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Method and system for identifying whole-spacecraft flexibility vibration modal parameters

A technology of flexible vibration and modal parameters, which is applied in the field of identifying the modal parameters of the flexible vibration of the whole satellite, using satellite gyroscope data to identify the modal parameters of the flexible vibration of the whole satellite, can solve the problem of increasing the number of slip ring signal channels of the drive mechanism, Increase design difficulty, restrictions and other issues

Active Publication Date: 2019-04-12
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, 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

Method used

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  • Method and system for identifying whole-spacecraft flexibility vibration modal parameters
  • Method and system for identifying whole-spacecraft flexibility vibration modal parameters
  • Method and system for identifying whole-spacecraft flexibility vibration modal parameters

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Embodiment approach

[0065] A remote sensing satellite is equipped with a single-wing solar cell array, the configuration is shown in figure 1 . After launching into orbit, the rolling X-axis attitude angular velocity measurement data during jet control is as follows: figure 2 shown.

[0066] Step 1: Select the rolling X-axis attitude angular velocity measurement data ω of the under-damped free vibration zone after the on-orbit jet closed-loop control of the satellite X (t) to analyze ( figure 2 ).

[0067] Step 2: According to the calculation results of the ground flexible satellite dynamics analysis, the frequency of the main vibration mode in the X direction is about 0.37Hz, set the vibration frequency band of interest to [0.259,0.481]Hz, and use the 5th-order Butterworth bandpass filter For the measurement data ω of the attitude angular velocity in the underdamped free vibration region X (t) Carry out filtering processing, strip the long-period motion and high-frequency vibration compon...

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Abstract

The invention provides a method for identifying whole-spacecraft flexibility vibration modal parameters. The method for identifying the whole-spacecraft flexibility vibration modal parameters comprises the following steps that pose angular speed is obtained, specifically, i-axis pose angular speed data omega' i (t) after filtering is obtained after pose angular speed measuring data omega i (t) corresponding to an i-axis of an underdamping free vibration area after satellite on-orbit air injection closed-loop control, wherein the i-axis is any one of an X-axis, a Y-axis and a Z-axis in a spacerectangular coordinate system; filtering is carried out, specifically, filtering is carried out on the omega i (t) to obtain the i-axis pose angular speed data omega' i (t) after filtering; on-orbit vibration frequency is calculated, specifically, the on-orbit vibration frequency fi is calculated and obtained according to the omega' i (t); time series is calculated, specifically, the time series eta i (t) of a modal variable is calculated and obtained according to the omega' i (t); and damping is calculated, specifically, the damping epsilon i of the i-axis vibration mode is obtained accordingto calculation. The method for identifying the whole-spacecraft flexibility vibration modal parameters meets the requirement of flexible satellite on-orbit structural dynamic characteristic identification, and on-orbit flexibility vibration modal frequency and modal damping ratio and other whole-spacecraft flexibility vibration modal parameters are extracted.

Description

technical field [0001] The present invention relates to the field of dynamics of flexible satellite structures, in particular to a method and system for identifying the modal parameters of the flexible vibration of the whole satellite, especially a method for identifying the modal parameters of the flexible vibration of the whole satellite by using satellite gyroscope data with the system. In particular, it relates to an on-orbit identification method and system for the on-orbit vibration mode of a flexible satellite, specifically an identification of structural dynamic parameters such as the frequency and modal damping ratio of the satellite's on-orbit flexible vibration mode methods and systems. 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, S...

Claims

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Application Information

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IPC IPC(8): G01M7/02
CPCG01M7/02G01M7/025
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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