弹用捷联式惯性导航系统数值仿真

Numerical Simulation of Strapdown Inertial Navigation System

以某导弹规划航迹为对象,对捷联式惯性导航系统进行了数值仿真.通过规划航迹数据提取出弹体的比力和角速度信息,输入至惯性测量器件模型,以其输出激励导航计算模块,得到弹体的位置、速度、姿态角误差等导航数据,将其与规划航迹中相应的数据对比得到计算误差.同时由捷联式惯性导航系统的误差方程建立SIMULINK模型,给出了模型的仿真结果.对比计算误差与模型仿真结果,验证了捷联式惯导系统数值仿真的正确和有效性.

The numerical simulation of strapdown inertial navigation system is investigated in this paper based on the planning track data of an anonymous missile. The specific force and angle velocity of the missile body extracted from the data are input to module of inertial measurement units（IMU）, then the navigation parameters computation module is feeded by the output of IMU, finally, the navigation states.positon, velocity and attitude angle are calculated. The navigation state errors are attained by subtracting planning track from the caculated one. Meanwhile, the equations of inertial navigation system error is simulated. The difference between computed state errors and simulated ones is quite small, then the numerical simulation of strapdown inertial navigation system is proved to be correct and valid.