Attitude prediction method for micro satellite on-orbit launch based on Monte-Carlo method
Micro satellites based on solid thrusters launched on-orbit are becoming increasingly widely used in the field of space on-orbit services,and the attitude of the micro satellite during separation is the key to determining the success of the mission.In order to predict the attitude range of a micro satellite during on-orbit launch separation,a multi rigid body dynamics theory and a Hertz contact model are used to establish a launch dynamics simulation model for the micro satellite-satellite platform system.A Monte-Carlo based method for predicting the separation attitude of the micro satellite on-orbit is proposed to address the thrust eccentricity generated during the production and assembly process of solid thrusters.The simulation results show that the separation angular velocity of the micro satellite followed a normal distribution law.Through ground simulation launch experiments,the launch dynamics simulation model and attitude prediction method are accurate and feasible,which could provide reference for the design of micro satellite on-orbit rapid launch systems and the study of launch target accuracy.
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维普
