带挠性帆板航天器热诱发姿态运动分析

doi:10.3969/j.issn.1674-1579.2013.01.006

›› 2013, Vol. 39 ›› Issue (1): 34-39.doi: 10.3969/j.issn.1674-1579.2013.01.006

Analysis of Thermally Induced Attitude Motion of Spacecraft with Flexible Solar Panels

Abstract：With the sudden temperature change of the solar panels considered, Lagrange’s energy equation of the system is established. The quasistatic bending is factorized into two types of functions: one is the shape function and the other is time function. Using the extended assumed modal method, the system dynamics model is derived. Analytical results demonstrate that temperature difference results in the attitude error. And the effects of thermal time constant and temperature difference on the attitude dynamics of the vehicle are studied. In the frequency domain, the effect of thermally induced disturbance torque on the spacecraft attitude control system is analyzed. Finally numerical simulations are provided to verify the correctness of the analysis.

(1.Beijing Institute of Control Engineering, Beijing 100190, China；
2.Science and Technology on Space Intelligent Control Laboratory, Beijing 100190, China)

Online:2013-02-24 Published:2013-02-26

Abstract

Abstract: Abstract：With the sudden temperature change of the solar panels considered, Lagrange’s energy equation of the system is established. The quasistatic bending is factorized into two types of functions: one is the shape function and the other is time function. Using the extended assumed modal method, the system dynamics model is derived. Analytical results demonstrate that temperature difference results in the attitude error. And the effects of thermal time constant and temperature difference on the attitude dynamics of the vehicle are studied. In the frequency domain, the effect of thermally induced disturbance torque on the spacecraft attitude control system is analyzed. Finally numerical simulations are provided to verify the correctness of the analysis.

Key words: Keywords：flexible solar panel, thermally induced vibrations, attitude dynamics, attitude control

CLC Number:

TP27

LI Li-Jun, YUAN Jun. Analysis of Thermally Induced Attitude Motion of Spacecraft with Flexible Solar Panels[J]., 2013, 39(1): 34-39.

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URL: http://journal01.magtech.org.cn/Jwk3_kjkzjs/EN/10.3969/j.issn.1674-1579.2013.01.006

http://journal01.magtech.org.cn/Jwk3_kjkzjs/EN/Y2013/V39/I1/34

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Analysis of Thermally Induced Attitude Motion of Spacecraft with Flexible Solar Panels

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