Research On Satellite Attitude Determination Method Based On The Combination Of Star-Sensor And Gyroscope

Attitude parameters are the key parameters for the normal operation of the satellite.The control level of the satellite is directly restricted by its attitude determination accuracy,and the accuracy of the satellite attitude determination is affected by the used determination algorithm and the performance of the sensor.This article is aimed at the mainstream configuration model in the satellite attitude determination system of the combination of star sensor and gyroscope,and researches on the nonlinear filtering algorithm of satellite attitude determination.The factors that affect the accuracy of attitude determination are analyzed and explored in detail,improve algorithm on the basis of predecessors,and mathematical and semi-physical simulation experiments are carried out.The main content of the full text is as follows:First,the related theoretical basis of satellite attitude determination is introduced,including satellite orbit parameters and commonly used coordinate systems,the attitude motion equation based on Euler angles and quaternion description methods is established,and the corresponding measurement is established according to the working principle of the sensor model.Then establish the satellite attitude determination related system equations based on the quaternion,design the satellite attitude determination process based on the EKF algorithm,combined with mathematical simulation and analyze the satellite maneuver angle,sensor measurement deviation,output frequency and other parameters on the attitude accuracy influences.Secondly,aiming at the problem of inaccuracy in the establishment of the system model and the mismatch of the prior mathematical and statistical characteristics of related parameters,an improved adaptive UKF filtering algorithm(AUKF)is proposed on the basis of the UKF algorithm,which introduces an adaptive matrix and combines The residual covariance matching theory adjusts the measured noise covariance matrix,and according to the established filter divergence criterion,adaptively corrects the system noise covariance matrix to suppress the possible divergence in the filtering process.Finally,the ground semi-physical real-time simulation system based on the PXI real-time simulation platform is studied.Matlab,Lab VIEW and other software are used as the development environment to develop the posture control simulation model,realtime environment configuration program,and telemetry and remote control program.Using this simulation system,a simulation experiment of the aforementioned attitude determination algorithm was carried out,and the correctness of the semi-physical simulation system for satellite attitude determination was verified.