relative orbit

The method solves an algebraic equation instead of a set of nonlinear differential equations to find the two initial conditions for the periodic relative rotating orbits for any eccentric orbit with nonlinear relative motion.

该方法不用求解非线性相对运动微分方程，只需解一个一元二次代数方程，就可给出任意偏心率和非线性条件下，两个具有明显物理意义的周期性相对运动初始条件。

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J 2 perturbation makes the relative orbit drift in the in track direction , nutation or procession.

J2摄动对相对轨道的影响分为相对轨道构形的漂移 、 相对轨道平面的章动和进动.

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Based on relative motion equation of satellite state transferring, analytic solution of two impulse orbit transfer of constellation is derived, which is analytic equation of impulse control variable.

基于卫星相对运动状态转移方程，推导出了星座双脉冲式变轨的理论解，即所要施加的脉冲控制量的解析式；

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An optimal orbit maneuver method based on continuous low thrust was presented to solve relative motion control.

针对近距离相对运动的轨道控制问题，提出用常值小推力完成最优转移的方法。

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Relative Orbit Design of a Chaser Tracking a Non-cooperative Target in Space

追踪星跟踪空间非合作目标的相对轨道设计

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It is well known that the spin-orbit coupling and hyperfine interaction in organic materials are very weak. So the spin relaxation time in organic materials is relative long.

有机材料由于具有较弱的自旋轨道耦合以及超精细相互作用，因此相对于普通无机半导体具有较长的自旋弛豫时间。

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The configuration initialization of satellite formations is carried out based on orbit maneuver control of relative elements.

根据相对轨道要素的变轨机动控制，进行编队飞行卫星群构型的初始化。

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High precise real-time autonomous relative orbit determination between distributed spacecraft is a key technology in the task of spacecraft formation maintenance.

分布式航天器间相对位置的实时高精度测量是分布式航天器实现空间队形保持的关键技术之一。

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Relative orbit determination for satellite formation flight is of great importance.

编队飞行卫星相对轨道的确定具有重要意义.

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Doublet fine structure results from-orbit coupling and the two possible relative orientations of S and L.

双重精细结构起源于自旋一轨道耦合以及S和L的两个可能相对取向.

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This paper deduces the orbit maneuver equations for relative motion control of satellite formations based on the relative orbit elements.

导出了基于相对轨道要素的编队飞行卫星群轨道相对运动控制的轨道机动方程；

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