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Propellant supply system and method for attitude control engine vacuum thermal environment test

An environmental test and supply system technology, applied in machines/engines, rocket engine devices, jet propulsion devices, etc., can solve the problems of easy condensation and thermal decomposition, unstable propellant performance, etc., to achieve local low temperature protection, prevent Heat transfer, the effect of reducing the contact area

Active Publication Date: 2022-05-10
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0005] The present invention aims to solve the problem that the performance of the propellant in the vacuum thermal environment of the existing attitude control engine is extremely unstable, and it is prone to condensation and thermal decomposition, so that the propellant cannot be reliably and stably supplied to the attitude control engine. And provide a kind of propellant supply system method for attitude control engine vacuum thermal environment test

Method used

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  • Propellant supply system and method for attitude control engine vacuum thermal environment test
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  • Propellant supply system and method for attitude control engine vacuum thermal environment test

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Embodiment Construction

[0042] The technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention and the accompanying drawings. Apparently, the described embodiments do not limit the present invention.

[0043] Such as Figure 1 to Figure 4 As shown, the propellant supply system for the vacuum thermal environment test of the attitude control engine in this embodiment includes a supply pipeline 2, an inlet valve 1 arranged on the supply pipeline 2, and a penetration flange 3. The penetration method The flange 3 is arranged on the vacuum bulkhead 4, and the supply pipeline 2 passes through the penetration flange 3,

[0044] It also includes a vacuum pumping system 5 and a filling and discharging system 6;

[0045]The supply pipeline 2 includes an outboard pipeline 21, a cabin penetration pipeline 22, and an engine inlet pipeline 23 that are connected in sequence, and the outboard pipeline 21 communicates with th...

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Abstract

The invention relates to a liquid rocket engine environmental simulation test technology, in particular to a propellant supply system and method for an attitude-controlled engine vacuum thermal environment test, so as to solve the problem that the propellant is supplied at high and low temperature in the existing attitude-controlled engine vacuum thermal environment propellant supply. Extremely unstable performance in the environment. The technical solution adopted in the present invention includes an inlet valve, a supply pipeline, a tank penetration flange, a vacuum pumping system and a filling and discharging system; the supply pipeline includes an outer tank pipeline, a tank penetration pipeline and an engine inlet pipeline which are connected in sequence. , the outer pipeline includes the outer center pipe and the outer vacuum interlayer arranged from the inside to the outside; the cabin penetration pipeline includes the cabin penetration center pipe, the cabin vacuum interlayer, and the cabin cladding arranged in sequence from the inside to the outside The engine inlet pipeline comprises an inlet central pipe, an inlet vacuum interlayer and an inlet heat-proof coating layer arranged in sequence from the inside to the outside; the invention also provides a propellant supply method for a vacuum thermal environment test of an attitude-controlled engine.

Description

technical field [0001] The invention relates to a liquid rocket engine environment simulation test technology, in particular to a propellant supply system and method for an attitude control engine vacuum thermal environment test. Background technique [0002] When conducting a 2000N level liquid attitude control engine vacuum thermal environment ignition test, the engine propellant supply needs to be supplied through the cabin. Since the low-temperature cooling system is installed on the vacuum bulkhead, the propellant in the propellant supply pipeline needs to pass through the lower part of the bulkhead. In the low temperature environment of -100 ℃ and the high temperature environment of more than 100 ℃ at the propellant inlet of the liquid attitude control engine in the cabin. At present, the propellants used in liquid rocket engines are oxidant green dinitrogen tetroxide (MON-3) and fuel methylhydrazine, of which green dinitrogen tetroxide has a boiling point of 21.15°C a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/96F02K9/44F02K9/54F02K9/60B32B29/00B32B9/00B32B9/06B32B9/04B32B27/28B32B17/02B32B17/10B32B7/12B32B1/08
CPCF02K9/96F02K9/44F02K9/54F02K9/60B32B29/00B32B29/02B32B5/02B32B27/281B32B27/12B32B7/12B32B1/08B32B2262/101B32B2307/304B32B2597/00
Inventor 寇鑫陈聪李林永安成琳董冬李民民党栋华程加万里赵明黄鹏辉李亮杨敏利廖云鹏李婧雯
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST
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