SUKF在导弹姿态估计中的应用

针对弹道导弹惯性星光复合制导系统(SINS/CNS)中的导弹姿态估计问题,设计了一种利用星光观测向量估计导弹姿态的SUKF滤波器。该滤波器中的导弹姿态运动学方程采用Rodrigues参数来描述,避免了利用四元数时的频繁正规化操作,利用四元数估计方法(QUEST)建立了Rodrigues参数测量方程,并给出了滤波器各参数的设计方法。通过将该算法应用到某弹道模型的仿真中,检验了该方法的有效性。

Application of SUKF in missile attitude estimation

To determine precise missile attitude from star observations in ballistic missile guidance system integrated with strap-down inertial navigation system and celestial navigation system(SINS/CNS),is a scaled unscented Kalman filter(SUKF) is to estimate real-time missile attitude.In the filter,build a set of missile attitude kinematics equations are built based on Rodrigues parameters,which avoids attitude quaternion normalizations.And measurement equation of Rodrigues parameters is designed based on quaternion estimation(QUEST) methods.A simulation with the SUKF application to a missile ballistic trajectory is done and the result shows that the method is available.