An indicial-Polhamus aerodynamic model of insect-like flapping wings in hover

Author(s):  
C.B. Pedersen ◽  
R. Żbikowski
2014 ◽  
Vol 11 (92) ◽  
pp. 20130992 ◽  
Author(s):  
Leif Ristroph ◽  
Stephen Childress

Ornithopters, or flapping-wing aircraft, offer an alternative to helicopters in achieving manoeuvrability at small scales, although stabilizing such aerial vehicles remains a key challenge. Here, we present a hovering machine that achieves self-righting flight using flapping wings alone, without relying on additional aerodynamic surfaces and without feedback control. We design, construct and test-fly a prototype that opens and closes four wings, resembling the motions of swimming jellyfish more so than any insect or bird. Measurements of lift show the benefits of wing flexing and the importance of selecting a wing size appropriate to the motor. Furthermore, we use high-speed video and motion tracking to show that the body orientation is stable during ascending, forward and hovering flight modes. Our experimental measurements are used to inform an aerodynamic model of stability that reveals the importance of centre-of-mass location and the coupling of body translation and rotation. These results show the promise of flapping-flight strategies beyond those that directly mimic the wing motions of flying animals.


AIAA Journal ◽  
1996 ◽  
Vol 34 (7) ◽  
pp. 1435-1440 ◽  
Author(s):  
Michael S. Vest ◽  
Joseph Katz

2016 ◽  
Vol 53 (3) ◽  
pp. 701-712 ◽  
Author(s):  
A. H. M. Faisal ◽  
A. Filippone

AIAA Journal ◽  
2016 ◽  
Vol 54 (12) ◽  
pp. 3849-3858
Author(s):  
A. H. M. Faisal ◽  
A. Filippone

Author(s):  
Xuan Yang ◽  
Aswathi Sudhir ◽  
Atanu Halder ◽  
Moble Benedict

Aeromechanics of highly flexible flapping wings is a complex nonlinear fluid–structure interaction problem and, therefore, cannot be analyzed using conventional linear aeroelasticity methods. This paper presents a standalone coupled aeroelastic framework for highly flexible flapping wings in hover for micro air vehicle (MAV) applications. The MAV-scale flapping wing structure is modeled using fully nonlinear beam and shell finite elements. A potential-flow-based unsteady aerodynamic model is then coupled with the structural model to generate the coupled aeroelastic framework. Both the structural and aerodynamic models are validated independently before coupling. Instantaneous lift force and wing deflection predictions from the coupled aeroelastic simulations are compared with the force and deflection measurements (using digital image correlation) obtained from in-house flapping wing experiments at both moderate (13 Hz) and high (20 Hz) flapping frequencies. Coupled trim analysis is then performed by simultaneously solving wing response equations and vehicle trim equations until trim controls, wing elastic response, inflow and circulation converge all together. The dependence of control inputs on weight and center of gravity (cg) location of the vehicle is studied for the hovering flight case.


2017 ◽  
Vol 12 (3) ◽  
pp. 036004 ◽  
Author(s):  
Jong-Seob Han ◽  
Jo Won Chang ◽  
Jae-Hung Han

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