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。
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.
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2007年第5期585-589,599,共6页
Journal of Nanjing University of Science and Technology
基金
"微小型航天器系统技术"长江学者和创新团队发展计划(IRT0520)
关键词
星敏仪
捷联惯导/星光
组合导航
star sensors
strap-down inertial navigation system/celestial navigation system
integrated navigation
