Research On Attitude Stability Control Of Statellite Spin Cancellation

With the development of society and the continuous development of human space resources,the field of aviation science and technology is more and more extensive,which puts forward higher requirements for the control system of spacecraft,and the disturbance of the space unknown environment and the influence of the flexible parts of spacecraft,the influence of non-linear factors becomes more and more serious.This requires the spacecraft control system to meet people's requirements for high-precision,high stability and high reliability.This paper mainly studies the attitude stability control of three-axis stabilized satellite,and the direct parameterization method is used to set up the controller to stabilize the satellite attitude and simulate the simulation.Firstly,this paper defines the coordinate system required by the subject,introduces several attitude description methods,such as Euler angle,four-element number,Rodrigo parameter and modified Rodrigo parameter,and discusses the advantages and disadvantages of each description method,and the modified Rodrigo parameters are used to describe the attitude of the satellite.After that,the kinematic model and dynamics model of satellite attitude were established,and the attitude parameters of satellite were measured by means of gyroscope,sun sensor,star sensor and leveling instrument,and the whole star 0 Momentum flywheel system was selected by executing mechanism.This topic carries on the analysis to the satellite just entering the orbit situation,after the separation of the satellite and the launch vehicle into the orbit,because of the impact of the separation with the launch vehicle,the expansion of the solar panel and the disturbance of the space gas will cause the satellite to produce a certain initial angular rate,then the satellite first has to undergo the initial rate damping process(that is,the spin)In order to stabilize the satellite angular velocity,the second-order nonlinear equation of satellite attitude is deduced by the method of mathematical modeling,and the moment of inertia matrix is diagonal array.The feasibility of parametric method is verified by simulation analysis.Satellite failure,service spacecraft after the failure of satellite capture,the complex will have a certain initial angular rate,the need to service spacecraft bias attitude control system to control the complex,so that it works stably.Firstly,the complex body system is modeled and analyzed,the second-order nonlinear equation is deduced,then the parametric controller isdesigned to control the attitude of the composite body,so that the complex is finally stabilized.Finally,the feasibility of parametric method is verified by simulation analysis.