Spacecraft Relative Navigation Based on Relative Mean Orbit Elements
In this paper,a simple and effective algorithm for determining the Relative Mean Orbit Elements (RMOEs) is presented. The short distance relative motion equations of spacecrafts are described by means of RMOEs, and the linear differential equations about RMOEs are established. The Converted Measurement Kalman Filter(CMKF) , which converts nonlinear measurements to the linear ones in the reference Cartesian coordinate frame, is applied to simplify the estimation algorithms of the relative navigation. The numerical simulation illustrates both the precision of the relative motion equations based on RMOEs and the performance of the CMKF for relative navigation.
Relative Navigation Relative Mean Orbit Elements Relative Motion Equations Converted Measurement Kalman Filter
Liu Yong Xu Shijie
Lab 504, School of Astronautics, Beijing University of Aeronautics and Astronautics,Beijing 100083,China
国际会议
The 11th International Space Conference of Pacific-basin Societies(第11届环太平洋国际航天会议)
北京
英文
238-247
2007-05-16（万方平台首次上网日期，不代表论文的发表时间）