Vibration and control of aircraft wings

The analysis and control of an aircraft, non-linear, variable parameter win g model is considered. Simple procedures using established techniques relat ed to wing vibrational problems are outlined. Frequency response methods ar e employed to accommodate analysis methods wherein both the poles and zeros of the system model vary with velocity. A simple control strategy is invok ed enabling regulation. The transient behaviour of the system is computed f or the operational speeds of interest. The effectiveness of the control str ategy is commented upon.