Limit cycle oscillation behavior of transonic control surface buzz considering free-play nonlinearity |
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| Institution: | 1. Department of Mechatronics, Ho Chi Minh City University of Technology, 268 Ly Thuong Kiet, Ho Chi Minh City, Vietnam;2. School of Mechanical Engineering, Faculty of Engineering, Tel Aviv University, Tel Aviv 69978, Israel;1. São Paulo State University (UNESP), Câmpus de São João da Boa Vista, São João da Boa Vista, São Paulo, Brazil;2. Mechanical and Aerospace Engineering, New Mexico State University, Las Cruces, NM 88003, USA;1. Department of Aerospace Engineering, Indian Institute of Science, Bengaluru 560012, India;2. Department of Aerospace Engineering, Muroran Institute of Technology, Muroran City, Hokkaido 050-8585, Japan;1. University of Sheffield, Dept. of Mech Engineering, Sheffield, England;2. Defence Science and Technology Laboratory, Salisbury, England;1. Physical Sciences Department, Embry–Riddle Aeronautical University, Daytona Beach, FL 32114, United States;2. Aerospace Engineering Department, Embry–Riddle Aeronautical University, Daytona Beach, FL 32114, United States;1. Department of Mechanical, Automotive & Materials Engineering, University of Windsor, ON, Canada N9B 3P4;2. Department of Mathematics & Statistics, University of Windsor, ON, Canada N9B 3P4;3. Department of Civil & Environmental Engineering, University of Windsor, ON, Canada N9B 3P4 |
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| Abstract: | The limit cycle oscillation (LCO) behaviors of control surface buzz in transonic flow are studied. Euler equations are employed to obtain the unsteady aerodynamic forces for Type B and Type C buzz analyses, and an all-movable control surface model, a wing/control surface model and a three-dimensional wing with a full-span control surface are adopted in the study. Aerodynamic and structural describing functions are used to deal with aerodynamic and structural nonlinearities, respectively. Then the buzz speed and buzz frequency are obtained by V-g method. The LCO behavior of the transonic control surface buzz system with linear structure exhibits subcritical or supercritical bifurcation at different Mach numbers. For nonlinear structural model with a free-play nonlinearity in the control surface deflection stiffness, the double LCO phenomenon is observed in certain range of flutter speed. The free-play nonlinearity changes the stability of LCOs at small amplitudes and turns the unstable LCO into a stable one. The LCO behavior is dominated by the aerodynamic nonlinearity for the case with large control surface oscillation amplitude but by the structural nonlinearity for the case with small amplitude. Good agreements between LCO behaviors obtained by the present method and available experimental data show that our study may help to explain the experimental observation in wind tunnel tests and to understand the physical mechanism of transonic control surface buzz. |
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| Keywords: | Control surface buzz Transonic flow Aerodynamic nonlinearity Free-play Single degree of freedom flutter Limit cycle oscillation |
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