摘要
针对低轨运行的编队卫星在J2和大气阻力摄动作用下其编队队形会很快遭到破坏的情况,以平均轨道根数描述卫星编队中从星相对于主星的相对轨道构形,基于高斯摄动方程,给出了在这两种摄动作用下的、以平均轨道根数为被控制量的状态方程并设计了相应的非线性控制律控制卫星编队队形。最后,数值仿真结果验证了所给出控制律的有效性。
Satellites formation moving on low earth orbit suffers from the influence of J2 and atmosphere perturbation, then the orbit configuration of the formation will be destroyed in a short time. The relative orbit of the follower satellite with respect to the leader one is described by the mean orbit elements. Under the J2 and atmosphere perturbation, a state equation with the mean elements as the controlled variables is proposed based on Gauss perturbation equation and a nonlinear control law is presented accordingly. In the end, simulation results show the effectiveness of the given controller.
出处
《系统工程与电子技术》
EI
CSCD
北大核心
2007年第8期1327-1330,共4页
Systems Engineering and Electronics
关键词
卫星编队
大气阻力摄动
平均轨道根数
非线性控制
satellites formation
atmosphere perturbation
mean orbit element
nonlinear control
