Testing system, method and device for satellite electric propulsion system

Abstract

The invention discloses a test system, method and device for a satellite electric propulsion system, and the system comprises a vacuum tank which is used for providing a vacuum environment for the satellite electric propulsion system; a satellite electric propulsion system which is arranged in the vacuum tank and comprises a power supply processing unit and an electric thruster, wherein the powersupply processing unit is used for supplying power, and the electric thruster is used for generating thrust; a load simulator which is used for simulating load characteristics of the electric thrusterin at least one state; and a simulation access conversion device which is arranged between the satellite electric propulsion system and the load simulator and is used for connecting the power supplyprocessing unit with the load simulator or the electric thruster. The technical problem that in the prior art, an electric propulsion system thermal vacuum experiment consumes long time is solved.

Description

technical field [0001] The present application relates to the technical field of satellite testing, in particular to a testing system, method and device for a satellite electric propulsion system. Background technique [0002] The electric propulsion system is a device that can generate thrust without relying on chemical fuel, and is widely used in spacecraft as one of the important subsystems of the spacecraft. Therefore, the performance of the electric propulsion system directly affects the performance of the spacecraft. Common tests for electric propulsion systems include thermal vacuum tests. Thermal vacuum test experiments not only need to verify the thermal control design related to the electric propulsion system, but also need to simulate and verify the actual ignition of the entire star electric thruster in the orbital environment and flight state. performance. [0003] Since the electrode assembly of the electric thruster can only work in a vacuum under high press...

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Problems solved by technology

[0004] The technical problem to be solved by this application is to provide a test system, method and device for a satellite electric propulsion system in view of the time-consuming thermal vacuum experiment of the electric propulsion system in the prior art, by setting a simulation channel outside the vacuum tank The conversion device can simply and directly realize the connection and conversion of the power processing module between the load simulator or the electric thruster, avoiding opening the vacuum tank to realize the power processing module in the load simulator or electric thruster when performing a thermal vacuum experiment on the satellite propulsion system. The connection conversion between electric thrusters reduces the time consumption of experiments and improves the efficiency of experiments

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