本文首先介绍了逆系统方法的基本思想，然后将其用于航天器非线性姿态控制系统的设计中。
In this paper, the basic theory of the inverse system method is introduced, and is used in the design of a spacecraft attitude control system.
这样通过非线性状态变换和非线性状态反馈，将飞行器原来的6阶非线性姿态模型部分精确线性化为二阶线性系统。
Thus by nonlinear state transformation and nonlinear state feedback, the original 6 order nonlinear attitude model of a spacecraft is partially precisely linearized into a 2 order linear system.
利用多重时间尺度奇异摄动理论，结合非线性动态逆方法设计了基本姿态控制器，包括快逆回路和慢逆回路两部分。
According to the singularity perturbation theory, dynamic inversion is adopted to design the basic attitude controller including fast inverse loop and slow inverse loop.
把姿态信息载入非线性方程组中，从而求得飞艇的位置信息。
Substituting the information of attitude into the nonlinear equations the position of airship was obtained.
根据坐标转换关系，可以获得飞艇在地面坐标系下的位置和姿态非线性方程组。
According to coordinate transforming relations the nonlinear equations containing the attitude and position of the airship in geographic coordinate system can be acquired.
提出了一种由仿射变换关系到线性回归的3d人脸空间姿态估计方法。
A method for estimating 3d space face pose was proposed based on affine transformation and linear regression.
其次，利用线性卡尔曼滤波器对其纵向运动姿态进行估计，依据LQG性能指标构造了最优控制规律。
Then the pose of longitudinal motion is estimated by linear Kalman filter. Finally, an optimal control rule is constructed by LQG performance index.
CMAC估计器先用线性模型进行训练，然后预测目标的质心和姿态。
CMAC estimator is trained with a linear model, then the centroid and attitude are predicted.
提出了一种基于最小二乘支持向量机(LSSVM)非线性观测器的卫星姿态控制系统故障诊断方法。
A fault diagnosis method for satellite attitude control systems is presented based on least squares support vector machine (LSSVM).
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 error between satellite attitude dynamics and its linearized model can affect the attitude control precision.
以非线性瞬态动力学理论为基础，计算和分析了某型火箭发射过程中管内姿态情况。
The posture of a rocket in launch tube was calculated and analyzed Basel on the theory of non-linear transient dynamics.
对于具有纯延迟、惯性和由开关控制的非线性飞行器姿态系统，本文提出了采用解耦变结构控制的方法。
For nonlinear attitude system of flying vehicle with pure time-delay, inertia and bang-bang control a control method using decoupling variable structure is given.
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。
Maneuverable warhead are the complex nonlinear system, which take a great challenge to the attitude control system designers.
采用输出变量反馈线性化控制律及其局部线性化将混沌姿态运动控制为给定的静止状态和周期运动。
The input_output feedback linearization method and its modified version are respectively applied to control chaotic attitude motions to the given attitude rest and the periodic motion.
为了实现对于独轮车机器人非线性系统的姿态控制。
The nonlinear characteristics in the unicycle robot dynamic system make the robot control much more difficult.
将所得结果应用于卫星姿态控制系统的设计，以解决对模型进行线性化处理时产生的误差。
The proposed method is applied to satellite attitude controller design to cope with the errors arising while linearization procedure.
基本姿态控制器采用基于在线神经网络的非线性动态逆控制器。
The nonlinear dynamic inversion controller based on online neural net is adopted for the attitude control loop.
研究了最近提出的非线性自抗扰控制器(adrc)在大挠性多体卫星姿态控制中的应用问题。
The recently developed nonlinear active disturbance rejection controller (ADRC) is applied to attitude control of large flexible multi-body satellite with reaction wheels.
研究了最近提出的非线性自抗扰控制器在大挠性多体卫星姿态控制中的应用问题。
The recently developed nonlinear Active Disturbance Rejection Controller (ADRC) was applied to the attitude control of large flexible multi-body satellite with reaction wheels.
在确定卫星姿态确定的状态估计法中，经典的扩展卡尔曼滤波(ekf)和新提出的非线性预测滤波(NPF)这两种实时滤波算法各有优缺点。
In state estimation of satellite attitude determination, both traditional extended Kalman filter (EKF) and the proposed nonlinear predictive filter (NPF) have their own merits and defects.
燃油量是液位的非线性函数，并与飞行姿态有关。
The fuel quantity is a nonlinear function of the liquid level which is affected by the flight posture.
采用输出变量反馈线性化控制律及其局部线性化将混沌姿态运动控制为给定的静止状态和周期运动。
The input_output feedback linearization method and its modified version are respectively applied to control chaotic attitude motions t.
针对清刷机器人水下作业的非线性特点，采用参数自调整模糊控制策略设计了位置模糊控制器，保证了机器人具有良好的姿态调节能力。
Due to the nonlinearity of the robot system, position controller USES the parameter self-adjusting fuzzy control strategy, which assures good pose regulating power.
拦截器姿态控制系统是一个非线性控制系统。
Interceptor attitude control system is a nonlinear control 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.
由于地磁场的方向在轨道上周期变化，卫星的姿态动力学方程是一个线性周期系统。
Since the geomagnetic field varies periodically on orbit, the dynamics of satellite is a linear periodic system.
由于地磁场的方向在轨道上周期变化，卫星的姿态动力学方程是一个线性周期系统。
Since the geomagnetic field varies periodically on orbit, the dynamics of satellite is a linear periodic system.
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