Abstract
This paper presents the dynamics simulation for ADEOS-IT (Advanced Earth Observing Satellite-II) attitude response of flexible solar array due to stick-slip. The numerical model is composed of main rigid body and flexible appendages consisting of torsional hinges-connected plates. Key parameters of the torsional hinges spring can be determined by using equation of vibration motion of uniform cantilever beam with physical parameters. As a result of simulation, it is concluded that the amplitude of attitude response caused by advanced TCM (Tension Control Mechanism) can be reduced to 3e-4 degree/sec, which is one tenth of ADEOS. The improvement of attitude disturbance is due to decrease of tension fluctuation in ADEOS-II TCM
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