对一种利用高空风的风速差控制飞行轨迹的新型低能耗临近空间飞行器，进行了力学分析与配平计算。
The mechanical analysis and the trimming were performed for a novel near space aircraft which uses the variation in wind speed at high altitude to control its flight path.
提出了非线性空间飞行器系统采用滑动模态控制方法，它对强非线性的空间飞行器系统通道间交叉影响进行解耦。
A control method with sliding mode of nonlinear spacecraft system is provided in this paper, in which the interactive influences among channels of strong nonlinear spacecraft system are decoupled.
提出了一种基于自适应观测器的故障诊断与容错控制策略，应用到近空间高超声速飞行器(NSHV)上处理执行器故障。
A fault diagnosis and fault-tolerant control scheme using adaptive observer is generalized to near space hypersonic vehicle (NSHV) to deal with actuator fault.
本文研究空间飞行器大角度姿态机动的控制问题。
This paper deals with the large Angle attitude maneuver control of spacecrafts.
星敏感器是为空间飞行器姿态控制系统提供姿态信息的测量系统。
The star sensor is a measuring unit used for providing information to the attitude control system on spacecraft .
目前空间飞行器的高精度姿态控制系统大多采用飞轮系统。
Now, flywheels systems are elected as the actuators of attitude control system with high precision for most spacecrafts.
VTOL空间飞行器是具有三个自由度，两个控制输入的欠驱动系统。
VTOL aircraft is an under-actuated system with three degrees of freedom and two control inputs.
研究空间飞行器大角度姿态机动反馈开关控制的消振参数优化设计问题。
The optimization design problem of controller parameters of optimal on-off times attitude maneuvers with switch moment is investigated.
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。
The relation among parameters is derived and the stability of single axis flexible spacecraft attitude control system is studied.
本模型可以描述航天员控制载人航天飞行器(如飞船、航天飞机和空间站等)的控制行为。
This model can be used to describe the control behavior of astronaut's controlling manned vehicle (such as spacecraft, shuttle and space station).
针对存在强烈不确定和干扰的近空间高超声速飞行器(NHV)，提出了一种新的非线性自适应控制方法。
A novel nonlinear adaptive control method is presented for a near-space hypersonic vehicle (NHV) in the presence of strong uncertainties and disturbances.
本文针对空间飞行器姿态控制问题，给出了一种基于优化控制与有限时间控制技术的控制方法。
In this paper, a control approach based on optimal control and finite-time control technology is derived for spacecraft.
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。
In this paper, the robustness stability analysis of the attitude control system of a three-axis stabilized flexible spacecraft is investigated.
首次推导了基于质量控制和推力矢量控制的一类无尾无舵翼碟形飞行器的空间六自由度运动动力学方程。
The six degrees of freedom dynamic equation of a kind of mass-controlled and thrust vectoring-controlled saucer-like air vehicles without tailes, wings and rudders was derived for the first time.
理论分析及仿真结果表明，本文所求控制律对空间飞行器跟踪系统具有全局稳定性和鲁棒性。
Theoretical analysis and simulation results show that the proposed SMC law is globally stabilizing and insensitive to both parameter variations and external disturbances.
基于充液飞行器的简化模型，在状态空间中设计控制规律以约束状态至滑模。滑模通过在一个约化空间中求解最优控制问题获得，其解是角速度作为姿态变量的函数。
A control law, that constrains the state to follow the sliding mode in the state space, is designed on the basis of a nonlinear, simplified model of the completely liquid-filled spacecraft dynamics.
基于充液飞行器的简化模型，在状态空间中设计控制规律以约束状态至滑模。滑模通过在一个约化空间中求解最优控制问题获得，其解是角速度作为姿态变量的函数。
A control law, that constrains the state to follow the sliding mode in the state space, is designed on the basis of a nonlinear, simplified model of the completely liquid-filled spacecraft dynamics.
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