Active control of gust- and interference-induced vibration of tilt-rotor aircraftAn active control system to suppress the response of the blade bending modes of a tilt-rotor aircraft to axial gusts and wing/rotor interference is described. The use of blade-mounted accelerometers as sensors is shown to permit the measurement and control of tilt-rotor blade modal responses and their associated vibratory loads directly. The feedback of modal acceleration, in addition to modal rate and displacement, is demonstrated to provide a control phase lead, in comparison with feedback of modal rate and displacement only, which makes higher system gains achievable.
Document ID
19900041146
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ham, Norman D. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Wereley, Norman M. (MIT Cambridge, MA, United States)
Von Ellenrieder, Karl D. (Massachusetts Inst. of Tech. Cambridge, MA, United States)