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该文在分析星光导航原理的基础上,给出了捷联惯导/星光飞行器组合导航方案;推证了该组合导航系统的状态方程和观测方程,分析了星敏仪量测误差。结合高超声速跨大气层再入飞行体的模拟飞行轨道,进行了组合导航数学仿真。结果证实该方案能够利用星光导航信息对捷联惯导进行即时修正,表明捷联惯导/星光组合导航系统在较精确地获取载体姿态信息方面具有优越性。
Based on the analysis of the principle of star navigation, this paper presents a scheme of SINS / Starlight integrated navigation. The state equation and observation equation of the integrated navigation system are deduced. The measurement error of star sensitive instrument is analyzed. Combining the simulated flight trajectories of hypersonic transonic reentry vehicle, a combined navigation mathematical simulation was carried out. The results show that this scheme can make instant correction of SINS with star navigation information, which shows SINS / Star Integrated Navigation System has superiority in obtaining carrier attitude information more accurately.