在卫星姿控任务中，经常需要估计卫星姿态角速度。
Accurate estimates of the angular velocity are often required for satellite attitude control.
但一般情况下惯导平台无法输出运动载体的姿态角速度。
The problem is that it is commonly unable for inertia platform to output attitude angular velocity of moving carrier.
研究了存在安装误差时基于加速度计比力信号解算高自旋弹丸角速度和姿态角的方法。
A method of solving the angular speed and attitude angular of high spinning projectile was proposed by accelerometers' specific force signal in existence of installation errors.
另一类可称为测量参数匹配法，它包括加速度匹配、姿态匹配和角速度匹配。
Another can be called measuring parameter matching, such as acceleration matching, attitude matching and angular rate matching.
陀螺安装的方式不同，则载体姿态的角速度补偿量也不同。
The angular velocity compensations of carrier attitude measurement are different if the installation modes of gyros are different.
分别推导了速度匹配、姿态匹配、角速度匹配和比力匹配传递对准的状态空间模型；
The state space models of the velocity matching, the attitude matching, the angular rate matching and the specific force matching transfer alignment are made.
然后，考虑无角速度信息下的姿态同步问题。
Then, the attitude synchronization without angular velocity is considered.
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。
A method for designing attitude stabilization controllers is proposed in this paper for flexible spacecraft without angular velocity measurements.
另一类可称为测量参数匹配法，它包括加速度匹配、姿态匹配和角速度匹配。
One can be called calculating parameter matching, such as velocity matching and position matching.
捷联惯导系统利用相对导航坐标系角速度计算姿态矩阵，把雷体坐标系轴向加速度信息转换到导航坐标系轴向并进行导航计算。
The platform inertial navigation system used peg-top to stabilize the loop through platform and control the angular speed of the platform track navigation coordinate system.
利用一种新的姿态描述形式推导出了角速度为零时航天器的目标姿态，然后基于线性化后的系统设计了线性二次型最优控制器。
Then, the expected orientation of spacecraft with zero angular velocity was derived with a new attitude parameterization and LQR controller was designed based on the linearized system.
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.
基于奇异摄动思想，将飞行器姿态控制系统分为慢变化的姿态角回路和快变化的角速度回路分别设计。
The spacecraft's attitude control system was divided into the outer loop that was Angle loop and the inner loop that was Angle velocity loop based on their time scales.
基于时标分离思想，将飞行器姿态控制系统分为慢变化的姿态角回路和快变化的角速度回路分别设计。
The aerocraft's attitude control system is divided into the outer loop that is an Angle loop and the inner loop that is an Angle velocity loop based on their timescale separation principle.
基于时标分离思想，将飞行器姿态控制系统分为慢变化的姿态角回路和快变化的角速度回路分别设计。
The aerocraft's attitude control system is divided into the outer loop that is an Angle loop and the inner loop that is an Angle velocity loop based on their timescale separation principle.
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