由于这类运动是确定性的，可以事先唯一地求出，由此设计出一种最优控制器，按照二次型最优消摆规律消除载荷摆振。
For this kind of motion is determinated, it is feasible to be worked out uniquely in advance and design an optimal controller to suppress the load sway according to the quadratic optimal law.
对水下航行器热动力推进系统的非线性模型进行了线性化处理，应用线性二次型控制方法设计了系统的最优控制器，采用极点配置的方法设计了系统的状态估值器。
Forward the foundation and linear of the system model, the optimal controller and the state observer were designed by using the optimal control theory and the manner of pole configuration.
针对二级倒立摆系统的平衡控制问题，对其进行数学建模，应用二次型最优控制理论设计了控制器。
The double inverted pendulum is modeled and the controller is designed by using quadratic optimal control theory to its equilibrium control question.
本文在MATLAB环境下建立了二级倒立摆的半物理实时仿真模型，并应用线性二次型最优控制策略，设计了一个二级倒立摆lQR控制器。
This paper build a model of hardware in the loop using MATLAB. The linear quadratic optimal control strategy is adopted to design a LQR controller of double inverted pendulum.
针对这种不足，选择现代控制理论中的线性状态反馈控制方法，采用了线性二次型最优控制器设计方案。
In order to resolve the shortage, the thesis chooses the linear quadratic form optimal controller design scheme by applying linear state feedback control of the modern optimal control theory.
首先进行线性二次型最优控制器设计。
线性部分采用改进的线性二次型最优控制器法进行计算，而非线性部分采用自适应增益来更好地适应故障情况。
A modified linear quadratic optimal controller is designed for the linear part, while adaptive gain is used in the nonlinear part for adapting to different control surface damages.
根据最优化原理，按线性定常二次型最优跟踪器设计了针对任意载荷谱的最优控制器。
The optimal_Controller is designed for random load on the optimal theory and linear optimal tracker.
混合优化控制算法，给出了求解最优控制器的上逼近算法及其凸二次规划求解方法。
Lower approximation algorithm and its solve of convex quadratic programming are also given in this article.
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.
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.
应用推荐