日本宇宙开发机构的津田雄一说：“借助智能玻璃，我们只要利用太阳光就可既控制飞行轨道又控制飞行姿态。”
"With this we can control both the orbit and the attitude using only sunlight," says Yuichi Tsuda of the Japan Aerospace Exploration Agency.
空间交会对接涉及到两个航天器同时要进行多达12个自由度的轨道和姿态控制问题。
The rendezvous and docking (RVD) between two spacecrafts in space involves both orbit control and attitude control with up to 12 degrees of freedom.
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.
本文利用整体微分几何的方法研究了人造卫星的轨道控制和姿态控制问题。
The orbit control and attitude control problems of satellite have been studied in this thesis by use of global differential geometry method.
本文研究如何用磁力矩器控制极地轨道上对地指向卫星的姿态。
This paper studies magnetic control of polar orbiting, nadir pointing satellite.
根据极地轨道地磁场变化的特性，利用卫星的姿态角和姿态角速率作为反馈信号，提出了一种采用磁力矩器的比例微分(PD)控制规律设计方法。
Taking into account properties of the geomagnetic field, a new PD magnetic control law using the feedback information of attitude Angle and attitude rate is developed.
本文对可重复使用运载器的自适应逆姿态控制进行了研究，以航天飞机轨道器为模型，建立了自适应逆姿态控制的数学模型，设计了自适应逆姿态控制方案。
In this paper, adaptive inverse attitude control of RLV (reusable launch vehicle) is studied. The mathematical model of the orbiter is built and adaptive inverse attitude controller is designed.
卫星轨道控制期间，轨道控制推力会激振挠性太阳帆板，从而也影响卫星的姿态。
When the satellite takes orbital maneuver, the control force may stimulate the vibration of the flexible appendages and, therefore, affects the attitude of the satellite.
运用卫星低轨道两个主要环境力矩(重力梯度矩和地磁力矩)对圆轨道卫星三轴姿态进行被动控制。
In this paper, three-axis passive stabilization is realized by using two main environment torques (gravity gradient and geomagnetic torque) in low orbit.
根据姿态控制推力器的输出特性，设计了轨道控制期间卫星姿态控制方案。
The attitude control law is designed for the orbital maneuver with considering the output character of the attitude control thrusters.
根据卫星在轨运行数据，给出了卫星在轨运行的部分曲线和姿态控制、轨道控制的指标实现情况，对姿态控制分系统方案进行了在轨验证。
According to operation data of the satellite on orbit, some operation results and the specification conformity are presented. Furthermore, the control system scheme is demonstrated on orbit.
根据卫星在轨运行数据，给出了卫星在轨运行的部分曲线和姿态控制、轨道控制的指标实现情况，对姿态控制分系统方案进行了在轨验证。
According to operation data of the satellite on orbit, some operation results and the specification conformity are presented. Furthermore, the control system scheme is demonstrated on orbit.
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