellant to the attitude control thrust chamber. The technical problems that in the prior art, a propellant supply system is complex in structure and large in redundancy are solved.

Description

technical field [0001] The invention relates to the technical field of spacecraft, in particular to an integrated propulsion system with attitude-orbit control and a spacecraft boosted by an electric pump. Background technique [0002] With the continuous complexity of space missions and the extension of the life of spacecraft, the overall design puts forward higher and higher requirements on the engine system. The attitude control engine system is a key system to maintain and adjust the orbit and attitude of the spacecraft and ensure the normal operation of the spacecraft. The working environment of weightlessness, radiation, and high vacuum in space, as well as the long-term working premise of the spacecraft in orbit, require the attitude and orbit control engine to have extremely high reliability, a very wide thrust range, and the ability to start multiple times and pulse work , extremely long standby time and total working time. [0003] The attitude control engine and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/50F02K9/46F02K9/42F02K9/62B64G1/40
CPCF02K9/50F02K9/46F02K9/425F02K9/62B64G1/402B64G1/401
Inventor 俞南嘉周闯蔡国飙师浩然龚昊杰
Owner BEIHANG UNIV
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