Unsteady aerodynamic model of flexible flapping wing
نویسندگان
چکیده
منابع مشابه
Unsteady aerodynamic forces of a flapping wing.
The unsteady aerodynamic forces of a model fruit fly wing in flapping motion were investigated by numerically solving the Navier-Stokes equations. The flapping motion consisted of translation and rotation [the translation velocity (u(t)) varied according to the simple harmonic function (SHF), and the rotation was confined to a short period around stroke reversal]. First, it was shown that for a...
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A computational fluid-dynamic analysis was conducted to study the unsteady aerodynamics of a model fruit fly wing. The wing performs an idealized flapping motion that emulates the wing motion of a fruit fly in normal hovering flight. The Navier-Stokes equations are solved numerically. The solution provides the flow and pressure fields, from which the aerodynamic forces and vorticity wake struct...
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Developing a FWNAV is an ambitious and arduous tasks relying currently mostly on trial and error method. In order to assist these developments, a preliminary design tool evaluating the aeroelastic performance of a flapping wing is sound. Our approach, coupling a structural finite element solver to a quasi-steady aerodynamic model, is here reported along with some of its applications: the select...
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Nonlinear aeroelasticity of a flapping wing Micro Air Vehicle (MAV) is analyzed in this paper. The geometrically nonlinear deformations are modeled by a nonlinear strain-based beam formulation, coupled with six rigid-body degrees of freedom of the aircraft. Wing flapping kinematics is described using a set of Euler angles. Two types of unsteady aerodynamic formulations are incorporated for load...
متن کاملBoundary Control for Flutter Suppression of a Flexible Wing under Unsteady Aerodynamic Loads
This paper addresses the boundary control for flutter suppression of a flexible wing, both in bending and twisting displacements, under unsteady aerodynamic loads. The wing is modeled by a distributed parameter system described as two coupled partial differential equations. The problem is tackled in the framework of semigroup theory, and a Lyapunov-based stability analysis is carried out to ass...
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ژورنال
عنوان ژورنال: Aerospace Science and Technology
سال: 2018
ISSN: 1270-9638
DOI: 10.1016/j.ast.2018.07.017