Research On Attitude Control Of Micro Nano Satellite In Large Angle Attitude Maneuver And Orbit Maneuver

Micro nano satellite has small volume,strong flexibility and high military and civil value.In order to meet the needs of complex space missions in the future,micro nano satellites must have high attitude control capability.However,the dynamic model of micro nano satellite is highly nonlinear,time-varying and uncertain,and there are many internal and external disturbances,which will seriously affect the attitude control accuracy of micro nano satellite.In view of the uncertainties such as model uncertainty,strong nonlinearity,strong coupling and uncertainty of internal and external disturbances,the micro satellite attitude control and micro satellite orbit maneuver stage stability control are studied in this paper.The research results have a certain reference value for the engineering application of high-precision attitude control of micro nano satellites.The main research contents of this paper are as follows:1)The research status of the micro nano satellite attitude control system and attitude control algorithm at home and abroad is analyzed,and the problems faced by the attitude control system are summarized.The existing problems in the attitude stabilization control of the micro nano satellite large angle attitude maneuver and orbit maneuver stage are summarized,and the solutions and research proposals are put forward.2)Under the application background of large angle attitude maneuver control and orbit control attitude stability control,the attitude dynamics and kinematics models of micro nano satellite based on zero momentum are established,and the environmental interference torque model and the mathematical model of actuator are given.3)The sinusoidal path planning method is used to plan the large-angle attitude maneuver,and the interference observer is designed to combine the terminal sliding mode control rate to track the path planning.Then the numerical simulation in Matlab environment,the simulation results show that the attitude control algorithm has a good tracking control effect,combined with sinusoidal path planning,and finally realized the rapid and stable control of the micro-nano satellite large-angle attitude maneuvering.4)The adaptive inversion sliding mode control method suitable for the attitude stability of the satellite orbital maneuver is studied,and the anti-saturation auxiliary system is designed to solve the input saturation problem during the orbital maneuvering phase.Then the numerical simulations have been carried out to prove that the anti-saturation auxiliary system can effectively reduce the impact of input saturation on the satellite attitude control system,improve the stability of the attitude control system,and realize the high-precision stability of the attitude of the micro-nano satellite in the orbital maneuvering phase.control.5)The effectiveness of the control algorithm designed in this paper is verified by semi physical simulation.In the semi physical simulation experiment,the three-axis attitude angle error in the large angle attitude maneuver stage can asymptotically converge to within ± 2 °,and the three-axis attitude angle error in the orbit maneuver stage can asymptotically converge to within ± 3.5 °.The simulation results show that the designed attitude control algorithm has good control performance.