Low-pressure liquefied gas thrust generating method for spacecraft

A generation method and technology of liquefied gas, which is applied in the direction of aerospace vehicle propulsion system devices, aerospace vehicle guidance devices, etc., can solve the problems of large occupied volume, low integration of thrust generation modules, unstable thrust, etc., and achieve the occupied volume The effect of small size, shortening the development cycle and increasing safety

Active Publication Date: 2015-08-12
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since the gaseous liquefied gas propellant is very easy to liquefy, the thrust generated by this thrust generation method is relatively unstable
And the whole thrust generation module is not highly integrated and occupies a large volume

Method used

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  • Low-pressure liquefied gas thrust generating method for spacecraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0036] Take butane as the propellant as an example to describe the thrust generation process of low-pressure liquefied gas,

[0037] Step (1), inject liquid butane into the storage tank 1 through the addition and discharge valve 3 for storage; afterwards, it can be directly loaded.

[0038] Step (2), the storage tank 1 is heated by the first heater 7. When the first temperature sensor 6 measures that the gas temperature in the storage tank 1 reaches 40°C, the self-locking valve 4 is opened to make the liquid butane in the storage tank 1 Enter the inlet of solenoid valve 5-1.

[0039] Step (3): Heat the thrust chamber 5-4 by the second heater 5-3, and turn off the second heater 5-3 when the second temperature sensor 5-3 measures that the temperature of the thrust chamber 5-4 reaches 200°C; Open the solenoid valve 5-1, make the liquid butane enter the thrust chamber 5-4 through the capillary 5-2, the flow rate is 0.1~0.2g / s, the high temperature gas generated in the thrust chamber 5-4...

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PUM

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Abstract

The invention relates to a low-pressure liquefied gas thrust generating method for a spacecraft. According to the method, a specially-designed thrust generating module is adopted to generate thrust and torque for the spacecraft and comprises a storage tank, a first pressure sensor, a charging / discharging valve, a self-locking valve, a thruster, a first temperature sensor and a first heater; the thrust generating module adopts a liquid-storage gas-use working mode, so that pressurized gas is not required to be additionally added into the storage tank, and the supply of a propellant can be driven by only using saturated vapor pressure of liquefied gas; thus, the thrust generating module only needs a liquid charging / discharging valve, and an additional gas charging / discharging valve is not required to be arranged, so that the weight of a system is greatly lowered, and thrust and torque, which have enough accuracy, can be provided for a miniature spacecraft in a microgravity environment and are applied to the attitude control, orbit control or formation flying of the miniature spacecraft.

Description

Technical field [0001] The invention relates to a method for generating a low-pressure liquefied gas thrust for a spacecraft, which can provide a micro-sized spacecraft with thrust and torque that meets the requirements of attitude orbit control under a microgravity environment, and belongs to the technical field of spacecraft propulsion system design. Background technique [0002] In the existing method for generating low-pressure liquefied gas thrust for spacecraft, it is often designed to provide gaseous liquefied gas propellant to the thruster in the manner of gas outlet from the storage tank, and the layout of the components in the thrust generating module is relatively dispersed. Because the gaseous liquefied gas propellant is very easy to liquefy, the thrust generated by this thrust generation method is relatively unstable. In addition, the integration of the entire thrust generation module is not high, and it occupies a large volume. Summary of the invention [0003] The ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/40B64G1/26
Inventor 高永马彦峰孙水生李永王渊丁凤林宋飞胡齐刘锦涛纪嘉龙宇文雷刘旭辉李永平
Owner BEIJING INST OF CONTROL ENG
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