| 椭圆轨道上航天器位置的一种计算方法 |
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| 引用本文： | 顾晓勤.椭圆轨道上航天器位置的一种计算方法[J].电子科技大学学报(社会科学版),2003(6). |
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| 作者姓名： | 顾晓勤 |
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| 作者单位： | 电子科技大学中山学院 广东中山528403 |
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| 摘 要： | 给出了沿椭圆轨道运动航天器真近点角和偏近点角的运动方程。用迭代法求出偏近点角变化规律,讨论了迭代收敛的充分条件。用数值积分方法求出真近点角与时间的关系曲线。数值模拟结果表明,该文提出的迭代计算方法有效且精度高,可作为航天器轨道计算的一种方法。
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| 关 键 词： | 航天器 偏近点角 真近点角 迭代法 |
A Calculating Method for Epicyclic Motion of Spacecraft |
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| Gu Xiaoqin.A Calculating Method for Epicyclic Motion of Spacecraft[J].Journal of University of Electronic Science and Technology of China(Social Sciences Edition),2003(6). |
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| Authors: | Gu Xiaoqin |
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| Abstract: | The analytic formulations are presented of the epicyclic motion of a spacecraft about the true anomaly and the eccentric anomaly. The eccentric anomaly as a function of time is calculated by the iterative method. And the iterations convergence-condition is discussed. The relationship between the true anomaly and the time is gotten by the numerical integral method. The numerical simulations results of this approach are presented. |
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| Keywords: | spacecraft eccentric anomaly true anomaly iterative method |
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