Aeroelastic Shape Optimization of a Flapping Wing

Stewart, Edward; Patil, Mayuresh; Canfield, Robert A.; Snyder, Richard

doi:10.2514/1.c033278

Cited by 10 publications

(2 citation statements)

References 37 publications

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“…Kim and Han [9], Li et al [10] developed a smart flapping wing with a macro-fiber composites actuator, in which the camber can be changed by using the surface actuators to enhance the aerodynamic performance. Stewart et al [11] performed a multi-objective optimization method on the shape of a rigid flapping wing to increase the cycle-averaged thrust and reduce the peak of input power. In the case of the AeroVironment NanoHummingbird wing design, the strong coupling problem between flapping deformation and aerodynamic force was approached experimentally [5].…”

Section: Introductionmentioning

confidence: 99%

A Wind Tunnel Experimental Study on the Flexible Flapping Wing With an Attached Airfoil to the Root

et al. 2019

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With the purpose to improve the performance of the flexible membrane flapping wing, a kind of flapping wing with an attached airfoil to the root is designed and tested in a wind tunnel. In order to study, the actual performance improvement of the flapping wing, the flight performance is calculated and compared instead of the aerodynamic performance. A method to establish a semi-empirical cycle-averaged mathematical model for the flapping wing with high precision based on the wind tunnel experiment is proposed to calculate the flight performance. The established continuous mathematical model can solve the problem of how to obtain the trimmed state by using discrete experimental data. By attaching the airfoil EPPLER 378 with a thickness of 4.07% chord length to the root, the cruise velocity envelope is expanded, especially with a small cruise velocity. Although the attached airfoil to the root can cause a slight decrease in endurance and range of the flapping wing, it will greatly enhance the climbing performance and effectively reduce the demand for the takeoff sites. Besides, the flapping wing with an attached airfoil to the root will result in a significant reduction in the radius of steady turning and will improve the maneuverability. In addition, the airfoil EJ 85, which is similar to the airfoil EPPLER 378 in shape and camber but has a larger thickness of 6.5% chord length, is attached to the root of the original flapping wing. The same experiment and modeling procedure are performed on the airfoil EJ 85 to analyze the difference in performance of the flapping wing with different airfoil thickness.

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Section: Introductionmentioning

confidence: 99%

A Wind Tunnel Experimental Study on the Flexible Flapping Wing With an Attached Airfoil to the Root

et al. 2019

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“…Stewart et al. 17 performed shape optimization of a plate-like flapping wing. The aeroelastic system was analyzed by using an unsteady vortex lattice aerodynamic model with a plate finite element model.…”

Section: Introductionmentioning

confidence: 99%

Multidisciplinary design optimization of the flapping wing system for forward flight

Choi

Park

2017

International Journal of Micro Air Vehicles

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The success of a flapping wing air vehicle flight is strongly related to the flapping motion and wing structure. Various disciplines should be considered for analysis and design of the flapping wing system. A design process for a flapping wing system is defined by using multidisciplinary design optimization. Unsteady aeroelastic analysis is employed as the system analysis. From the results of the aeroelastic analysis, the deformation of the wing is transmitted to the fluid discipline and the dynamic pressure is conveyed to the structural discipline. In the fluid discipline, a kinematic optimization problem is solved to maximize the time-averaged thrust coefficient and the propulsive efficiency simultaneously. In the structural discipline, nonlinear dynamic topology optimization is performed to find the distribution of reinforcement by using the equivalent static loads method for nonlinear static response structural optimization. The defined design process is applied to a flapping wing air vehicle model and the flapping wing air vehicle model is fabricated based on the optimization results.

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Experimental study of flapping-wing aerodynamic coefficients and landing performance estimation

2023

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Aeroelastic Shape Optimization of a Flapping Wing

Cited by 10 publications

References 37 publications

A Wind Tunnel Experimental Study on the Flexible Flapping Wing With an Attached Airfoil to the Root

A Wind Tunnel Experimental Study on the Flexible Flapping Wing With an Attached Airfoil to the Root

Multidisciplinary design optimization of the flapping wing system for forward flight

Experimental study of flapping-wing aerodynamic coefficients and landing performance estimation

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