Abstract
With the application of advanced composite materials in High-Aspect-Ratio wings (HARW), the randomness of structural parameters, such as elastic modulus and Poisson's ratio, is enhanced. Hence, in order to explore the whole picture of aeroelastic problems, it is of great significance to study the role of random structural parameters in aeroelastic problems. In this paper, the dynamic response of flexible HARW considering random structural parameters is analyzed. An aeroelastic model of a one-dimensional cantilevered Euler–Bernoulli beam considering aerodynamic forces acting on the wing is established based on Hamilton's principle. Adopted the idea of simplifying calculation, the effect of random structural parameters is analyzed. Then, considering the elastic modulus and torsional stiffness as continuously one-dimensional random field functions, and discretized by local method. The first and second order recursive stochastic nonlinear finite element equations of wing are derived by using perturbation method. Based on it, statistical expression of aeroelastic effects of the wing is derived. Monte Carlo method is adopted to verify the effectiveness of the method. Numerical simulations indicate that the method proposed can well mirror the statistical characteristics of aeroelastic response.
Highlights
With the application of advanced composite materials in High-Aspect-Ratio wings (HARW), the randomness of structural parameters, such as elastic modulus and Poisson’s ratio, is enhanced
The results show that the nonlinear static aeroelastic characteristics of flexible wing with high aspect ratio are different from those of linear aeroelastic response in transonic flow
The number of elements is 1000, time step is 0.01 s, and Newmark-Beta algorithm is adopted to study the dynamic response of HARW under the action of aerodynamic force and aerodynamic torque caused by initial root angle of attack 2 deg
Summary
HARW in air vehicle are subject to gravity, aerodynamic force, and these forces will result in multiple elastic deformation forms of the structure. This paper assumes that the torsion centers of each cross-section of the wing are in the same straight line, called elastic axis. Each cross-section of the wing is twisted around the elastic axis, which is perpendicular to the wing root section. The wing’s elastic deformation is defined in the coordinate system oexeyeze , whose origin at the torsion center of the wing root cross-section. The oeye-axis is located at the wing root cross-section and is perpendicular to the chord. Θ (x) represents the torsional deformation of the cross-section. Oxyz is a moving coordinate system with the origin fixed at the torsion center of the wing’s cross section.
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