Experimental Identification of a System Containing Geometric Nonlinearities
In this paper we discuss a technique for the experimental identification of structures exhibiting geometric nonlinearities, in particular aircraft with highly flexible wings. A half joined wing sensorcraft model is used to demonstrate the approach, which involves performing vibration tests whilst simultaneously applying static loads to the structure. A series of static and dynamic tests are undertaken and demonstrate that parts of the structure undergo both stiffening and softening behaviour, and then the Resonant Decay Method is used to identify the nonlinear parts of the structure.
KeywordsGeometric nonlinearity Experimental identification Resonance decay method Joined wing Nonlinear identification
This work is supported as part of the EPSRC funded Programme Grant on Engineering Nonlinearity, grant EP/K003836/1.
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