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Fuel gas pressurization attitude and orbit control propulsion system based on electric pump

A technology of propulsion system and electric pump, which is applied in the direction of jet propulsion device, machine/engine, rocket engine device, etc., to avoid potential safety hazards and leakage risks and improve safety

Active Publication Date: 2020-11-17
SHANGHAI INST OF SPACE PROPULSION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the gas pressurization system still needs to supply a certain pressure of propellant for the gas generator, and the problem of pressurizing the propellant still needs to be solved

Method used

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  • Fuel gas pressurization attitude and orbit control propulsion system based on electric pump

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Embodiment Construction

[0037] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0038] According to the present invention, an electric pump-based gas pressurization attitude control propulsion system includes a gas generator pressurization module based on an electric pump, an oxidant storage tank, a fuel storage tank, an orbit control engine, an attitude control engine, an electric explosion valve;

[0039] The gas generator pressurization module based on the electric pump is respectively connected with the inlet of the oxidant storage tank and the inlet of the fuel storage tank; ...

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Abstract

The invention provides a fuel gas pressurization attitude and orbit control propulsion system based on an electric pump. The fuel gas pressurization attitude and orbit control propulsion system comprises a fuel gas generator pressurization module based on the electric pump, an oxidizing agent storage tank, a fuel storage tank, an orbit control engine, an attitude control engine and an electric explosion valve. The fuel gas generator pressurization module based on the electric pump is connected with an inlet of the oxidizing agent storage tank and an inlet of the fuel storage tank respectively;an outlet of the oxidizing agent storage tank is connected with the orbit control engine and the attitude control engine respectively after passing through the electric explosion valve; and an outletof the fuel storage tank is connected with the orbit control engine and the attitude control engine after passing through the electric explosion valve. Pressurized gas needed in the attitude and orbit control propulsion system is provided by the fuel gas generator pressurization module based on the electric pump, normal-pressure long-term storage of the pressurized gas can be achieved before thesystem does not work, and potential safety hazards and leakage risks existing in long-term storage of high-pressure gas are avoided.

Description

technical field [0001] The invention relates to the field of aerospace attitude and orbit control power systems, in particular to a gas pressurized attitude and orbit control propulsion system based on an electric pump. Background technique [0002] Attitude control power system One of the important subsystems of the spacecraft provides control force and control torque for the spacecraft's attitude control, orbit transfer, orbit maintenance, orbit correction, orbit entry, deorbit and reentry during flight. [0003] At present, a typical attitude and orbit control power system adopts a gas constant pressure extrusion pressurization system. High-pressure gas is pre-filled and stored in a high-pressure cylinder. Before the system works, it is isolated from the downstream by an electric explosion valve. Pressurizing the tank at a constant pressure completes the propellant supply to the engine. In order to improve the rapid response requirements of spacecraft and reduce the prep...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/50F02K9/56F02K9/58
CPCF02K9/50F02K9/56F02K9/566F02K9/58
Inventor 姜丹丹任建军周明龙潘振兴仲明张舜禹
Owner SHANGHAI INST OF SPACE PROPULSION
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