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Dynamics model and simulation for flexible satellite with orbit control force

The influence of the orbit control force on the flexible satellite is under consideration. The dynamics model of the satellite with a large solar panel is established via Lagrange equations. The dynamic characters of the system are analyzed. The coupling coefficient matrixes between the motion of the satellite and the flexible vibration are related to the fixing position and fixing angle of the flexible panel. The influence of the control force on the flexible vibration is also related to the fixing angle. The coupling relationship among the motion of the satellite mass center, the flexible vibration, and the attitude motion is discussed. Numerical simulation was carried out to express the effects of the orbit control force on the flexible vibration and the attitude of the satellite. These dynamic characters when the satellite takes orbit control would be important to analyze and control the attitude of the satellite.