04.2 - Aerostructures Design, Structural Dynamics, Aeroelasticity
AEROELASTIC DIVERGENCE AND FLUTTER ANALYSIS OF A WING WITH ALL MOVING WING TIP
W. Wang¹, W. Qian¹, X. Ai¹; ¹Dalian University of Technology, China
This paper makes a first pass at simulating and analyzing aeroelastic characteristics for a wing with all moving wing tip (AMT) that uses fluid structural interaction methods for different flight conditions. The AMT is a promising control surface that fits in the control effector for tailless aircraft because it can increase the drag, decrease the maximum lift-to-drag ratio, reduce radar reflection area, and provide yawing moment. Aeroelastic divergence depends on the torsional stiffness of wings and flutter relied on the structural dynamic of wings are concern in the design of flights. The computational fluid dynamic method offers an approach for calculating unsteady aerodynamic force, the Newmark method is applied to solve the aeroelastic equation, the Delaunay method is used for dynamic mesh, and the Rational Base Function is adopted to interpolate the load and displacement. A novel configuration, which is a wing with all moving tip, were present for the study of the aeroelastic of all moving tip. A structural dynamic model based on the finite element method and an aerodynamic model based on the finite volume method were developed in this study to investigate the aeroelastic divergence and flutter of the wing with AMT. The natural frequencies and mode shapes are gained by the Lancozs method and the mode matrix is sent to solve the aeroelastic equation. The first bending mode of wing and the second rotation mode of AMT were calculated by the Lancozs method. The generalized displacement time history of the two modes were computed by the fluid structural interaction method. According to the results, the divergence dynamic pressure is approximately 220 KPa at the subsonic condition in which the Mach number is less than or equal to 0.8. The flutter dynamic pressure is between 111 KPa with 135 Kpa at the transonic condition which the Mach numbers are 0.9, 0.95, 1.05, 1.1, 1.2, and 1.3. Different flight conditions can compute different generalized displacement time hist