This actuator is used in the longitudinal control system of fighter t improve longitudinal control and stability , and is a power actuating unit of autopilot 用于歼击机纵向操纵系统，改善纵向操稳性能，也是自动驾驶仪的输出执行部件。
The control scheme is successfully applied to the simulation of fighter control system . the simulation results demonstrate that the control scheme is effective 控制方案成功的应用于歼击机飞行控制系统中,仿真结果表明了方法的有效性。
This thesis takes a certain model of fighters as the plant . the purpose is to study the self - repairing flight control technology in terms of engineering 本文以某研究所提供的某型歼击机的飞机模型为对象,从工程实际的角度出发,重点研究歼击机自修复飞行控制技术。
Third , self - repairing control of some kind of fault states of fighter is studied by using the robust adaptive tracking control method based on the fuzzy t - s model 再次,应用基于t - s模糊模型和自适应神经网络的跟踪控制方案,对歼击机在各种故障条件下进行了自修复控制的仿真研究。
The new generation fighter and its integrated fire / flight / propulsion control system are rapidly developed by the western countries and russia for scrambling the mastery of the sky 为了争夺21世纪的制空权，西方发达国家和俄罗斯竞相发展最先进的新一代歼击机及其综合火力飞行推进系统。
At last , the proposed methods are successfully applied to the simulation of fighter flight control system , results of simulation test show the effectiveness of the proposed methods 最后将文中所提出的方法成功地应用于歼击机飞行控制系统的数字仿真实验，仿真结果表明了本文方法的有效性。
Second , the t - s fuzzy model is adopted for modeling of the known nonlinear system approximately , meanwhile fuzzy - model - based h tracking control law is designed to track the desired output signal 其次,利用t - s模糊模型对系统进行近似建模,应用基于模糊模型的模糊h _跟踪控制律对歼击机进行输出跟踪控制。
In this dissertation , the control methods of mimo uncertain nonlinear system are designed and used to solve the key control problems involving the integrated iire / flight / propulsion system 本文主要研究多输入多输出不确定非线性系统的鲁棒控制方法并应用于解决新一代歼击机的综合火力飞行推进系统的关键控制问题。
The main work of this thesis is fault diagnosis for flighter control surface . three diagnosis methods , rough neural networks , wavelet analysis and fractal geometry methods are emphasized , then these methods are validated by simulations 本文的主要工作是进行歼击机操纵面的故障诊断，重点研究粗糙神经网络方法、小波分析方法和分形几何方法三种故障诊断方法，并进行仿真验证。
First , the thesis summarizes the states of research about fault diagnosis for flighter control surface , points out the disadvantages . then , the way of this thesis is ascertained , that is , the thesis should be emphasized in the model - independent methods 首先，对歼击机操纵面故障诊断的研究现状进行了总结，指出了缺点和不足。然后确定了本文的研究方向? ?不依赖于解析模型的故障诊断方法的研究。
