true anomaly

For elliptic reference orbits, the variation of the relative trajectory is dependent on the eccentricity of the reference orbit and the initial true anomaly and that only one parameter group can provide the desired trajectory.

对于椭圆参考轨道编队，编队队形的变化与主星的轨道偏心率及编队初始真近点角的选择密切相关，且满足队形要求的从星运动参数组合是惟一的。

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In this paper, true anomaly of the chief satellite was taken as basic parameter, in unperturbed situation, formation flying relative dynamic equation was modeled.

稳定性是卫星编队动力学状态耦合分析的重要内容之一。

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Calculating Method of Series for the True Anomaly of a Spacecraft Elliptic Orbit

椭圆轨道真近点角的级数计算方法

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The analytic formulations are presented of the epicyclic motion of a spacecraft about the true anomaly and the eccentric anomaly.

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。

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The transcendental equation of a true anomaly was written in a power series instead of a differential form. When the sufficient condition of the iterative convergence is satisfied, the relationship between the true anomaly and the time was gotten by the iterative method.

用级数展开方法得到真近点角超越方程，由迭代法求真近点角与时间的关系，讨论迭代收敛的充分条件。

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The relationship between the true anomaly and the time is gotten by the numerical integral method.

用数值积分方法求出真近点角与时间的关系曲线。

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