刚体的姿态可以用不同的参数来描述，由此可以产生不同的控制方法。
The attitude of a rigid body can be described by different parameters , hence it yields different control methods.
给出了用四元数表示的刚体姿态调节问题的两种控制规律。
Two control laws are presented for attitude regulation of a rigid body expressed by unit quaternion.
研究了刚体飞行器大角度机动的姿态控制问题。
In this paper, attitude control problem of a rigid spacecraft with large Angle maneuvers is investigated.
针对存在不确定惯量矩阵和外干扰的刚体航天器姿态跟踪系统，提出了一种自适应滑模控制方法。
For rigid spacecraft attitude tracking system with uncertain inertia matrix and external disturbances, an adaptive sliding mode approach is presented.
研究了刚体卫星在控制输入饱和、外干扰和参数不确定性存在时的姿态调节控制问题。
This paper deals with the problem of attitude regulation control of rigid satellite subject to control input saturation, external disturbance and parametric uncertainty.
利用最优控制方法研究了带有两个动量飞轮的刚体航天器姿态优化控制问题。
Based on the optimal control theory, an optimal attitude control strategy was proposed for the rigid spacecraft with two momentum wheel actuators.
检验了大部分提出的单个刚体姿态跟踪和多个刚体姿态同步的控制算法。
Most of the proposed control laws, from single rigid body attitude tracking to multiple rigid bodies attitude synchronization, are verified.
退步控制是一种有效设计级联系统控制律的方法，而基于单位四元数的刚体姿态方程就是一种典型的级联系统。
Backstepping control scheme was an effective way to design control laws of a cascade system. Quaternion-based attitude equations of a rigid body was a typical cascade system.
基于分析结果，先后研究了刚体航天器姿态稳定、柔性航天器姿态稳定、以及航天器姿态机动的正规矩阵控制问题。
The researches are based on the spacecraft that can be regarded as a central rigid-body with stored angular momentum and some ?exible appendages attached.
基于分析结果，先后研究了刚体航天器姿态稳定、柔性航天器姿态稳定、以及航天器姿态机动的正规矩阵控制问题。
The researches are based on the spacecraft that can be regarded as a central rigid-body with stored angular momentum and some ?exible appendages attached.
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