本文簡(jiǎn)單介紹了高超聲速飛行器，并通過(guò)分析目前應(yīng)用較為普遍組合導(dǎo)航方式，提出了采用SINS/GPS/CNS 組合導(dǎo)航作為高超聲速巡航導(dǎo)彈的中段制導(dǎo)方案。本文采用四元數(shù)法進(jìn)行SINS 計(jì)算，并運(yùn)用聯(lián)邦濾波的方法對(duì)組合導(dǎo)航進(jìn)行了仿真。仿真程序是在軌跡發(fā)生器產(chǎn)生高超聲速巡航飛行器飛行軌跡及相關(guān)參數(shù)的基礎(chǔ)上進(jìn)行的，仿真結(jié)果表明了高
超聲速巡航飛行器中制導(dǎo)采用SINS/GPS/CNS 組合導(dǎo)航系統(tǒng)的可行性。
關(guān)鍵詞：高超聲速巡航飛行器；組合導(dǎo)航；中制導(dǎo)；聯(lián)邦濾波
Abstract：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 feasibility of integrated SINS/GPS/CNS system as midcourse navigation of hypersonic cruise aircraft.
Keywords: Hypersonic Cruise Aircraft，Integrated Navigation，Midcourse Navigation，F(xiàn)ederated Filtering