All-satellite electromagnetic compatibility verification method and system based on electric propulsion radiation emission simulator

Abstract

Provided are an all-satellite electromagnetic compatibility verification method and system based on an electric propulsion radiation emission simulator. The method includes firstly obtaining a radiation emission parameter of an electric propulsion system under a real ignition condition under vacuum conditions; constructing an electric propulsion electromagnetic radiation emission simulator which can generate the same electromagnetic radiation emission as the radiation emission parameters under the actual ignition conditions of the electric propulsion system; finally, in the all-satellite electromagnetic compatibility test, and the electric propulsion radiation emission simulator is used instead of the electric propulsion radiation emission under vacuum ignition conditions, to complete thetesting and evaluation of the satellite electromagnetic compatibility of the electric propulsion system. According to the all-satellite electromagnetic compatibility verification method and system, the range of radiated interference intensity of an electric thruster working normally to the satellite, and the test frequency band covers the frequency range of 1 GHz to 31 GHz; the magnitude of the electromagnetic radiation interference of the electric propulsion work is confirmed through the testing of three phases, and the electromagnetic radiation effect of the electric propulsion work processdoes not affect the normal operation of the all-satellite communication load in the L-band, C-band, Ku-band and Ka-band.

Description

technical field [0001] The invention relates to a whole-satellite electromagnetic compatibility verification method and system based on an electric propulsion radiation emission simulator, and belongs to the technical field of electromagnetic compatibility tests of satellites equipped with electric propulsion systems. Background technique [0002] As an advanced satellite propulsion technology, the electric propulsion system has the characteristics of high specific impulse and low thrust, which can effectively improve the carrying capacity and control accuracy of spacecraft, and has become the standard configuration of advanced spacecraft in various aerospace powers. [0003] The ignition of the electric propulsion system is required to be carried out in a vacuum environment and equipped with plasma protection equipment, while the satellite electromagnetic compatibility verification should be carried out in a professional electromagnetic compatibility laboratory. Professiona...

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Problems solved by technology

[0005] The technical problem solved by the present invention is: to overcome the deficiencies of the existing technology, to provide a whole-satellite electromagnetic compatibility verification method and system based on the electric propulsion radiation emission simulator, which can solve the requirement that the electric propulsion system can only be ignited in a vacuum environment. The existing satellite electromagnetic compatibility test environment cannot provide

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