Method for designing electromagnetic radiation sensitivity control magnitude of spacecraft equipment

Abstract

Disclosed is a method for designing an electromagnetic radiation sensitivity control magnitude of spacecraft equipment, comprising the following steps: 1) judging the stage of development of a spacecraft, and calculating a maximum field strength Es corresponding to the stage; 2) determining a critical category of the equipment; 3) determining a safety margin SM according to the critical category of the equipment; and 4) calculating the radiation sensitivity control magnitude ERS=Es+SM according to the maximum field strength Es and the safety margin SM. The method effectively adapts to the state of different design and development stages of the spacecraft; on the other hand, the method adapts to the actual state and key of a design object on the spacecraft.

Description

technical field [0001] The invention relates to a design method for controlling the magnitude of electromagnetic radiation sensitivity of spacecraft equipment. Spacecraft systems and sub-systems can be designed and tested for the magnitude of electromagnetic radiation sensitivity of equipment on the spacecraft according to the method. Background technique [0002] With the development of spacecraft technology, the number of electronic equipment required in the same spacecraft is increasing, the operating frequency band of electromagnetic equipment is getting wider and wider, the transmitting power of the radio frequency transmitting system is increasing, and the receiving sensitivity of the radio frequency receiving system is getting higher and higher. At the same time, all these technological advances have brought the complexity of spacecraft electromagnetic compatibility issues. In order to ensure the electromagnetic compatibility of the spacecraft system, the electromagne...

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Problems solved by technology

However, there is no general standard for this kind of tailoring in China, and the tailoring is often carried out by inheriting the relevant electromagnetic compatibility technical requirements of the existing models, but this method is not very specific, and it is likely to cause under-design to the electromagnetic compatibility design of the equipment. or unnecessary overdesign

[0004] In the patent "ZL201218001467.X A Tailoring Method for Satellite System-Level Electromagnetic Compatibility Radiation Sensitivity Control Standard", a tailoring method for satellite system-level radiation sensitivity control standard is proposed, and to a certain extent, an electromagnetic However, there are several problems in this method: ① The essence of this method depends on the far-field Friss transmission formula. Since the electromagnetic compatibility in the spacecraft system is more of a near-field problem, this method cannot completely Applicable; ②This method is mainly for tailoring the radio frequency transmission band, and the out-of-band control still refers to the standard requirements or inherits the model requirements, and the radio frequency out-of-band control is also the focus of electromagnetic compatibility. At the same time, this method does not consider the design object in the The actual state on the satellite; ③This method does not take into account the impact of the criticality of the equipment on the electromagnetic compatibility of the system. In practical applications, the control level of the radiation sensitivity of the equipment is closely related to its criticality on the spacecraft

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