The jitter control technique by using dual-stage vibration isolation system for optical payload on satellites is discussed in this paper, and it is applied on a satellite to improve the imaging performance. The dual-stage vibration isolation system includes two vibaration isolation platform. The first vibration isolation platform is at the actuator disturbance source like control moment gyroscopes (CMGs). The second stage of isolation is placed between the top of the satellite bus and the optical payioad. The first step constructs an integrated satellite dynamic model including a dual-stage vibration isolation system, pyramid configuration CMGs and solar arrays by Newton-Euler method, while the validity of this dynamic model is verified by Adams software. The transmissibility matrices from CMGs motion to satellite motion and that to optical payload motion are then obtained. The parameters constraint conditions of the vibration isolation platform for the CMGs are described, with its influence on the attitude control system analyzed. The third part presents the frequency domain characteristics of the optical payload with the dual-stage vibration isolation system. Finally, using the reasonable parameters of the dual-stage vibration isolation system, the performance of this vibration isolation system on the satellite is testified by numerical simulations. The study shows that the jitter control technique by using dual-stage vibration isolation system in this paper can attenuate the disturbances to a great extent thus improve the attitude stability of the optical payload, and this technique can provide an ultra quiet environment for the optical payloads.
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