The multi axis coupling attitude control of a spacecraft with thrusters for attitude tracking is investigated. The attitude kinematics and dynamics are both described by error quaternions. The four error quaternion dy...The multi axis coupling attitude control of a spacecraft with thrusters for attitude tracking is investigated. The attitude kinematics and dynamics are both described by error quaternions. The four error quaternion dynamic equations are then transformed into four perturbed double integrators via linear transformations. An on off controller is designed based on the perturbed double integrators. The controller is determined by parabolic switching functions of the scalar error quaternion and the transfor...展开更多
Euler angle error model, rotation vector error model （RVE） and quaternion error model （QE） were qualitatively and quantitatively compared and an in-flight alignment filter algorithm was designed. This algorithm us...Euler angle error model, rotation vector error model （RVE） and quaternion error model （QE） were qualitatively and quantitatively compared and an in-flight alignment filter algorithm was designed. This algorithm used extended Kalman filter （EKF） based on RVE and QE separately avoi- ding the accuracy problem of the Euler angle model and used Rauch-Tung-Striebel（RTS） smoothing method to refine the accuracy recuperating the coning error for simplified RVE. Simulation results show that RVE and QE are more adapt for nonlinear filter estimation than the Euler angle model. The filter algorithm designed has more advantages in convergence speed, accuracy and stability comparing with the algorithm based on the three models separately.展开更多
基于微陀螺、加速度计、磁强计以及GPS模块构建了姿态航向位置参考系统(Attitude heading position ref-erence system,AHPRS)。首先,通过等效旋转矢量法由陀螺解算出估计姿态角;其次通过GPS、加速计的测量值,结合磁强计估计补偿姿态角...基于微陀螺、加速度计、磁强计以及GPS模块构建了姿态航向位置参考系统(Attitude heading position ref-erence system,AHPRS)。首先,通过等效旋转矢量法由陀螺解算出估计姿态角;其次通过GPS、加速计的测量值,结合磁强计估计补偿姿态角,推导基于误差四元数的滤波方程,滤波器的周期采用GPS的更新周期;然后,为降低导航方程的阶次,忽略姿态角的误差小量简化方程,提高了系统的解算实时性;最后,通过仿真与飞行试验验证了该姿态估计系统具有很好的姿态估计精度,满足微小型飞行器的姿态估计要求。展开更多
基金National Natural Science F oundation of China(No.10 172 0 12 )
文摘The multi axis coupling attitude control of a spacecraft with thrusters for attitude tracking is investigated. The attitude kinematics and dynamics are both described by error quaternions. The four error quaternion dynamic equations are then transformed into four perturbed double integrators via linear transformations. An on off controller is designed based on the perturbed double integrators. The controller is determined by parabolic switching functions of the scalar error quaternion and the transfor...
文摘Euler angle error model, rotation vector error model （RVE） and quaternion error model （QE） were qualitatively and quantitatively compared and an in-flight alignment filter algorithm was designed. This algorithm used extended Kalman filter （EKF） based on RVE and QE separately avoi- ding the accuracy problem of the Euler angle model and used Rauch-Tung-Striebel（RTS） smoothing method to refine the accuracy recuperating the coning error for simplified RVE. Simulation results show that RVE and QE are more adapt for nonlinear filter estimation than the Euler angle model. The filter algorithm designed has more advantages in convergence speed, accuracy and stability comparing with the algorithm based on the three models separately.
文摘基于微陀螺、加速度计、磁强计以及GPS模块构建了姿态航向位置参考系统(Attitude heading position ref-erence system,AHPRS)。首先,通过等效旋转矢量法由陀螺解算出估计姿态角;其次通过GPS、加速计的测量值,结合磁强计估计补偿姿态角,推导基于误差四元数的滤波方程,滤波器的周期采用GPS的更新周期;然后,为降低导航方程的阶次,忽略姿态角的误差小量简化方程,提高了系统的解算实时性;最后,通过仿真与飞行试验验证了该姿态估计系统具有很好的姿态估计精度,满足微小型飞行器的姿态估计要求。
