摘要
大气摄动会造成近地轨道卫星编队构形产生沿航迹方向漂移。面质比直接决定了大气阻力引起的长半轴衰减,因此可以通过调整面质比实现对构形沿航迹漂移的控制。以构形绕飞中心的漂移距离和编队卫星长半轴差作为输入量,以面质比改变量作为控制量,研究了编队构形沿航迹模糊控制方法。设计了输入量的模糊语言变量和模糊控制规则;根据Mamdani模糊推理算法进行模糊推理;以面积中心法实现了控制量解模糊化。仿真结果表明,对于文中给定的算例,沿航迹漂移距离能够控制在20m之内。对于构形存在初始误差的情况下,该方法也具有较好的控制效果。
LEO satellite formation configurations may get an in-track drift under the perturbation of atmosphere. The area-mass-ratio of the satellite directly influences the decrease of semi-major axis caused by the perturbation atmosphere, so the in-track drift can be controlled by the adjustment of the area-mass-ratio. Taking the drift distance of the formation center and the difference of the semi-major axes as the input, and the change of area-mass-ratio as the control, a fuzzy controller for in-track drift of formation configuration was studied. On the basis of the design of the input fizzification and the fuzzy rules, the Mamdani inference was used in the fuzzy inference, followed with a centroidal defuzzification. The simulation indicates that the drift distance can be controlled within 20m, with the given condition. The method proves effective, even with the presence of initial errors.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2007年第3期6-10,共5页
Journal of National University of Defense Technology
基金
国家自然科学基金资助项目
关键词
编队构形
大气阻力
模糊控制
formation configuration
atmosphere drag
fuzzy control
