Chemical test method for bipropellant thruster after thermal standard cleaning

Abstract

The invention relates to a chemical test method for a bipropellant thruster after thermal standard cleaning. The chemical test method of a burning path comprises the following steps: firstly, steady state and pulse mixed flushing and blowing are performed to methylhydrazine (fuel) difficult to clean away in a small flowing channel through isopropyl alcohol; sampling is performed on the isopropyl alcohol cleaning solution and the blowing gas to form gaseous sample and liquid sample of the burning path; the concentrations of the gaseous sample and the liquid sample are obtained through a standard solution concentration curve, so as to judge whether the burning path is cleaned out or not. An oxygen path adopts the same chemical test method. The chemical test method of he oxygen path comprises the following steps: cleaning and blowing are performed on nitrogen tetroxide (the oxygen path) through freon; then sampling is performed on the freon cleaning solution and the blowing gas; the concentrations of the freon cleaning solution and the blowing gas are measured through the same method (the standard solution concentration curve), so as to judge whether the oxygen path is cleaned out or not. According to the chemical test method, a chemical test can be performed on the engine of the bipropellant attitude and orbit control liquid-propellant rocket after thermal standard cleaning. Besides, the chemical test method can be taken as reference for the cleaning test methods of other chemical propulsion engines.

Description

technical field [0001] The invention relates to a chemical inspection method after the thruster is cleaned, in particular to a thermal standard cleaning of the attitude and orbit control thruster components of the chemical propulsion system in which the oxidant is dinitrogen tetroxide (MON-1) and the combustion agent is methylhydrazine Subsequent chemical testing methods. Background technique [0002] The rapid development of the national economic construction puts forward higher requirements on the design life of the dual-component chemical propulsion system satellite, and the most significant impact on the satellite life is the consumption of chemical propellants. In order to achieve the purpose of reducing the consumption of satellite propellant, the accuracy of satellite attitude control must be improved, which directly depends on the test accuracy of attitude control thruster performance. In order to effectively improve the test accuracy of the thermal performance of t...

AI Technical Summary

Problems solved by technology

[0004] At present, no literature has been found on the hot-mark test of the dual-component attitude control thruster, so no literature on the chemical inspection method after hot-mark cleaning has been found

Images