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Propelling agent supply system for catalytic ignition hydrogen oxygen small-sized rocket thruster test

A technology of rocket thrust and catalytic ignition, which is applied in the testing of machine/structural components, instruments, and engines, etc., can solve problems such as the inability to meet the test requirements, and achieve the effect of shortening the pressure build-up time

Inactive Publication Date: 2011-11-23
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The catalytic ignition and small flow characteristics of this kind of thruster make the traditional dual-component thruster test propellant supply system unable to meet its test requirements

Method used

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  • Propelling agent supply system for catalytic ignition hydrogen oxygen small-sized rocket thruster test
  • Propelling agent supply system for catalytic ignition hydrogen oxygen small-sized rocket thruster test

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Embodiment Construction

[0022] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0023] The present invention is a kind of propellant supply system for catalytic ignition gas hydrogen oxygen small rocket thruster test, such as figure 1 shown, including: O 2 Cylinder assembly 1, H 2 Gas cylinder assembly 13, first flow controller 4, second flow controller 16, first pressure gauge 5, second pressure gauge 17, first filter 7, second filter 18, first solenoid valve 8, second Two solenoid valves 19, two-position three-way solenoid valve 20, first check valve 9, second check valve 21, hydrogen flow distribution structure 25, first pressure sensor 11, second pressure sensor 23 and third pressure sensor 26 , and the necessary connection devices, the connection devices mainly include pipelines, tees, adapters and other equipment necessary for connecting components.

[0024] o 2 Cylinder assembly 1 by O 2 Composed of high pressure cylinder, fi...

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PUM

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Abstract

The invention discloses a propelling agent supply system for a catalytic ignition hydrogen oxygen small-sized rocket thruster test. The propelling agent supply system comprises an air bottle assembly, a flow controller, a solenoid valve, a check valve, a pressure gauge and a connecting device. A fuel hydrogen (H2) pipeline system consists of a test pipeline and an emptying pipeline, wherein the emptying pipeline is used for coarsely adjusting H2 flow and pressure required by the upstream of a catalytic ignition hydrogen oxygen small thrust engine before the test starts, so that the time of coarsely adjusting H2 flow and pressure intensity and the time of H2 passing through the pipeline in the test process can be shortened by the emptying pipeline to the maximum degree.

Description

technical field [0001] The invention belongs to a rocket engine test system, and relates to a propellant supply system for catalytic ignition gas hydrogen oxygen small rocket thruster test. Background technique [0002] The propellant supply system of the gas-hydrogen-oxygen small-scale rocket thruster test using catalytic ignition is a system that provides propellant for the engine and plays an important role in the test. [0003] Compared with traditional chemical propellants, hydrogen and oxygen have advantages such as higher specific impulse, and have always been considered to have great potential in space propulsion. For a long time, the space storage problem of high-pressure hydrogen has not been effectively solved, thus limiting the wide application of hydrogen-oxygen propellants in space propulsion. The water-based rocket space propulsion system can use low-pressure water to electrolyze high-pressure hydrogen in real time, which solves the problem of hydrogen storag...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/02
Inventor 王长辉林震刘宇王玚
Owner BEIHANG UNIV
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