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

A technology of flexible vibration and modal parameters, applied in the field of satellite data identification, can solve problems such as limitations, increasing the number of slip ring signal channels of the driving mechanism, and increasing design difficulty

Pending Publication Date: 2020-03-27
SHANGHAI SATELLITE ENG INST
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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, ...

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

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specific Embodiment

[0029] The invention provides a method for identifying the modal parameters of the whole-satellite flexible vibration by using the satellite gyroscope data, which uses the attitude angular velocity data measured by the gyroscope during the under-damped free vibration period after the satellite is on-orbit air jet control to identify the modal parameters of the whole-satellite flexible vibration. The modal parameters of the whole satellite's flexible vibration include the modal frequency of the on-orbit flexible vibration and the modal damping ratio. The identification process only uses the gyro measurement data loaded on the satellite platform for analysis and processing, and does not use the displacement, velocity, and acceleration vibration sensors installed on the flexible attachment. Specific examples are as follows:

[0030] A remote sensing satellite is equipped with a single-wing solar cell array, the configuration is shown in figure 1 . After launching into orbit, th...

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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...

Claims

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Application Information

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IPC IPC(8): G06F30/20G01C25/00
CPCG01C25/00G01C25/005
Inventor 周徐斌董瑶海吕旺沈毅力满孝颖薛景赛
Owner SHANGHAI SATELLITE ENG INST
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