摘要
提出了一种保持卫星间距离不变的编队飞行设计新方法。卫星轨道采用小偏心率假设,相对运动由参考系中的线性化动力学方程描述。通过对相对距离方程中的时间项进行单独消元,获得了一组约束方程,并进行了简化处理。提出并证明了多星系列化设计方法,减少了保持卫星群间距不变的约束方程数目。给出了星间距离计算公式,并分析了三种特殊情况的约束条件。采用包含地球扁率摄动的力学模型在地心惯性系下进行运动仿真,验证了设计方法。
A novel methodology to design satellite formation flying with invariant inter-satellite distance is pres- ented. The orbits are assumed to be Keplerian with small eccentricity. The motion of the satellites, with respect to the orbital reference frame, is described by linearized dynamic equations. One pair of quadratic constraint equa- tions is obtained and simplified by eliminating the time term dependence from the expression of the relative dis- tance. A sequential design approach is presented and proved, which much decreases the number of constraint equa- tions for the whole cluster. The formulation of distance is given and constraint conditions for three distinct cases are analyzed. The applications of the constraint equations are validated with respect to simulations using J2 dynamics.
出处
《科学技术与工程》
北大核心
2013年第12期3356-3361,共6页
Science Technology and Engineering
基金
国家高科技研究与发展计划(2011AA2015)资助
关键词
卫星编队飞行
恒定相对距离
小偏心率
系列化设计
地球扁率摄动
satellite formation flying invariant relative distanceearth oblate disturbanceeccentricitysequential design
