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飞机在飞行过程中会遭遇结冰问题,对飞机安全造成严重危害。通过检测飞机结冰参数,改变飞机控制律的方法,将成为解决飞机结冰问题的重要手段之一。通过引入飞机结冰参数模型,并定义两种不同严重程度的结冰情况下的结冰严重因子随时间变化曲线。分别介绍了利用H∞参数识别方法检测“时不变”与“时变”结冰气动参数,并将两种方法综合起来仿真计算。从而利用两者的优点,可以解决飞机结冰参数在线识别困难的问题。仿真计算结果达到满意的效果,对于减少检测方法的延时问题十分有效。
Planes encounter icing problems during flight, causing serious damage to aircraft safety. By detecting the icing parameters of the aircraft and changing the control law of the aircraft, it will become one of the important means to solve the icing problem of aircraft. By introducing the parameters of airplane icing parameters and defining the icing severity factors with time under two different severity icing conditions. The method of H∞ parameter identification is introduced to detect the “time-invariant” and “time-varying” icing aerodynamic parameters respectively, and the two methods are combined to simulate and calculate. Therefore, the advantages of both can be utilized to solve the problem of difficulty in recognizing the on-line ice icing parameters. Simulation results to achieve satisfactory results, to reduce the detection delay method is very effective.