The dynamic equations of flexible spacecraft are derived by introducing a moving coordinate frame.
首先建立了采用任意浮动参考系时的柔性航天器动力学方程；
Sliding mode with reference input-shaping control design for flexible spacecraft slewing maneuvers;
研究了具有模型不确定性的多体航天器大角度机动控制问题。
The problem of robust attitude control for three-axial-stabilized flexible spacecraft is considered.
研究三轴稳定的挠性航天器姿态的鲁棒控制问题。
Finally, it is considered that the stability of flexible spacecraft with liquid-filled multi-body system.
最后，讨论了多体系统充液挠性空间飞行器的稳定性问题。
Researches on the dynamic and control for the flexible spacecraft usually use the modal of the flexible appendages.
研究柔性航天器的动力学与控制问题时，通常需要利用柔性附件的模态信息。
The relation among parameters is derived and the stability of single axis flexible spacecraft attitude control system is studied.
推导系统参数间的关系式，分析挠性空间飞行器主轴姿态控制系统稳定性问题。
This article presents a dynamic model for a large flexible spacecraft with its end mass undergoing a large Angle, high speed maneuvering.
建立带附加质量大型挠性航天器大角度快速机动时的动力学模型。
The control problem of a flexible spacecraft during a large-angle maneuver is studied and a direct output feedback control method is proposed.
本文研究了柔性航天器大角度操纵的控制问题，提出了直接输出反馈控制方法。
In this paper, the robustness stability analysis of the attitude control system of a three-axis stabilized flexible spacecraft is investigated.
本文应用区间矩阵的理论，研究三轴稳定的挠性空间飞行器姿态控制系统的鲁棒稳定性分析问题。
A method for designing attitude stabilization controllers is proposed in this paper for flexible spacecraft without angular velocity measurements.
研究了一种无角速度信息挠性航天器的姿态稳定控制方法。
Moreover, this method is used for the research on the problems of attitude stability of dual-spinning satellite, the large flexible spacecraft and the satellite with cavity containing fluid.
并应用该方法研究了自旋卫星(包括陀螺体卫星)，挠性卫星以及空腔充液卫星的姿态稳定性问题。
A modified sliding mode fault tolerant controller is developed for flexible spacecraft attitude stabilization control in the presence of loss of actuator effectiveness fault and actuator stuck fault.
针对挠性航天器执行器卡死与失效故障的姿态稳定控制问题，提出了一种结构简单、计算量小的改进型滑模容错控制策略。
The several important problems such as deployment procedure of flexible appendages on complex spacecraft are analyzed, and corresponding programme and application software are introduced.
分析了复杂航天器在柔性附件展开过程中的几个关键问题，并提出了相应的解决方案，编制了应用软件。
The dynamic equation of the spacecraft with extensional flexible appendages system is time variable and nonlinear, so it is very difficult to solve this kind of equation with traditional methods.
带伸展柔性附件航天器的动力学方程是刚-柔耦合的时变非线性动力学方程，用传统方法求解其动力学响应时会遇到很大的困难。
The characteristic model is derived based on the dynamics model of the spacecraft with flexible appendix.
根据带柔性附件的航天器的动力学模型推导并建立其特征模型。
The attitude dynamic equations of a spacecraft with flexible appendages are obtained by using the momentum theorem.
利用动量矩定理推导出带挠性伸展附件航天器的动力学方程。
In this paper, the issue on fast attitude maneuver control of a spacecraft with flexible appendix is studied.
研究带柔性附件航天器的姿态快速机动控制问题。
The coupled dynamic equations of a spacecraft with tip mass attached flexible appendage which is deployable are obtained by using the momentum theorem.
结构复杂的航天器带有几十米、上百米大型挠性附件，附件末端还带有大质量刚体。
Output tracking problems for non minimum phase system existed in many practical problem, such as aircraft flight controlling, spacecraft launching and flexible manipulation, are considered.
讨论了一类非最小相位系统的输出跟踪问题。非最小相位系统广泛存在于机器人柔性结构控制、飞机的飞行控制和航天器发射等实际问题中。
This paper is concerned with the dynamics and control for planar, large Angle rapid slew maneuvering of a flexible multi body spacecraft, consisting of a rigid central body and a flexible beam.
研究一类构形为中心刚性带挠性梁的航天器平面快速大角度机动的动力学与控制问题。
This paper is concerned with the dynamics and control for planar, large Angle rapid slew maneuvering of a flexible multi body spacecraft, consisting of a rigid central body and a flexible beam.
研究一类构形为中心刚性带挠性梁的航天器平面快速大角度机动的动力学与控制问题。
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