Nonlinear aeroelastic analysis of aircraft with high-aspect-ratio wings

Patil, Mayuresh; Hodges, Dewey H.; S., Cesnik, Carlos E.

doi:10.2514/6.1998-1955

Cited by 37 publications

(33 citation statements)

References 27 publications

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“…An improvement in the flutter behaviour can be obtained, according to the conclusions of the previous section, if the chord-wise stiffness is increased in order to obtain a lagging frequency closer to the bending torsion one (a different method is reported in reference [18]). A value of EJ lag ¼ 3:3610 6 N m 2 is introduced into the model.…”

Section: Similar Scaled Wingmentioning

confidence: 91%

Aeroelastic behaviour of a solar-powered high-altitude long endurance unmanned air vehicle (HALE-UAV) slender wing

Frulla¹

2004

Proceedings of the Institution of Mechanical Engineers, Part G:

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A preliminary dynamic and aeroelastic investigation is performed in a simplified equivalent configuration derived from the HELIPLAT HAVE-UAV (high-altitude very-long endurance unmanned air vehicle) wing structure. The presence of slender wing structures introduces in the structural design a certain degree of non-linearity, forcing the designer to deal with specific phenomena, one of which is described. A simple dynamic system is used to point out the important effect due to the inclusion of the deformed equilibrium configuration into the dynamic behaviour of the system. A modified wing structure configuration is used to point out this effect in the flutter behaviour of slender structures. Some interesting design indications are presented.

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Section: Similar Scaled Wingmentioning

confidence: 91%

Aeroelastic behaviour of a solar-powered high-altitude long endurance unmanned air vehicle (HALE-UAV) slender wing

Frulla¹

2004

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…This offset can be attributed again to the 2D nature of the UM/NAST solution, and to the difficulty Euler codes have in accurately predicting drag. It is interesting to note (in this result and those that follow) the strong interaction between the chordwise bending and torsional degrees of freedom [5]. …”

Section: A Static Aeroelastic Verificationmentioning

confidence: 99%

“…Several other studies on HALE wings have used low-order aerodynamics [5][6][7][8][9][10][11][12][13][14]. First, Patil, Hodges, and Cesnik authored a series of works [5,6,8] about the coupling of an exact intrinsic beam model with Peters' finite-state aerodynamics [15] and its application to highly flexible aircraft. In a parallel effort, Drela [7] developed ASWING, an integrated design and analysis package which incorporated a nonlinear beam model with lifting-line aerodynamics.…”

Section: Introductionmentioning

confidence: 99%

High-fidelity Aeroelastic Analysis of Very Flexible Aircraft

Hallissy

Cesnik

2011

52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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This paper describes the development and capabilities of a high-fidelity aeroelastic simulation tool for very flexible aircraft (HiFi-VFA) within a Multi-Disciplinary Computing Environment (MDICE). The code loosely couples a geometrically nonlinear, quasi-3D structural solver with an Euler/Navier-Stokes flow solver capable of arbitrary, large, mesh deformation. Verification of the static aeroelastic solver is presented for a hypothetical high aspect ratio wing discussed in the literature. Time domain aeroelastic simulations using the new code generally agree well with the response of an in-house aeroelastic simulation toolbox, but the high-fidelity results suggest the presence of higher aerodynamic damping than predicted by the finite state aerodynamics. With these results, flutter boundaries are sought using two flutter prediction methods (ARMA and FMDS) and the advantages/disadvantages of these prediction methods in computational aeroelasticity are assessed.

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“…In order to get a better understanding of the nonlinear aeroelastic phenomena involving the entire vehicle, Refs. [2] and [7] developed a low-order high-fidelity aeroelastic model for preliminary design and control synthesis. It focuses on a very flexible high-aspect ratio (passive) composite wing with discrete flap control, and models the entire aircraft.…”

Section: Introductionmentioning

confidence: 99%

Active Aeroelastic Tailoring of High-Aspect-Ratio Composite Wings

Cesnik¹

2005

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This paper presents a framework for studying the effects of combined bending and twisting actuation on the aeroelastic performance of highly-flexible active composite wings. The effects of embedded anisotropic piezoelectric strain actuators are consistently accounted for throughout the nonlinear aeroelastic analysis. The nonlinear active aeroelastic analysis consists of an asymptotically correct active crosssectional formulation, geometrically-exact mixed formulation for dynamics of moving beams, and a finitestate unsteady aerodynamics with the ability to model dynamic stall using the ONERA model. Once the nonlinear equilibrium is determined, a linearization about that point yields a set of equations in state space form. From that, different LQG controllers can be designed and the closed-loop system simulated to determine the impact of the anisotropic piezoelectric strain actuators on the stability enhancement and gust alleviation characteristics of flexible wings. A proposed wind tunnel model is presented to illustrate the analysis framework and to show the potential of active aeroelastic tailoring using active fiber composites. Results show that the orientation of the actuators and the electric field profile can be tailored for maximum stability augmentation or for maximum gust alleviation, and that a compromised situation can still have significant improvement in both performance metrics.

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Nonlinear aeroelastic analysis of aircraft with high-aspect-ratio wings

Cited by 37 publications

References 27 publications

Aeroelastic behaviour of a solar-powered high-altitude long endurance unmanned air vehicle (HALE-UAV) slender wing

Aeroelastic behaviour of a solar-powered high-altitude long endurance unmanned air vehicle (HALE-UAV) slender wing

High-fidelity Aeroelastic Analysis of Very Flexible Aircraft

Active Aeroelastic Tailoring of High-Aspect-Ratio Composite Wings

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