Study On Modeling And Simulation Of A Satellite With A Architecture Of Disturbance-free Payload In Pointing Control

With the continuous development of science and technology, control and motionstability requirements for current and future space-borne missions are more stringentthan ever.The interference of the noise on the spacecraft must be isolated. This articlemainly studies a satellite with a architecture of disturbance-free payload and analysisvalidate the unique advantages of this satellite in control and motion stability.Firstly, this paper established the attitude kinematics equations and dynamicsequations of the general rigid body small satellite. Then according to the principle ofactive vibration isolation, put forward the method that blocked the route of transmissionof the noise basically.This satellite is divided into two parts, respectively is payloadmodule and support module. the payload module is mainly to provide sensitive deviceinstallation position, and also need a very low noise environment. Support modulemainly provide service for the payload module, it is home to the the main noise sourceon the satellite. Measured the relative position between the payload module and supportmodule, energy exchange and the attitude change of payload module mainly throughsensors and actuator that are not in contact. The two parts is completely no rigidconnection.Secondly, according to the structure characteristics of this satellite, using satelliteattitude dynamics knowledge. Established the flexible and un-flexible mathematicalmodel and control model of this satellite. Finally on the basis of the established controlmodel, to model simulate and compare with the satellite which don’t use this particularstructure.This satellite isolate the noise out completely from the structure. But it alsoincreases the control difficulty, payload module attitude control without the influence ofthe attitude control of support module and the two modules relative motion control. Andservice module by not contact relative position sensor to obtain the relative positionrelations with payload module, so as to control its attitude position. The control ofrelative position is through control the attitude of service module. So the attitude controlof payload module are completely independent, also blocking the error and noisethrough the support module. And from the mechanical structure and control structureenables the payload module to isolate the noise completely, so that this satellite can gethigh control and motion stability.