摘要
弹道导弹飞行特点对其导航系统提出了较高的技术要求,因此提出一种惯性/双星/天文组合导航方案对弹道导弹实时估计和修正导航误差,提高导航精度,该组合导航方案以惯性导航系统与天文导航系统的姿态角差值、惯性导航系统与双星定位导航系统的位置差值作为观测量,建立弹道导弹导航系统的数学模型和观测方程,以无反馈模式联邦滤波器在线估计弹道导弹导航参数误差值。通过计算机仿真并分析仿真结果:和惯性导航系统相比较,这种组合导航系统可以提高弹道导弹导航精度,适合弹道导弹组合导航。
This paper introduces an INS/double - star/CNS integrated navigation mode for ballistic missile to estimate and correct the error of parameters and enhance the accuracy. The angle differences of INS and CNS, the position differences of INS and double - star navigation are used as measurements to establish math model and observation equation for the navigation system of ballistic missile. The error of the integrated navigation parameters for ballistic missile can be online estimated by non - feedback federal filtering. The results of computer simulation shows that compared with SINS navigation, this integrated system can enhance the accuracy of navigation system and is suitable for the navigation of ballistic missile.
出处
《计算机仿真》
CSCD
北大核心
2009年第3期40-42,107,共4页
Computer Simulation
关键词
组合导航
惯性导航
天文导航
联邦滤波
Integrated navigation
Inertial navigation
Starlight navigation
Federal filter
