In the paper, the application of feedback linearization in the flight control is described firstly, then the simulation demo system of nonlinear flight control system is designed.
文中首先采用反馈线性化理论设计了非线性飞控系统，进一步设计了非线性飞控系统仿真视景演示平台。
Flight control system designed by this nonlinear control method can achieve decoupling control, and has better adaptability to inaccurateness of model and the change of system parameters.
用该非线性控制方法设计的飞行控制系统不仅能够实现动态解耦控制，获得良好的动态性能，而且对模型不够准确或系统内部参数发生变化具有较强的适应性。
A very severe nonlinear is presented because flight parameters vary along with the flight condition in the flight of missile which brings much difficulty to the design of control system.
导弹在飞行过程中，其飞行参数随着飞行条件的变化而发生较大变化，呈现严重的非线性，给控制系统的设计带来较大困难。
The design of the flight controller that exploits the advantages of the nonlinear dynamic inversion, adaptive fuzzy system and slide model control is discussed.
论述了综合运用非线性动态逆、自适应模糊系统和滑模控制的优点进行飞行控制律设计的方法。
A nonlinear PD controller is presented in this paper and is used in the design of the control laws for an automatic terrain following flight control system.
提出了一种非线性PD控制方法，并将其应用在自动地形跟随系统飞行控制律的设计中。
Conventional linear flight control systems do not satisfy nonlinear control requirement of aircraft with thrust vector, which is a multiple control redundances and nonlinear MIMO system.
常规线性飞控系统针对推力矢量飞机这样的多控制冗余、非线性MIMO系统，无法实现非线性控制。
According to the demand of flight control system, a nonlinear dynamics model with considerable aerodynamic forces and moments for a large maneuver re entry missile head is built.
根据飞行控制要求，考虑了影响较大的气动力和气动力矩因素，建立了一个完全表征大机动情况下弹头运动的非线性动力学模型。
According to the demand of flight control system, a nonlinear dynamics model with considerable aerodynamic forces and moments for a large maneuver re entry missile head is built.
根据飞行控制要求，考虑了影响较大的气动力和气动力矩因素，建立了一个完全表征大机动情况下弹头运动的非线性动力学模型。
应用推荐