RCS Simulation of Spacecraft Based on Orbital Dynamics
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 1 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 2. 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.
RCS simulation physical optics orbital dynamics
Xiangying Li Xin Meng
Graduate School of the Chinese Academy of Sciences Beijing, China Center for Space Science and Applied Research,Chinese Academy of Sciences Beijing, China
国际会议
北京
英文
588-592
2009-10-27（万方平台首次上网日期，不代表论文的发表时间）