Research On Formation Keeping Control Method Of Lunar Satellite Formation

Nowadays,satellite formation technology can develop rapidly because of its unique advantages.With the rapid development of human aerospace technology,it is very worthwhile to apply satellite formation technology to space missions around other celestial bodies.Based on the background of the lunar space environment,this paper studies the maintenance control of satellite formation,taking into account the characteristics of lunar satellite space operation.The main work is as follows:Firstly,the dynamic model used in the design of the satellite formation configuration controller is deduced,including the more accurate nonlinear dynamic model,which is suitable for the precise nonlinear dynamic model of the orbital orbit as the circular reference orbit.The linearized CW equation applied to the circular reference orbit and the Lawden equation for the elliptical reference orbit are based on the dynamic model of the near-point angle.The spatial environment of the moon is analyzed,and the perturbation and the perturbation of the relative motion between the star and the star are given.The linearity of the dynamics model is linearized The error is analyzed and verified.Considering the complexity of the disturbance,a robust sliding mode variable structure control method is used to design the control of the formation configuration.The control problem of the formation control is discussed for the circular reference orbit or elliptical orbit Research and simulation verification,and then aim at the orbital information when the main star is missing,the controller is designed by using the time varying part as the disturbance,and the effect of the controller is verified by simulation.The adaptive control law is designed for the formation kinetics model of the circular reference orbit with the uncertain disturbance and the elliptical reference orbit system with simultaneous perturbation and time-varying parameter perturbations.The adaptive control law is designed.The uncertainty of the uncertain term depends on the relative state error between the master and the star,and can estimate the error range of the relative precision perturbation acceleration,and verify the performance of the control law.Finally,based on the elliptical orbit as the reference orbit,based on the dynamicmodel under the near-near-point angle domain,the sliding mode control method and the backstepping method are used to study the formation configuration problem.The feasibility of the controller design by the dynamic model of the near-point angle.