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.
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.
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.
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.
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.
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。
As inertial actuators mounted on the spacecraft, Single Gimbal control Moment Gyroscopes (SGCMGs) can affect the attitude control accuracy to a great extent.
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