satellite orbit control

Analysis and Control Method for Constellation Rotation in Navigation Satellite Autonomous Orbit Determination

导航卫星自主定轨星座旋转误差分析与控制方法

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The attitude control system of the earth observation satellite is a complicate, high accurate, long-life and earth-oriented three axis stable system with the solar panels orienting the sun in the sun synchronous orbit.

地球观测卫星姿态控制系统是个复杂的，高精度，长寿命对地三轴稳定，在太阳同步轨道上帆板对太阳定向的系统。

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In the paper, considering three satellite constellation, optimal time control of orbit transfer with constant value, continue working and Newton grade thrust is studied, by means of Minimum Principle in optimal control theory.

本文针对形成三星星座，利用最优控制中的极小值原理，解算了用恒值、连续工作、牛顿级小推力变轨的时间最短控制问题。

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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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It was showed that PPT was a kind of advanced propeller with small thrust, which was suitable to orbit transfer, attitude control, station keeping and formation flying for small and micro satellite.

分析认为PPT是一种先进的小推力动力装置，特别适合于微小卫星的轨道转移、姿态控制、位置保持以及星座编队飞行。

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