کنترل ارتعاشات بال هوشمند با استفاده از میکروفلپ ها

The present study considers the use of Piezoelectric sensors and Micro trailing edge flap actuators to vibration control of aircraft wing. Consider wing as cantilever beam and using Piezoelectrics as sensors and using their output voltages as input of P-action or PD-action controllers and using controllers output to be the actuation energy of Microflaps provides us to control the wing vibrations. Microflaps require low actuation power and low hinge moments in comparison to conventional flaps due to small size. Even we can eliminate hinge moments. To actuate Microflaps we use piezoelectric sensors because they provide us sufficient DC voltage at low deflection, so we can decrease vibration significantly. Result shows decrease about 30 to 40 percent in maximum vibration amplitude.

Keywords:

ارتعاشات بال , پیزوالکتریک ها , سنسورهای پیزوالکتریک , کنترل ارتعاشات , میکروفلپ ها