Title :
RCS simulation of spacecraft based on orbital dynamics
Author :
Li, Xiangying ; Meng, Xin
Author_Institution :
Grad. Sch., Chinese Acad. of Sci., Beijing, China
Abstract :
A method for RCS simulation of spacecrafts is developed. The Keplerian orbit and its perturbations are discussed before a simulated trajectory is given. Based on orbital dynamics and Euler´s transformation, the attitudes of spacecraft are determined and the incident wave angle is calculated. Then, a 3D model of spacecraft is constructed for RCS calculation through physical optics (PO) method. The simulation results demonstrate good estimates of RCS for spin-stabilized spacecrafts. The method also shows efficiency of RCS simulation which can be used for further research on EM reflectivity of in-orbit spacecrafts.
Keywords :
electromagnetic wave propagation; electromagnetic wave reflection; radar cross-sections; space vehicles; target tracking; EM reflectivity; Euler transformation; Keplerian orbit; in-orbit spacecrafts; orbital dynamics; physical optic method; simulated trajectory; spacecraft RCS simulation; spacecraft attitude; spin stabilized spacecraft; Electromagnetic scattering; Orbital calculations; Physical optics; Position measurement; Radar cross section; Radar scattering; Reflectivity; Satellites; Space vehicles; Spaceborne radar; RCS; orbital dynamics; physical optics; simulation;
Conference_Titel :
Microwave, Antenna, Propagation and EMC Technologies for Wireless Communications, 2009 3rd IEEE International Symposium on
Conference_Location :
Beijing
Print_ISBN :
978-1-4244-4076-4
DOI :
10.1109/MAPE.2009.5355607
