摘要
针对弹道导弹在工程实际中噪声特性的不确定性及其引起的模型误差,本文提出了一种适用于弹道导弹的SINS/CNS组合导航方案。该方案融合了简单组合模式和基于全面最优校正的组合模式特点,采用自适应卡尔曼滤波来保证滤波的稳定性和鲁棒性,并根据导弹的飞行弹道,建立了合理、完备的弹载导航星表。仿真验证结果表明,该导航方案可以达到全面提高弹道导弹导航参数精度的目的。
Combined with the characteristics of ballistic missile and the model error caused by uncer-tain noise characteristics in engineering practice, this paper proposes a SINS/CNS integrated navigationsystem suitable for ballistic missiles. This system, integrated some characteristics of simple combinationmodels and overall optimal correction combination models, uses the adaptive Kalman filtering to ensurethe stability and robustness of the filter. In the simulation, according to the missile trajectory, it establi-shes a reasonable, complete guide star catalog of missile. The simulation illustrates that this navigationscheme can improve the precision of navigation parameters of ballistic missile.
出处
《航空兵器》
2015年第2期21-25,共5页
Aero Weaponry
基金
航空科学基金资助项目(20110151002)
关键词
惯性导航
天文导航
组合导航
自适应卡尔曼滤波
弹载导航星表
inertial navigation
celestial navigation
integrated navigation
adaptive Kalman filter
guide star catalog of missile
