基于IMM算法的容错气动参数辨识

Fault-tolerant aerodynamic parameter identification based on IMM algorithm

针对高超声速飞行器非线性模型气动参数在线辨识问题,将需要辨识的参数增广为状态,建立理论解析模型和实际飞行模型。利用交互多模型(IMM)算法在传统3-2-1-1激励输入条件下对增广"状态"进行跟踪,并将跟踪结果作为对参数的辨识结果。仿真结果表明,IMM算法可以在正常及舵面卡死条件下实现对高超声速气动参数的准确辨识,具有较好的容错性能,并能快速诊断出舵面故障。

For on-line identification of aerodynamic parameters of the hypersonic vehicle with nonlinear model,the parameters that need to be identified are extended as state,and the theoretical model and the actual flight model are established.IMM is used to track the " state" under the traditional 3-2-1-1 excitation input condition,and the tracking results are used as the results of the identification of the parameters.Simulations show that IMM algorithm can realize the accurate identification of hypersonic aerodynamic parameters with the rudder at normal and jammed conditions,so it has good fault-tolerant performance and can quickly diagnose the rudder＇s fault.