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采用球面几何方法,严格定义了相对轨道要素(ROE),推导了其与绝对轨道要素(AOE)之间精确的相互转换关系;针对近圆和椭圆基准轨道相对运动情况,给出相对轨道要素和绝对轨道要素之间相互转换的近似式,以满足不同任务的要求;分析了卫星近距离相对运动时相对轨道要素的一些特性;基于相对轨道要素,推导了无奇点问题的、适用于近圆和椭圆基准轨道的近距离相对运动方程;据此分析了椭圆基准轨道卫星的相对运动特性,对比近圆基准轨道相对运动模型和精确解的结果进行了误差分析,通过典型算例验证了本文提出的方法和结果的正确性和有效性。论文研究结果完善了相对轨道要素的基本理论,统一了近圆轨道和椭圆轨道的卫星近距离相对运动的描述形式。
Using the spherical geometry method, the relative orbital element (ROE) is strictly defined, and the exact reciprocal relationship between it and the absolute orbital element (AOE) is deduced. According to the relative orbital elements and the relative motion of elliptical reference orbit The absolute orbital elements of the conversion between the approximate formula to meet the requirements of different tasks; analysis of satellite relative motion of orbital elements of the relative movement of some of the characteristics; based on the relative orbital elements, non-singularity problem is derived for near-circle And the elliptical reference orbit. Based on this, the relative motion characteristics of elliptical orbit satellites are analyzed. The error analysis is made on the relative motion model of the near-circular reference orbit and the result of the exact solution. The correctness and validity of the methods and results. The results of the thesis improve the basic theory of relative orbital elements and unify the description form of near-satellite relative motion between near-circular orbits and elliptical orbits.