Satellite flexible part on-orbit modal identification realization system and method

Abstract

The invention provides a satellite flexible part on-orbit modal identification realization system and method. The realization system comprises a pulse excitation module, a signal acquisition module, a data transmission module, a satellite on-orbit vibration monitoring and modal identification module and a data processing module. The pulse excitation module is used for carrying out pulse excitation on a satellite flexible part; the signal acquisition module is used for collecting pulse response signals at the place of each measuring point on the satellite flexible part; the data transmission module is used for transmitting the pulse response signals of each measuring point to the ground; the satellite on-orbit vibration monitoring and modal identification module is used for receiving and monitoring the pulse response signals of each measuring point and collecting acceleration response signals generated by the satellite flexible part in the satellite on-orbit steady-state operation process; and the data processing module is used for carrying out modal frequency and modal vibration shape identification according to pulse response signals of each measuring point. The system and method solve the problem of inaccurate ground modal frequency measurement of the satellite flexible part; and the system is reliable and high in universality.

Description

technical field [0001] The invention relates to an on-orbit modal test method for satellite flexible components, in particular to a system and method for realizing on-orbit modal identification of satellite flexible components. Background technique [0002] In order to meet the requirements of high-power and high-resolution tasks, current satellite platforms generally use large-scale and flexible solar cell arrays or extended antennas. These flexible accessories complicate the dynamic characteristics of satellite structures, especially low-frequency characteristics. Under the influence of some payload rotation mechanisms, due to insufficient prediction of the ground mode, it is very likely to cause significant attitude oscillations. This will inevitably reduce the detection accuracy of spaceborne remote sensing equipment and may even cause a large change in the attitude angle of the satellite. Therefore, it is necessary to monitor and analyze the on-orbit mode. [0003] At ...

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Problems solved by technology

[0004] 1) Limited by ground test conditions and simulation parameter settings, it is impossible to accurately and reliably display the on-orbit operation status of the entire satellite, resulting in high or low reliability in the design process of the entire satellite, making the parameters in the design process inconsistent with the actual situation in orbit , leading to control deviation in attitude and orbit control;

[0005] 2) On the other hand, it causes vibration coupling between certain components and the mode of the whole star, resulting in a decrease in attitude stability, affecting the load and the work and life of the whole star, and there are reliability problems, weak links and hidden dangers of accidents;

[0006] 3) There is a lack of effective on-orbit modal test methods, especially the selection of excitation methods for on-orbit modal tests, which has always been a blank

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