Aeroelastic tailoring - Theory, practice, and promise

Shirk, M. H.; Hertz, Terrence J.; Weisshaar, Terrence A.

doi:10.2514/6.1984-982

Cited by 32 publications

(46 citation statements)

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“…The aircraft is modeled by nearly 30000 finite elements. The material fiber directions are designed to make the wing have outer-wash, which means the upward bending results in the nose-down twist [19]. The nonlinear aeroelastic stability of the wing part was shown in ref.…”

Section: Example Studymentioning

confidence: 99%

Linearization method of nonlinear aeroelastic stability for complete aircraft with high-aspect-ratio wings

Xie

Yang

2011

Sci. China Technol. Sci.

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A linearization method and an engineering approach for the geometric nonlinear aeroelastic stability analysis of the very flexible aircraft with high-aspect-ratio wings are established based on the little dynamic perturbation assumption. The engineering practicability of the method is validated by a complex example. For a high-altitude long-endurance unmanned aircraft, the nonlinear static deformations under straight flight and the gust loads are calculated. At the corresponding nonlinear equilibrium state, the complete aircraft is linearized dynamically and the vibration modes are calculated considering the large deformation effects. Then the unsteady aerodynamics are calculated by the double lattice method. Finally, the aeroelastic stability of the complete aircraft is analyzed. The results are compared with the traditional linear calculation. The work shows that the geometric nonlinearity induced by the large structural deformation leads to the motion coupling of the wing chordwise bending and the torsion, which changes the mode frequencies and mode shapes. This factors change the aeroelastic coupling relationship of the flexible modes leading to the decrease of the flutter speed. The traditional linear method would give not only an imprecise flutter speed but also a possible dramatic mistake on the stability. Hence, for a high-altitude long-endurance unmanned aircraft with high-aspect-ratio wings, or a similar very flexible aircraft, the geometric nonlinear aeroelastic analysis should be a necessary job in engineering practice. aeroelasticity, geometric nonlinearity, flutter, large deformation solar energy Citation:Xie C C, Yang C. Linearization method of nonlinear aeroelastic stability for complete aircraft with high-aspect-ratio wings.

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Section: Example Studymentioning

confidence: 99%

Linearization method of nonlinear aeroelastic stability for complete aircraft with high-aspect-ratio wings

Xie

Yang

2011

Sci. China Technol. Sci.

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“…The chromosomes are crossed variable-by-variable to create two new children y (1) and y (2) . Each variable (gene) is crossed with a probability of P c using the following procedure:…”

Section: Optimization Modelmentioning

confidence: 99%

“…The constraints of lamination parameters V 1 , V 2 , V 3 are described in equation (1), and the bound constraints of the t face , t core , and G core are assumed.…”

Section: Numerical Examplementioning

confidence: 99%

Aeroelastic tailoring of composite sandwich panel with lamination parameters

Jin

Song

Zhong

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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For sandwich panel with a thick core, stiffness matrix of composite sandwich panel can be formulated as function of membrane lamination parameters of the composite facesheet. In this paper, the flutter speed of a cantilevered sandwich panel is studied using lamination parameters of composite facesheet, with influence of transverse shear on sandwich panel considered. The results show that the flutter mode switch is not only related to the bending stiffness change, and also the transverse shear effect can result in switch of flutter mode. A minimum weight design of composite sandwich panel is conducted by using master-slave parallel real-coded genetic algorithm, with lamination parameters of facesheet and transverse shear modulus of foam core as design variables. The constraints considered include the flutter and divergence velocity constraints, the bound constraints of thicknesses of the facesheet and foam core. The feasible region constraints of membrane lamination parameters are also considered.

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“…In this sense, a new technology, known as the aeroelastic tailoring (see e.g., Ref. 27) and its unique advantages have been demonstrated, among others, by the successful construction and test of the Gruman's X-29 sweptforward wing aircraft. In the last decade, due to their inherent, material-level coupling between mechanical and electrical properties, piezoelectric materials (see Ref.…”

Section: Introductionmentioning

confidence: 98%

<title>Aeroelastic vibration feedback control of smart aircraft wings in subsonic flight speeds</title>

Qin

Librescu

2002

SPIE Proceedings

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A minimax control design aimed at augmenting the flutter envelope and enhancing the dynamic aeroelastic response of a smart aircraft wing subject to gust/blast loads is presented. The smart aircraft wing is modeled as an anisotropic thin-walled beam featuring circumferentially asymmetric stiffness lay-up and a number of non-classical effects such as transverse shear, warping restraint and 3-D strain effects. Adaptive materials technology is used for implementing the active control via the boundary bending moment feedback mechanism. The unsteady aerodynamic loads in subsonic compressible flows are based on 2-D indicial functions considered in conjunction with aerodynamic strip theory extended to 3-D wing model. The capability of control on flutter suppression and dynamic response enhancement are investigated, the corresponding applied voltage requirement and power consumption are addressed.

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Aeroelastic tailoring - Theory, practice, and promise

Cited by 32 publications

References 0 publications

Linearization method of nonlinear aeroelastic stability for complete aircraft with high-aspect-ratio wings

Linearization method of nonlinear aeroelastic stability for complete aircraft with high-aspect-ratio wings

Aeroelastic tailoring of composite sandwich panel with lamination parameters

<title>Aeroelastic vibration feedback control of smart aircraft wings in subsonic flight speeds</title>

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