采用边条控制技术，可获得所需要的控制力与控制力矩。
The required control forces and moments can be obtained using strake control techniques.
装有电子自动控制力矩限制器、防过卷装置、液压伺服操纵。
Equipped with electronic control torque limiter, vol - off devices, hydraulic servo control.
研究了月球探测器转速与控制力矩受限的姿态大角度机动问题。
This paper studies the attitude large Angle slew problem that rate and control moment of the lunar probe are limited.
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。
Inside the Z1 are four control Moment Gyroscopes that provide the International Space Station's attitude control.
本文提出了一种在时域上设计柔性机械臂开环控制力矩的逆动力学方法。
In this paper, the new inverse dynamics method, which designs the open-loop control torque for one-link flexible manipulator, is proposed.
后者采用控制力矩饱和约束和滑动模态设计，提高了控制系统的鲁棒性。
The latter is designed by sliding mode control under constraints of control torque saturation and improves robustness of the control system.
目前使用的绝大多数减摇鳍都是角度反馈系统，它通过鳍的转角来计算控制力矩。
Most of the fin stabilizers we use now are angle-feedback system, whose control torque is gotten by the calculation of fin Angle.
目前使用的绝大多数减摇鳍都是鳍角控制系统，它通过鳍的转角来计算控制力矩。
Most of the fin stabilizers we use now are angle-control system, whose control torque is gotten by the calculation of fin Angle.
根据实际情况限定了大型航天器单框架控制力矩陀螺（SGCMG）构型分析研究的对象；
The single gimbal control moment gyro (SGCMG) configuration of a large spacecraft is studied. First, the research object of analyzing configuration is restricted.
并研究了姿控发动机的配置特点和点火逻辑，给出了由期望力矩计算实际控制力矩的方法。
The formula of anticipant control moment is deduced by adopting the method of exponent reaching law and twitter reducing of boundary layer.
研究了以变速控制力矩陀螺（VSCMG）作为执行机构的卫星多目标快速机动的控制问题。
The multi-target rapid maneuver control problem is studied for agile satellites with Variable Speed Control Moment Gyro(VSCMG) as actuator.
以放卷辊为研究对象，对其运动状态作了详细的分析，进而给出了计算控制力矩的程序框图。
Take puts the winding up roller as the research object, has made the detailed analysis to its state of motion and a program scheme for calculating the tension control torque was provided.
提出了一种用于双框架控制力矩陀螺的梯度型伪逆控制律，介绍了控制律的原理与计算方法。
The design of a gradient singularity avoidance pseudo-inverse control law used for double gimbal control moment gyro (DGCMG), its principle and calculation were introduced.
将控制律给出的控制力矩合理分配给气动面的反作用控制系统，并考虑了实际的硬件特性要求。
The control moment from control law is allocated to aero-surface and reaction control system, in this phase the limits from hardware are taken into consideration.
在介绍集成轴角变换器的工作原理后，详细介绍了用于控制力矩陀螺速率控制系统中的测角系统。
In this paper, the Angle measuring system using in Single Gimbal Control Moment Gyroscope (SGCMG) is discussed after introducing the basic theory of resolver-to-angle converter.
综述了单框架控制力矩陀螺(SGCMG)系统操纵律研究概况，并对现存操纵律的性能进行了评价。
A survey of steering laws for Single Gimbal Control Moment Gyroscope (SGCMG) systems is made. Meanwhile, steering performance of the art is appreciated.
本文以控制力矩陀螺为研究背景，依据有限元方法对控制力矩陀螺进行动态特性分析和可靠性分析。
Based on the background of the CMG, the dissertation is about CMG's dynamic characteristics and reliability analysis using the theory of finite element method.
给出了在奇异点处输出控制力矩误差的表达式，并证明了框架角速度和输出力矩误差之间的不可调和性。
The expression of output-torque error is given at the point of singularity, proving the incompatible relationship between the gimbal rate and the output-torque error.
实验证明，该系统能够有效地抑制高速转子的陀螺效应，达到控制力矩陀螺电磁轴承高速稳定运行的要求。
Experiment result shows that the method can effectively compensate gyroscopic effects, and meet the requirements of high-speed magnetic bearing.
在单框架控制力矩陀螺(SGCMG)系统操纵律的设计中，通常假定框架伺服系统具有理想的伺服跟踪性能。
Gimbal servo systems of single gimbal control moment gyroscopes (SGCMGs) are often assumed to have ideal tracking performance during the steering law design.
首先建立了以变速控制力矩陀螺为执行机构的航天器姿态动力学模型，并给出了全局稳定的姿态反馈控制律。
The attitude dynamic equation of a spacecraft with VSCMG attached and a global asymptotical attitude feedback control law are presented firstly.
本文正是针对控制力矩陀螺在大型卫星应用的几个关键问题而开展研究，为控制力矩陀螺工程应用提供依据。
This paper, aimed at several crucial problems in the application of CMG to large satellites, is studied to afford basis for the application of moment gyroscope in aerospace engineering.
磁悬浮控制力矩陀螺(CMG)中转子一阶弹性模态自激振动是影响磁悬浮高速转子系统稳定性的关键因素之一。
In magnetically suspended control moment gyroscope (CMG), self-excited vibration of high-speed rotor is one of principal factor which effects stability of active magnetic bearing (AMB) system.
使用几何方法对单框架控制力矩陀螺群（包括转子恒速的CSCMG和转子变速的VSCMG）的奇异性进行了分析。
This research is focused on the singularity analysis for single-gimbal control moment gyros systems (SCMGs) which include two types, with constant speed (CSCMG) or variable speed (VSCMG) rotors.
另外，本文第2章和第4章还对相关的控制算法进行了饱和控制的处理，使得控制力矩的最大值限制在容许的范围内。
In addition, some control laws in Chapter 2 and 4 are further modified on the basis of saturated control, then the maximum of the control torques will be constrained within the admissible range.
给出了该零运动微分动力学下具有冗余度的单框架控制力矩陀螺系统奇异状态的性质，并改进了奇异可脱离性的判别方法。
The character of SGCMG system in the form of zero motion differential dynamic equation is given. The criterion of singularity escapable from reference 4 is improved.
在单框架控制力矩陀螺（SGCMG）系统操纵律的设计中，如果考虑框架伺服特性，往往假设系统的物理参数是确切已知的。
Physical parameters of single gimbal control moment gyroscopes(SGCMGs) are often assumed to be known exactly when steering law is designed by taking gimbal servo characteristics into account.
在单框架控制力矩陀螺(SGCMG)系统操纵律的设计中，如果考虑框架伺服特性，往往假设系统的物理参数是确切已知的。
Physical parameters of Single gimbal Control Moment Gyroscopes (SGCMGs) are often assumed to be known exactly when steering law is designed taking gimbal servo characteristics into account.
在单框架控制力矩陀螺(SGCMG)系统操纵律的设计中，如果考虑框架伺服特性，往往假设系统的物理参数是确切已知的。
Physical parameters of Single gimbal Control Moment Gyroscopes (SGCMGs) are often assumed to be known exactly when steering law is designed taking gimbal servo characteristics into account.
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