An example of an attitude control system of a bending vehicle is given.
文中给出了一个弹性飞行器的姿态控制系统作为设计举例。
The design procedure is demonstrated by a satellite attitude control example.
通过卫星姿态控制的算例具体说明了这种优化设计过程。
The attitude control system designed with this concept has better flexibility.
用这种方案设计的姿态控制系统有非常好的灵活性。
Reaction wheels are widely used in the modern spacecraft attitude control systems.
在现代卫星的姿态控制系统中，反作用轮得到了广泛应用。
The attitude control thruster (ACT) is the control component of the flight vehicle.
姿态控制推力器(act)是飞行器控制系统的执行部件。
A momentum wheel control system is widely used for the attitude control of satellite.
在人造卫星的姿态控制中，广泛地采用偏置动量轮控制系统。
The flywheels are used as attitude control actuators as well as energy storage device.
系统中飞轮是姿态控制的执行机构，同时也是储能装置。
As an application example, its application to flight attitude control system is analysed.
作为应用实例，分析了在飞行姿态控制系统中的应用。
Accurate estimates of the angular velocity are often required for satellite attitude control.
在卫星姿控任务中，经常需要估计卫星姿态角速度。
The algorithm has been embedded in the attitude control system of a small unmanned helicopter.
该算法已应用于小型无人直升机的姿态控制中。
The model of spacecraft attitude dynamics and the attitude control technology are generalized.
对航天器姿态动力学模型和姿态控制技术进行了概括和总结。
The integrated power and attitude control for a bias momentum attitude control system is investigated.
研究偏置动量姿态控制系统中的集成能量与姿态控制问题。
The attitude Control System (ACS) software is responsible for maintaining the attitude of the spacecraft.
姿态控制系统(acs)软体负责维护航空器的姿态。
In this paper, attitude control problem of a rigid spacecraft with large Angle maneuvers is investigated.
研究了刚体飞行器大角度机动的姿态控制问题。
This paper presents a control scheme based on NN disturbance compensation for attitude control of satellite.
提出了一种基于神经网络扰动补偿的姿态控制方法。
Reaction wheel is one of the main disturbance sources for the attitude control system accuracy of spacecraft.
反作用轮是影响航天器姿态控制系统精度的主要扰动源之一。
The primary node is responsible for running the communications subsystems and the attitude control system code.
主要节点负责执行通讯子系统与姿态控制系统。
The error between satellite attitude dynamics and its linearized model can affect the attitude control precision.
卫星姿态动力学系统与其线性化模型之间的误差会影响姿态控制的精度。
The star sensor is a measuring unit used for providing information to the attitude control system on spacecraft .
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。
Inside the Z1 are four control Moment Gyroscopes that provide the International Space Station's attitude control.
在Z 1内是提供国际太空站的态度控制的四个控制力矩陀螺仪。
Maneuverable warhead are the complex nonlinear system, which take a great challenge to the attitude control system designers.
机动弹头是复杂的非线性系统，它给姿态控制系统设计人员以极大的挑战。
The stratospheric nacelle attitude control system is the key technology in keeping position stabilization and posture adjustment.
气球吊篮姿态控制系统是吊篮在空中保持姿态稳定、进行姿态调整的关键部件。
The orbit control and attitude control problems of satellite have been studied in this thesis by use of global differential geometry method.
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 relation of shield tunnel and the designing tunnel is stated from the Angle of shield machine production and attitude control of the duct piece.
从盾构机制造及盾构施工隧道管片姿态控制的角度讲述了盾构隧道与设计线路隧道的关系。
The rendezvous and docking (RVD) between two spacecrafts in space involves both orbit control and attitude control with up to 12 degrees of freedom.
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。
Then, base on the problem of attitude control of a satellite under development, we design a NN compensation controller for high accuracy orientation phase.
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。
In view of the particularity for maneuver warhead reentry trajectory and the guidance method, key techniques in attitude control system design are analyzed.
针对机动弹头再入弹道和制导方式的特殊性，分析了激光末制导机动弹头姿控系统设计的关键技术。
As inertial actuators mounted on the spacecraft, Single Gimbal control Moment Gyroscopes (SGCMGs) can affect the attitude control accuracy to a great extent.
作为应用在航天器上的惯性执行机构，单框架控制力矩陀螺(SGCMG)的操纵性能对航天器姿态控制精度有着极大的影响。
As inertial actuators mounted on the spacecraft, Single Gimbal control Moment Gyroscopes (SGCMGs) can affect the attitude control accuracy to a great extent.
作为应用在航天器上的惯性执行机构，单框架控制力矩陀螺(SGCMG)的操纵性能对航天器姿态控制精度有着极大的影响。
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