Nonlinear modeling of composite wing with application to UAV flight dynamic analysis

摘要

Wings have obvious nonlinear vibrations such as buffeting and flutter during the flight of the aircraft, the nonlinear vibrations are harmful to the safety of wing structures and stability of aircraft flight. Thereby, studying nonlinear dynamic characteristics of wings is extremely important, which makes the accurate nonlinear dynamic model urgently needed. For composite wings, traditional modeling theory cannot accurately predict the variability caused by manufacturing process, machining behavior and operating condition. Therefore, this paper used a numerical-experimental method to establish the dynamic model of a composite wing, considering geometric nonlinearity. In the method, the nonlinear dynamic model of the composite wing was predicted by an experimental modal analysis with a frequency response function, and a nonlinear static test with the nonlinear least squares method. Then, the nonlinear modeling was applied to a UAV flight dynamic simulation and a flight test was also conducted. The results of the simulation are in good agreement with those of the test, which shows that the nonlinear modeling is perfectly suited for the nonlinear dynamic analysis of the composite wing.