Test system and test method for pressure protection system of spacecraft sealed cabin

Abstract

The application discloses a test system and a test method for a pressure protection system of a spacecraft sealed cabin. The test system comprises a first space environment simulation device, a secondspace environment simulation device, a simulation cabin body, an emergency pressure protection system, an air inlet pipeline assembly and a pressure relief pipeline assembly, wherein the pressure relief pipeline assembly comprises a pressure relief pipeline, a second program-controlled opening valve is arranged on the pressure relief pipeline, the air inlet pipeline assembly comprises an air inlet pipeline, and the air inlet pipeline is provided with a first program-controlled opening valve; wherein the second program-controlled opening valve controls the pressure relief rate of the pressurerelief pipeline to the second space environment simulation equipment to realize the simulation of different leakage holes of different spacecrafts in orbit, and the first program-controlled opening valve controls the re-pressure rate of the air inlet pipeline to the simulation cabin body for calibrating the equivalent diameters of the leakage holes. According to the test system and the test method, the working process of the pressure protection system in the cabin is simulated when the spacecraft loses pressure in orbit, and the performance of the pressure protection system is evaluated to provide support for the safety of future manned spacecraft.

Description

technical field [0001] The invention generally relates to the technical field of spacecraft ground tests, and in particular to a test system and a test method for a pressure protection system of a sealed cabin of a spacecraft. Background technique [0002] The in-orbit pressure loss of manned spacecraft is one of the failures that seriously endanger the safety of astronauts. The reasons include: 1) breakdown of micro meteors and space debris; 2) processing defects; 3) failure of the environmental control and life support system itself. Among them, the loss of pressure caused by the failure of the environmental control and life support system itself is often unable to seal the loopholes, and it is difficult to repair the system, which is one of the most serious types of failures. When a manned spacecraft loses pressure in low-Earth orbit, the astronauts generally wear emergency pressure suits and start the emergency oxygen supply system. The pressure system of the pressure su...

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Problems solved by technology

[0004] The current rapid pressure relief system is mainly used to simulate the rapid pressure change process of the active section of the spacecraft, which is simulated based on the existing pressure drop curve. - Establish a theoretical connection between the leak hole diameters, but in the ground test environment, due to factors such as the resistance loss along the system pipeline, it is difficult to equivalent the leak hole diameter through pressure, and it is impossible to determine the valve opening and equivalent leak hole diameter relationship, it is impossible to obtain valid test results

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