高轨飞行器精确导航的载波相位时间差分/捷联惯导紧组合算法

详细信息

Time-differenced Carrier Phase/SINS Tight Integration Algorithm in the High-precision Navigation for High Earth Orbit Spacecraft

¹ College of Aerospace and Material Engineering,National University of Defense Technology,47 Yanwachizheng Street,Changsha 410073,China

摘要: 提出了基于载波相位时间差分与捷联惯导紧组合的方法对高轨飞行器进行自主导航,其中捷联惯导主要在飞行器进行轨道机动时使用,分析了载波相位观测方程中的误差因素,通过SRUKF建立了组合导航非线性滤波模型,研究了周跳检测与修复策略。研究表明,提出的导航方法避免了整周模糊度的求解和周跳的影响,因而可使导航系统具有高精度和高可靠性。
- 载波相位 /
- 时间差分 /
- 组合导航 /
- 高轨飞行器
Abstract: The paper proposed a method based on time-differenced carrier phase and strapdown inertial navigation system(SINS) in autonomous navigation.The SINS worked only when the spacecraft maneuvered.In this study,the error factors in the carrier phase observation were analysed.We established the the nonlinear model of integrated navigation by SRUKF and studied cycle slip detection and repair strategies.Our findings indicated that the proposed navigation method avoided the solution of ambiguity and the impact of cycle slips,which made the navigation system with high precision and reliability.
- carrier phase /
- time difference /
- integrated navigation /
- cycle slip detection and repair