Research On Vibration Control For Smart Rotor

As a new type of active vibration control for helicopter, the smart rotor is a hot point in the field of helicopter engineering. This thesis, which is devoted to the research on the smart rotor with actively controlled trailing-edge flap for hub oscillatory load reduction, offers a potential approach for the vibration reduction of helicopter.Because of the periodicity of the hub oscillatory load and the nonlinearity of the I/O relationship of the smart rotor, the neural control methods with both off-line and on-line modeling in frequency domain on the smart rotor and their realization procedures are presented. Their availability, stability, and robustness are proved by simulation on both model rotor and real rotor with the effect of the design parameters of the flap studied.In order to prove the feasibility of the control method mentioned, both the semiphysical test for the plant simulated by analogue computer and the model test for the cantilever beam are designed and finished with the study of the parameter selection in realization.Based on the aerodynamics, control, structural dynamics model of smart rotor in frequency domain deduced and the determination for the number of neurons in hidden layer, the neuro-emulator using multiple independent MISO neural networks with its deduced matrix expression for the smart rotor is set up. The rate of training is improved by introducing the orthogonal selection applying for smart rotor to the selection of training cases in neural modeling.