Numerical studies of a non-linear aeroelastic system with plunging and pitching freeplays in supersonic/hypersonic regimes |
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| Institution: | 1. College of Aerospace Engineering; Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;2. Mechanical and Aeronautical Engineering Department, Clarkson University, Potsdam, NY 13699, USA;1. Departamento de Matemáticas, Fac. Ciencias Experimentales, University of Huelva, Avda. Tres de Marzo s/n, 21071 Huelva, Spain;2. Departamento de Matemática Aplicada II, E.S. Ingenieros, University of Sevilla, Camino de los Descubrimientos s/n, 41092 Sevilla, Spain;1. Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu 210016, China;2. Shenyang Aircraft Design and Research Institute, Shenyang, Liaoning 110035, China;1. Centre for Aeronautics, Cranfield University, Cranfield, Bedfordshire MK43 0AL, UK;2. School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, People’s Republic of China |
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| Abstract: | The flutter and post flutter of a two-dimensional double-wedge lifting surface with combined freeplay and cubic stiffness nonlinearities in both plunging and pitching degrees-of-freedom operating in supersonic/hypersonic flight speed regimes have been analyzed. In addition to the structural nonlinearities, the third-order piston theory aerodynamics is used to evaluate the unsteady non-linear aerodynamic force and moment. Such model accounts for stiffness and damping contributions produced by the aerodynamic loads. Responses involving limit cycle oscillation and chaotic motion are observed over a large number of parameters that characterizes the aeroelastic system. Results of the present study show that the freeplay in the pitching degree-of-freedom and soft/hard cubic stiffness in the pitching and plunging degrees-of-freedom have significant effects on the LCOs exhibited by the aeroelastic system in the supersonic/hypersonic flight speed regimes. The simulations also show that the aeroelastic system behavior is greatly affected by physical structural parameters, such as the radius of gyration and the frequency ratio, especially in post-flutter regimes, when accounting for all system nonlinearities. It has been shown that at high Mach numbers the non-linear aerodynamic stiffness yields detrimental effects from the aeroelastic point of view, while the damping one do not. |
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