椭圆轨道上航天器位置的一种计算方法

详细信息

A Calculating Method for Epicyclic Motion of Spacecraft

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。
- 航天器 /
- 偏近点角 /
- 真近点角 /
- 迭代法
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 iteration's convergence-condition is discussed. The relationship between the true anomaly and the time is gotten by the numerical integral method. The numerical simulation's results of this approach are presented.
- spacecraft /
- eccentric anomaly /
- true anomaly /
- iterative method