摘要
针对典型的星敏感器/陀螺姿态卫星确定算法运算复杂这一问题,提出了一种基于简化误差修正的星敏感器/陀螺卫星姿态确定算法。通过对陀螺角速度进行简化修正,减少了滤波器的状态变量,降低滤波器的复杂性。仿真结果表明:该算法在保证姿态确定精度的条件下,能够减少运算量,提高算法的实时性。
A satellite attitude determination algorithm based on predigest error correction with star-sensor/ gyro is proposed to solve the problem of typical satellite attitude determination algorithm operation complexity. By predigest correcting the angular velocity of gyro, the states variables and complexity of filter are reduced. Simulation resvlts indicate that the proposed algorithm provides effective performance in the com- putational complexity and instantaneity when it performances as the same as the typical algorithm in attitude determination precision.
出处
《航天电子对抗》
2013年第5期15-18,22,共5页
Aerospace Electronic Warfare
关键词
姿态确定
四元数
陀螺漂移
星敏感器
简化误差修正
attitude determine
quaternion
gyro excursion
star-sensor
predigest error correction
