摘要
空天飞行器往返于大气层内外,持续工作时间长。捷联惯性/天文组合导航自主性强、隐蔽性好,是最适合空天飞行器的导航方式之一。为提高传统天文定位的导航精度和可靠性,解决其在机载应用中水平基准制约的问题,分析了平台误差角和位置误差对高度角量测的影响,提出了一种以天体高度角为量测信息的捷联惯性/天文深组合导航算法。该算法采用卡尔曼滤波器进行最优估计,可有效估计并补偿系统的姿态误差,减少天文导航定位对水平基准的依赖。仿真表明,单星观测条件下,导航系统姿态误差快速收敛,定位的均方根误差在200 m以内,且系统导航性能随导航星数量的增加而提高。
Aerospace vehicles usually work both inside and outside the Earth＇s atmosphere for long-range missions, and strap-down inertial navigation system （SINS） / celestial navigation system （CNS） integrated navigation method has been considered as an appropriate navigation solution for aerospace vehicles due to its autonomous and concealment capabilities. In order to overcome the limitation of horizontal reference in CNS and improve its accuracy and reliability, this paper analyzes the influence of platform error angles and positioning errors on altitude angle measurement, and proposes a novel algorithm for SINS/CNS tightly integrated navigation based on measured altitudes of celestial bodies. Kalman filter is utilized in this approach in order to effectively compensate attitude errors of SINS and reduce the dependence on horizon reference in CNS. Simulation result demonstrates that the convergence of attitude errors is rapid when single navigational star is observed, and the estimated root mean square positioning error （RMSE） is within 200 m. It also shows that more navigational stars will improve system navigation performance.
出处
《中国惯性技术学报》
EI
CSCD
北大核心
2013年第4期478-483,共6页
Journal of Chinese Inertial Technology
基金
海军装备预研项目(4010103)
中央高校基本科研业务费专项基金资助(YWF-10-01-B-30)
关键词
空天飞行器
捷联惯性
天文
深组合导航
天体高度角
aerospace vehicles
SINS/CNS
tightly integrated navigation
altitudes of celestial bodies
