摄动条件下椭圆轨道卫星相对运动研究  

Study on Satellite Relative Motion in Eccentric Orbit under Influence of Orbit Perturbation

作　　者：饶殷睿 殷建丰[1] 韩潮[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《上海航天》2014年第3期1-10,38,共11页Aerospace Shanghai

摘　　要：基于严格定义的相对轨道要素,考虑非球形引力、大气阻力和三体引力等摄动力的影响,用拟平均根数法添加相关摄动项,推导了椭圆轨道摄动条件下无奇点的卫星近距离相对运动模型。分析了考虑摄动力的影响时相对轨道要素的特性,并据此分析了各摄动力对卫星相对运动轨道预报精度的影响,比较了有无摄动的相对运动模型与精确解间的误差。算例验证了方法与结果的正确性和有效性。研究结果完善了相对轨道要素的基本理论,并将其适用范围拓展至摄动条件下的椭圆基准轨道卫星相对运动研究领域。Based on the strictly defined relative orbit elements,the interrelated perturbation terms were added by the quasi-mean element method in which the influence of perturbations due to nonspherical gravitational potential,atmospheric drag and third body gravitation was in consideration in this paper.The elliptical without singularity close relative motion in the condition of orbit perturbation was presented.Some characteristics of relative orbit elements were also analyzed in the case of orbit perturbation.The effect of these perturbation forces on the precision of orbit prediction was studied.The error analysis was carried out through a comparison of the relative motion considering or not considering perturbations with the results of exact solutions.The proposed method and conclusions were validated by simulation through some examples.The study improved the basic theory of relative orbit elements,and made this method also suitable for close relative motion under the elliptical reference orbit with perturbations conditions.

关 键 词：轨道摄动 椭圆轨道 卫星相对运动 相对轨道要素 相对运动方程 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]