Method for identifying whole-satellite flexible vibration modal parameters by utilizing satellite gyroscope data

Abstract

The invention provides a method for identifying whole-satellite flexible vibration modal parameters by utilizing satellite gyroscope data. The whole-satellite flexible vibration modal parameters are identified by utilizing attitude angular velocity data measured by a gyroscope in an under-damping free vibration period after satellite on-orbit air injection control, wherein the whole-satellite flexible vibration modal parameters comprise an on-orbit flexible vibration modal frequency and a modal damping ratio. In the identification process, only gyro measurement data loaded on a satellite platform are used for analysis and processing, and displacement, speed and acceleration vibration sensors installed on flexible accessories are not used. According to the method, only measurement data of an existing inertial attitude sensor of a satellite platform are used for analysis and processing; the increased satellite design and manufacturing difficulty and the risk of on-orbit operation due tothe installation of other vibration sensors are avoided. The identified whole-satellite flexible vibration mode parameters can provide necessary support for application in the aspects of structural design, structural health monitoring, structural fault diagnosis, structural vibration control and the like of space flexible components.

Description

technical field [0001] The invention relates to the field of satellite data identification, in particular to a method for identifying the modal parameters of the whole satellite's flexible vibration by using satellite gyroscope data. Background technique [0002] With the continuous development of aerospace technology, large-scale space structures have become an important development direction in the aerospace field, and will also be the necessary infrastructure for space development [Yu Dengyun, Xia Renwei, Sun Guojiang. Identification of dynamic parameters of on-orbit spacecraft Technology Research. China Space Science and Technology, February 2008, Issue 1]. In order to obtain the dynamic characteristics of flexible satellite structures, finite element modeling, ground tests, and on-orbit identification are often used to calculate vibration modal parameters. Model simplification and conditional assumptions in the finite element modeling process affect the accuracy of the...

AI Technical Summary

Problems solved by technology

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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