中文摘要：

近空间高超声速飞行器具有高动态性特点,能实现精确打击,要保证其高精度,导航系统是关键。惯性导航技术具有可靠性好、输出连续的优点,是近空间巡航飞行器的核心导航系统。本文利用Simulink与M语言结合完成对近空间高超声速飞行器惯性导航系统的仿真研究。构建了近空间高超声速飞行器惯性导航系统的Simulink仿真模型,通过对静基座下的惯导导航误差进行分析,验证了仿真系统的正确性。对近空间高超声速飞行器的航迹进行了仿真,分析了飞行速度对向心加速度及哥氏加速度的影响,对开展近空间高超声速飞行器惯性导航系统的研究具有良好的参考意义。

英文摘要：

The near space hypersonic vehicle has strong dynamic features and precise attack capability. The navigation system is the key to ensure the high precision of the vehicle. The inertial navigation system （INS） can provide the all-weather and full-state movement information of the vehicle. And it also takes the advantages of reliability and continuous output. Thus, the INS is the core navigation system of the near space hypersonic vehicle. In this paper, the simulink and M-file are used to establish the inertial navigation system of hypersonic vehicle, and simulation and research are conducted for the system. The simulink model is completed for the INS on the hypersonic vehicle, and the feasibility of the model is verified as well. The tracks of the hypersonic vehicle are simulated, and the effects of the vehicle velocity on the centripetal acceler-ation and Coriolis acceleration are analyzed. The results have reference values for the study of the inertial navigation system on the hypersonic vehicles.