SINS/GPS/CNS组合导航在高超声速巡航飞行器上的应用

The Application of SINS/GPS/CNS Integrated Navigation in Hypersonic Cruise Aircraft

本文简单介绍了高超声速飞行器,并通过分析目前应用较为普遍组合导航方式,提出了采用SINS/GPS/CNS组合导航作为高超声速巡航导弹的中段制导方案。本文采用四元数法进行SINS计算,并运用联邦滤波的方法对组合导航进行了仿真。仿真程序是在轨迹发生器产生高超声速巡航飞行器飞行轨迹及相关参数的基础上进行的,仿真结果表明了高超声速巡航飞行器中制导采用SINS/GPS/CNS组合导航系统的可行性。

This paper simply introduces hypersonic cruise aircraft and puts forward SINS/GPS/CNS navigation as midcourse navigation of it through the analysis of several universally integrated navigation models. SINS is calculated by quaternions and the integrated navigation system is simulated by federated Kalman filtering method in this paper. Track generator is used to generate a track and other correlation parameters of hypersonic cruise aircraft, then simulation can be made at the base of it. While simulation results show the feasibihty of integrated SINS/GPS/CNS system as midcourse navigation of hypersonic cruise aircraft.