Flutter Suppression of an Aircraft Wing Using a Control Surface

摘要

A set of techniques was devised to design a control system to suppress the onsetof hard and soft flutter to a higher speed. The study was a purely theoretical analysis carried out an two wing models: a tip missile configuration which exhibited hard flutter, and an engine pylon configuation which exhibited soft flutter. The method of flutter control used frequency response data fits around unity radius encirclements of the 1 point on Nyquist plots. These methods were revised and made much more efficient and easy to use giving better results than achieved before. The engine pylon (soft flutter) model was suppressed to 1.37 Vf using the onboard pair of tranducers as defined by BAe (British Aerospace), and the tip missile (hard flutter) model was suprressed to 1.73 Vf using all four BAe transducers as defined by BAe. These control laws gave stability between the original flutter speeds and those as above so gain scheduling against velocity was not required. Using an optical transducer positioning method, the soft flutter model was suppressed further, to 1.46 Vf but the outboard transducers were found to be in the optimal position for the hard flutter model.