摘要
针对给定星下点的精确重访轨道设计,提出了一种已知两星下点精确重访约束下的圆回归轨道设计方法。分析了卫星的地心矢量同星下点地心矢量的关系,将精确星下点重访约束轨道设计问题转换为惯性坐标系内的一个动矢量同动坐标系内一个定矢量在惯性系下的重合问题。建立了不同轨道参数各自对应的目标函数,通过对目标函数零点的搜寻确定相应轨道参数,完成轨道设计。计算及仿真结果表明,所提出的构造目标函数并搜索零点的方法能够设计出满足约束条件的轨道,达到了预期目标。
A new orbit design method is needed for precise revisit the given ground track points. A method of designing precise revisit of 2 given ground track round repeating orbit was proposed. The relationship between the satellite geocentric vector and the ground track geocentric vector was analyzed; the problem was converted to the coincidence problem in the inertial coordinate system of a motion vector in inertial coordinate system and a constant vector in the moving coordinate system. Different target functions were constructed, while orbit elements were obtained by searching the zeros of the corresponding function. Calculation and simulation results demonstrate the effectiveness of the proposed approach,
出处
《中国空间科学技术》
EI
CSCD
北大核心
2016年第4期67-73,共7页
Chinese Space Science and Technology
基金
上海市科学技术委员会资助课题(14XD1423400)
关键词
星下点
精确重访
轨道设计
回归轨道
仿真
ground track point
precise revisit
orbit design
repeating orbit
simulation
