摘要
为了提高弹道导弹捷联惯性/天文组合导航系统的精度及其在实际工作环境下的自适应性,本文对导航元器件误差进行深入分析,提出了一种基于自适应卡尔曼滤波的状态转移矩阵算法。该方法将简化的Sage-Husa自适应卡尔曼滤波算法与状态转移矩阵校正方法相结合,通过自适应滤波方法来补偿由于复杂工作环境而引入的元器件误差,并利用状态转移矩阵法校正主动段积累的速度、位置误差。通过实际弹道数据的仿真分析表明,新算法能够适应实际工作环境中元器件误差的时变特点,增强了系统对工作环境的适应能力,提高了导弹的导航精度。
In order to enhance the precision and adaptability of strapdown inertial/celestial navigation system for ballistic missile in actual working condition, this paper analyzes the element error and proposes a new method of transmission matrix based on adaptive Kalman filter. The simplified Sage-Husa adaptive filtering method and the transmission matrix method are synthesized. Adaptive filtering method is used to compensate the element error which is induced by the complex working environment, and transmission matrix method is used to revise the speed and position error. The simulation results show that the new method can adapt to the time-varied characteristic of element error, and can improve the adaptability and precision of navigation system.
出处
《航空兵器》
2009年第4期12-16,23,共6页
Aero Weaponry
基金
国家863高新技术项目
关键词
惯性导航
天文导航
组合导航
信息融合
自适应卡尔曼滤波
inertial navigation
celestial navigation
integrated navigation
information fusion
adaptive Kalman filter
