Thruster of hydrogen-oxygen catalytic ignition mini rocket

A technology of catalytic ignition and oxygen catalysis, which is applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve problems restricting the space application of gas, hydrogen, oxygen thrusters, etc., achieve lower thermal protection requirements, and be easy to disassemble and replace parts , Improve the effect of gas temperature and specific impulse

Inactive Publication Date: 2011-09-21
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the space storage problem of high-pressure hydrogen ha

Method used

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  • Thruster of hydrogen-oxygen catalytic ignition mini rocket
  • Thruster of hydrogen-oxygen catalytic ignition mini rocket
  • Thruster of hydrogen-oxygen catalytic ignition mini rocket

Examples

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Embodiment Construction

[0023] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0024] The present invention proposes a small thruster for catalytic ignition of gas hydrogen and oxygen, such as figure 1 As shown, the thruster includes a catalytic ignition device 1 and a combustion chamber device 2 .

[0025] The catalytic ignition device 1 is composed of a head 101, a catalytic cylinder 102 and a bottom plate 103 of the catalytic cylinder. The front end of the head 101 has a gas through hole passing through the axis of the head vertically. The two ends of the gas through hole are respectively used to communicate with hydrogen. and oxygen to form gas hydrogen inlet 1011 and gas oxygen inlet 1012, such as figure 2 , the rear end of the head 101 has an axial blind hole along the axial direction, the bottom of the blind hole communicates with the side hole wall of the central section of the gas through hole, the catalytic cylinder is locat...

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PUM

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Abstract

The invention provides a thruster of a hydrogen-oxygen catalytic ignition mini rocket, comprising a catalytic ignition device and a combustor device, wherein the catalytic ignition device comprises an end socket, a catalytic cylinder and a catalytic cylinder baseplate; and the combustor device comprises a graphite lining, a graphite precombustion chamber, a precombustion chamber sleeve, a nozzle steel jacket and a tungsten-doped copper nozzle. The thruster is used for realizing hydrogen-oxygen catalytic ignition which can be used for realizing the purpose of repeated ignition. Hydrogen inletsare uniformly distributed at the back semi-section of the combustor in the thruster in the circumferential direction, thus adjusting the hydrogen-oxygen mixing ratio and achieving an afterburning effect. The thruster is simple in structure and ensures that parts can be disassembled and replaced easily.

Description

technical field [0001] The invention belongs to the field of propulsion systems for space vehicles such as satellites, and in particular relates to a small thruster with catalytic ignition of gas, hydrogen and oxygen. Background technique [0002] At present, the thrusters on satellites are mostly decomposed by cold gas and hydrazine, which have low specific impulse and are toxic. However, the theoretical specific impulse of gas-hydrogen-oxygen propellant is much higher than that of hydrazine propellant, which can greatly improve the performance of the space propulsion system. However, the space storage problem of high-pressure hydrogen has restricted the space application of hydrogen-oxygen thrusters. 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 storage in space and puts the development of space gas hydrogen-oxygen thrusters on the agenda. [0003] The high...

Claims

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Application Information

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IPC IPC(8): F02K9/95F02K9/62
Inventor 王长辉林震刘宇曹熙炜
Owner BEIHANG UNIV
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