Overpressure autonomous management test method and system of attitude and orbit control pipeline of spacecraft propulsion system
A technology for autonomous management and propulsion systems, which is applied in the field of spacecraft testing to ensure safety and test coverage, and avoid excessive reverse pressure.
Pending Publication Date: 2021-12-14
SHANGHAI SATELLITE ENG INST
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This patent is only applicable to the autonomous task management of the joint work mode of the ground and the spacecraft, and does not involve the autonomous management of the attitude and orbit control pipeline overpressure of the propulsion subsystem, let alone the related autonomous management test method
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[0035] According to the spacecraft propulsion system attitude control pipeline overpressure self-management test method provided by the present invention, when the self-locking valve of the attitude control pipeline cannot reversely withstand excessive pressure, the self-management program has an overpressure threshold adjustment function, so as to Ensure propulsion system product safety and test coverage, such as figure 1 , including the following steps:
[0036] Step 1: Connect the attitude and orbit control pipeline to the external air source;
[0037] Step 2: Open the self-locking valve, close the self-locking valve after the downstream pipeline is connected with the external air source;
[0038] Step 3: Evacuate the gas in the upstream pipeline;
[0039] Step 4: Lower the overpressure threshold of the attitude and orbit control pipeline, and start the overpressure self-management function;
[0040] Step 5: The program triggers the self-locking valve to open, and after ...
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The invention provides an overpressure autonomous management test method and system of an attitude and orbit control pipeline of a spacecraft propulsion system. The method comprises the following steps of 1, connecting the attitude and orbit control pipeline with an external gas source; 2, opening a self-locking valve, and closing the self-locking valve after a downstream pipeline is communicated with the external air source; 3, exhausting gas in an upstream pipeline; 4, adjusting the overpressure threshold of the attitude and orbit control pipeline, and carrying out overpressure autonomous management; and 5, opening the self-locking valve of the attitude and orbit control pipeline according to a preset program, reducing the pressure of the downstream pipeline to atmospheric pressure, and if the situation that after the upstream of the self-locking valve of the attitude and orbit control pipeline is connected with the external air source, the pressure of the downstream pipeline of the self-locking valve does not change, occurs, indicating that the overpressure autonomous management succeeds. The method and the system are suitable for the overpressure autonomous management test of the attitude and orbit control pipeline of the spacecraft propulsion system, prevents the self-locking valve from reversely bearing overhigh pressure, and guarantees the product safety and test coverage of the propulsion system.
Description
technical field [0001] The invention relates to the technical field of spacecraft testing, in particular to a method and system for self-management and testing of overpressure in an attitude-orbit control pipeline of a spacecraft propulsion system. Background technique [0002] The spacecraft propulsion system mainly cooperates with the attitude and orbit control system to complete tasks such as attitude control, orbit modification, and flywheel unloading. The overpressure of the attitude and orbit control pipeline of the propulsion system may cause the pressure sensor to exceed the range and the reverse pressure of the self-locking valve to be too high. In severe cases, it may lead to propellant leakage, no thrust of the spacecraft, insufficient thrust, and reversal of the control attitude. The overpressure self-management test of the attitude and orbit control pipeline itself will introduce a high-voltage source, and poor control during the test may lead to the above-menti...
Claims
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Login to View More IPC IPC(8): G01M99/00
CPCG01M99/007G01M99/008Y02T90/00
Inventor 赵训友朱新波李绿萍信思博王伟张玉花
Owner SHANGHAI SATELLITE ENG INST