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

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...

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

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