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中文摘要：
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。
英文摘要：
Principles of navigating by CNS （celestial navigation system）, and SINS （strap-down inertial navigation system）/CNS are analyzed. Based on these principles, equations of state and observation and errors in measurement are derived, and the project of SINS/CNS is put forward. The integrated navigation system instantly revises the SINS by the navigation information of CNS. Results of math-simulation on sub-real traces of hypersonic reentry vehicle, proves that the integrated navigation system possesses advantages on grasping at the infomation of attitude in higher accuracy and feasibility of the project.
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