Identification Method for Constructing Helicopter Flight Dynamics Model with Rotor Degrees of Freedom

摘要

A system identification method for constructing helicopter high order flight dynamics model is presented.rnA parameterized rotor flapping model which is suitable for identification is deduct, the 6 DOF (Degrees OfrnFreedom) rigid body flight dynamics model is extended to 9 DOF high order flight dynamics identificationrnmodel. Frequency identification algorithm that based on Bode sensitivity function is established. Anrnacceleration method is designed according to the convergence speed of parameters in the identificationrnalgorithm is different. A frequency two step method which can be used for identifying helicopter high orderrnflight dynamics model is formed. Model identification and validation based on flight test data of certainrnhelicopter are implemented. A comparison research to the 6 DOF low order model is conducted. Thernresults show that the developed method can solve the identification problem of helicopter high order flightrndynamics model effectively; the model accuracy is increased considerably.