战略导弹惯性/星光复合制导技术研究

Study of the Inertial/Celestial Integrated Guidance System Technique for Strategic Missile

以Kalman滤波为基础,研究了惯性/星光复合制导系统的原理和特点,并对系统进行了计算机仿真。通过将惯导系统和星敏感器所测得的战略导弹相关姿态信息进行数据融合,估计出复合制导系统的误差状态量,进而修正惯导系统的位置、速度和姿态角误差。仿真结果表明,采用惯性/星光复合制导可以有效地提高战略导弹的姿态精度。

Based on Kalman filtering, inertial/celestial integrated guidance system is simulated and its principle and characteristics are researched. The error of the integrated guidance system is estimated by fusing the data of strategic missiles attitude acquired by inertial guidance system （IGS） and star sensors, so the errors of position, velocity and attitude angle in the IGS can be decreased. The simulation result shows that the attitude accuracy is effectively improved after integrated guidance is introduced.