The Study Of Isolation And Control For The Vibration Isolation System Of The Satellite

For the spacecraft, the two most important issues at this stage are the pointingaccuracy and stability problem. One of the key factors to solve these two problems isto solve the vibration isolation and vibration suppression problem of the spacecraft.To distinguish from the traditional methods, we chose another way, by improving thestructure, we propose a new concept of satellite to solve the vibration problem of thespacecraft——the satellite with a structure of non-disturbance payload. The socalled satellite with a structure of non-disturbance payload is to divide the satelliteinto two parts, the motion cabin and the static cabin, by introducing a new type ofnon-disturbance active vibration isolation platform to achieve the goal that the noisysignal of the moving cabin can not be fully passed to the quiet cabin, and it does notinfluence the control of the system.In this paper we propose a active vibration isolation platform by adopting a newway. The components on the satellite are classified according movement Thecomponents which produce no noise when they work are installed on the payloadmodule, while the components which produce noise when work are installed on theservice module.Using the unified isolation method, and this way can avoid thevarious isolation methods of different interference sources for the conventionalmethods.This paper introduces the development of the vibration isolation system firstly.Then we conduct a brief introduce about the development of the history of vibrationisolation about the satellite and then compare various isolation methods. The paperimprove the drawbacks of traditional methods and then proposes the concept of thesatellite with a structure of non-disturbance payload,then introduces the newplatform simplify By building Space coordinates to analysis the geometry of theisolation platform,then analysis the influence of the platform to the satellite attitude.Then introduce the Euler angles and quaternion attitude description methods simple.Establish the dynamics model of the rigid body, and then establish a space dynamicsmodel of the coupled actuators for the vibration isolation platform.By the decoupling calculation of the coupled dynamics equation, the originalmulti-input and multi-output system change to the single-input and single-outputcontrol to achieve effective control of the actuators.We conduct the design andsimulation of the satellite control systems for the designed vibration isolationplatform, design the system of the static cabin and motion cabin respectively to getwell attitude control of the payload and the motion cabin can follow the attitude ofthe payload quite good. Verifying the performance of the payload attitude and the follow performance of the motion cabin according to the simulation. And thenobserve the performance of the anti-disturbance of the payload to the motion cabin’sdisturbance sources. Illustrating the performance of isolation by comparing theresults.Finally, we highlight the advantages of the new concept satellites designed inthis paper by compare with the conventional satellite, showing the prospects in thefuture of the satellite in space applications by compare, illustrating the value of thework in this paper.