期刊
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS
卷 23, 期 4, 页码 604-610出版社
AMER INST AERONAUT ASTRONAUT
DOI: 10.2514/2.4605
关键词
-
The classic treatment of rendezvous mechanics and other problems involving the relative motion of two spacecraft assumes a circular reference orbit, allowing a simple closed form description of the motion. A solution is developed using an elliptical reference orbit, expanding the state transition matrix in powers of eccentricity, while retaining the explicit time dependence of the three-dimensional motion. The solution includes separate matrix elements for first- and second-order terms in eccentricity and for bath Cartesian and cylindrical coordinates. Assessment of the maximum errors in position and velocity components over one complete revolution of the reference satellite shows that the solution is accurate for practical purposes with eccentricities in the range 0-0.3. An example application is given for the proposed laser interferometer spare antenna gravity wave experiment.
作者
我是这篇论文的作者
点击您的名字以认领此论文并将其添加到您的个人资料中。
推荐
暂无数据