Method and system for identifying in-orbit relative displacement of satellite flexible attachments using gyroscope data

Abstract

The invention provides a method for identifying on-orbit relative displacement of a satellite flexible appendage by using gyroscope data. The method comprises the following steps that an attitude angle velocity is acquired, specifically, attitude angle velocity measurement data omega(t) corresponding to an i axis of a under-damped free vibration zone after the closed-loop control over satelliteon-orbit air injection is acquired; filtering is performed, specifically, the omega(t) is subjected to filtering obtain filtered i-axis attitude angle velocity data omega'(t); time series calculation is performed, specifically, time series eta(t) of modal variable is obtained by calculating according to the omega'(t); and relative displacement calculation is performed, specifically, the relative displacement m12(t) of any two nodes on the flexible appendage is obtained by calculating according to the eta(t) and array data of any two nodes on the flexible appendage. The invention further provides a system for identifying the on-orbit relative displacement of the satellite flexible appendage by using the gyroscope data. The method does not require other sensors to be mountedon the flexible appendage, and only uses the measurement data of an existing attitude sensor of a satellite platform for analysis and processing.

Description

technical field [0001] The present invention relates to the field of satellite monitoring, in particular to a method and system for identifying the relative displacement of on-orbit vibration of satellite flexible accessories using gyroscope data, and in particular to an on-orbit identification method and system for flexible satellite vibration state information , specifically a method and system for identifying the relative displacement of the overall displacement during the on-orbit vibration of a flexible satellite. Background technique [0002] With the continuous development of aerospace technology, large-scale space structures have become an important development direction in the field of aerospace, and will also be the necessary infrastructure for space development [Research on Identification Technology of Dynamic Parameters of In-orbit Spacecraft—Yu Dengyun]. In order to obtain the dynamic characteristics of flexible satellite structures, finite element modeling, gro...

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Problems solved by technology

[0004] The above identification methods of dynamic parameters of flexible satellites in orbit have two constraints in terms of engineering application: one is that it is difficult to apply known excitations required for dynamic parameter identification on orbiting spacecraft, and only the deployment and retraction of the space structure in orbit can be used. , The docking and separation of the structure, the ignition of the engine, etc. generate excitation sources for excitation, and the signals of these excitation sources are difficult to measure [Research on Identification Technology of Dynamic Parameters of On-orbit Spacecraft——Yu Dengyun]

Second, the number of vibration sensors installed on flexible accessories is limited by engineering implementation

Generally, flexible accessories need to be deployed on rails, and the installation and fixing of various speed, acceleration, and displacement sensors, as well as cable laying, will have adverse effects on the deployment mechanism, increasing the difficulty of design

In addition, for rotating flexible components such as solar arrays, it is necessary to increase the number of signal channels of the drive mechanism slip ring

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