关键词:

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Abstract:

When the satellite takes orbital maneuver, the control force may stimulate the vibration of the flexible appendages and, therefore, affects the attitude of the satellite.The dynamic model of the satellite with a large solar panel is established via Lagrange equations.The coupling relations between the motion of the satellite orbit, the attitude and the flexible vibration are analyzed.The attitude control law is designed for the orbital maneuver with considering the output character of the attitude control thrusters.Numerical simulation is conducted to verify the effects of the orbital control force on the flexible panel and the satellite attitude.The efficiency of the attitude control law is also verified.

Key words:

font-size:10.5pt, font-family:Calibri, sans-serif, "> color:windowtext, flexible satellite')">">flexible satellite, orbital maneuver, attitude control, flexible vibration, ')">">