高速自旋飞行器惯性制导系统技术研究

Study on the Inertial Guidance System of the High-Speed Spinning Aircraft

高速自旋飞行器对导航制导系统提出了较高的技术要求,针对目前在高速自旋飞行器制导系统广泛使用的平台式惯性导航系统和捷联式惯性导航系统(SINS)各自存在的优缺点,提出一种新型的单轴稳定SINS。该系统通过在原捷联IMU上增加一个横滚隔离环隔离了飞行器的高速自旋运动,并设计了适用于单轴稳定SINS的力学编排,保证了导航定位精度。通过仿真,比较分析了采用上述两种惯导系统的自旋飞行器的姿态和定位精度。仿真结果表明,单轴稳定SINS在减小其体积和重量的同时又保证了系统的姿态和定位精度。研究结果可为高速自旋飞行器惯导系统的工程设计提供理论参考依据。

The higher technical requirements are presented for high-speed spinning aircraft guidance systems for navigation.Viewing of their respective shortcomings of the platform navigation system and strapdown inertial navigation system（SINS） used in the spinning aircraft guidance system,a new type of single-axis stable SINS is provided.By adding a roll isolated ring in the strapdown IMU for isolating the movement of the high-speed roll aircraft,mechanical arrangement is designed for single-axis stable SINS,which ensures the accuracy of navigation and positioning.By simulating,the attitude and positioning accuracy of spinning missiles using the above two kinds of inertial navigation systems are compared and analyzed.The simulation results show that the single-axis stable SINS is decreased in size,in weight,and guarantee the accuracy of the system.The study results offer an academic basis for designing of single-axis stable SINS.