然后，基于某型小卫星的姿态控制问题，设计了高精度定向阶段的神经网络补偿控制器。
Then, base on the problem of attitude control of a satellite under development, we design a NN compensation controller for high accuracy orientation phase.
所得结果不仅适用于具有大型运动部件的航天器的姿态动力学分析及控制系统设计，也适用于灵敏小卫星的相应研究。
The proposed results are useful to the attitude dynamic analysis and control system design for not only the spacecraft with large rotation parts, but also the agile small 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。
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.
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