飞机结冰气动参数综合检测方法研究

Research on Comprehensive Parameter Identification of Inflight Aircraft Icing

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。

Aircraft icing will cause serious damage to aircraft flight security. Identifying aircraft icing parameter and changing control law will become one of important methods to solve aircraft icing problem. The paper introduces ice parameter mode for the six degrees of freedom of aircraft. Two different orders of severity icing which change over time are defined. Then time invariant and time variable aircraft icing parameter identification methods are introduced. There two methods both base on H-infinity and can be used synthetically. With two methods＇ advantage, the difficult of online icing parameter identification can he solved effectively. Simulation results verify its feasibility and it is useful for reducing the delay of icing detection.