The analysis and control of an aircraft, non-linear, variable parameter wing model is considered. Simple procedures using established techniques related to wing vibrational problems are outlined. Frequency response methods are employed to accommodate analysis methods wherein both the poles and zeros of the system model vary with velocity. A simple control strategy is invoked enabling regulation. The transient behaviour of the system is computed for the operational speeds of interest. The effectiveness of the control strategy is commented upon.
Vibration and control of aircraft wings
1998-05-01
13 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
stability , control , vibrations , aircraft , wing
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