基于非开普勒轨道的高超声速临近空间飞行器自主天文导航研究  

Study on the Autonomous Celestial Navigation of Near Space Vehicles With Hypersonic Speed Based on Non-Keplerian Orbits

作　　者：李海林[1] 吴德伟[1] 

机构地区：[1]空军工程大学信息与导航学院,西安710077

出　　处：《空间科学学报》2012年第6期874-880,共7页Chinese Journal of Space Science

基　　金：国家自然科学基金项目资助(61273048)

摘　　要：针对航天器自主导航方法不适合高超声速临近空间飞行器的问题,研究了基于非开普勒轨道的高超声速临近空间飞行器自主天文导航方案.论述了基于非开普勒轨道的自主天文导航机理,通过对高超声速临近空间飞行器受力分析,建立了动力学方程;利用矢量倒数法则推导出空间运动方程;设计了基于非开普勒轨道的状态模型和基于星光折射间接敏感地平的观测模型,采用卡尔曼滤波进行了仿真验证.仿真结果表明,基于非开普勒轨道的高超声速临近空间飞行器自主天文导航可达到较高的位置和速度精度.In allusion to the problem that the aircraft autonomous celestial navigation is not suitable for the near space vehicles with hypersonic speed, an approach of the autonomous celestial navigation of near space vehicles with hypersonic speed based on non-Keplerian orbits is studied. Mechanism of the autonomous celestial navigation based on non-Keplerian is analyzed, and the dynamic equations are developed by analyzing the strength of near space vehicles with hypersonic speed. The space motion equation is educed using the vector derivatives rules. States model based on non-Keplerian orbits and measurement model using the concept of stellar horizon atmospheric refraction are de- signed, and the Kalman filter simulation is adopted. Results show that the autonomous celestial navigation of near space vehicles with hypersonic speed based on non-Keplerian orbits can meet the requirement of high precision for position and velocity, which is important for further research on the near space vehicles with hypersonic speed.

关 键 词：非开普勒轨道 高超声速临近空间飞行器 天文导航 星光折射间接敏感地平 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]