Journal
CHINESE JOURNAL OF AERONAUTICS
Volume 33, Issue 1, Pages 48-63Publisher
ELSEVIER SCIENCE INC
DOI: 10.1016/j.cja.2019.07.006
Keywords
Aeroelasticity; Flutter; Geometric nonlinearity; Reduced order models; Response analysis; Structural model
Categories
Funding
- National Key Research and Development Program of China [2016YFB 0200703]
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In this paper, a framework is established for nonlinear flutter and gust response analyses based on an efficient Reduced Order Model (ROM). The proposed method can be used to solve the aeroelastic response problems of wings containing geometric nonlinearities. A structural modeling approach presented herein describes the stiffness nonlinearities with a modal formulation. Two orthogonal spanwise modes describe the foreshortening effects of the wing. Dynamic linearization of the ROM under nonlinear equilibrium states is applied to a nonlinear flutter analysis, and the fully nonlinear ROM coupled with the non-planar Unsteady Vortex Lattice Method (UVLM) is applied to gust response analysis. Furthermore, extended Precise Integration Method (PIM) ensures accuracy of the dynamic equation solutions. To demonstrate applicability and accuracy of the method presented, a wind tunnel test is conducted and good agreements between theoretical and test results of nonlinear flutter speed and gust response deflection are reached. The method described in this paper is suitable for predicting the nonlinear flutter speed and calculating the gust responses of a large-aspect-ratio wing in time domain. Meanwhile, the results derived highlight the effects of geometric nonlinearities obviously. (C) 2019 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd.
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