Modeling of Dynamic Loading of Morphing Wing Aircraft

Obradovic, Borna; Subbarao, Kamesh

doi:10.2514/6.2010-8236

Cited by 11 publications

(9 citation statements)

References 11 publications

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“…Under these conditions, both control surface and overall wing efficiency is reduced leading to suboptimal aircraft performance. This drawback of the current system is one of the main reasons the search for "morphing" aircraft systems and technologies continues [2][3][4][5][6][7][8][9][10][11][12][13]. If successful, and through using control configurations that allow more general and subtle changes in streamwise curvature, morphing for control may lead to increases in aerodynamic efficiency while maintaining comparable performance.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation into the Control and Load Alleviation Capabilities of Articulated Winglets

Gatto

Bourdin²

2012

International Journal of Aerospace Engineering

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An experimental investigation into the real-time flow and control characteristics of a flying wing with articulated winglets is described in this paper. The philosophy of the concept centres around the use of active, in-flight adjustment of each wing's winglet dihedral angle, both as a primary means of aircraft roll control (single winglet actuation) and though smaller equal and simultaneous winglet deflections, tailor and alleviate main wing load. Results presented in this paper do provide good evidence of the concept's ability to adequately perform both tasks, although for the current chosen wing/winglet configuration, roll control authority was unable to achieve, per unit of control surface deflection, the same level of performance set by modern aileron-based roll control methodologies.

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Section: Introductionmentioning

confidence: 99%

Experimental Investigation into the Control and Load Alleviation Capabilities of Articulated Winglets

Gatto

Bourdin²

2012

International Journal of Aerospace Engineering

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“…The rigid body equations of motion are sufficient to describe monocopters whose control surfaces involve small mass distribution changes, such as a trailing-edge flap. For monocopters with full wing motion (typically used in helicopters), the rigid body assumption is questionable, and a better approach is to extend the rigid body dynamics by including morphing forces 9 and moments. The full equation set the reads:…”

Section: Flight Dynamicsmentioning

confidence: 99%

A Multi-Scale Simulation Methodology for the Samarai Monocopter ?UAV

Obradovic

Barto

et al. 2012

AIAA Modeling and Simulation Technologies Conference

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The Samarai µUAV is a biologically-inspired monocopter, similar in its flight characteristics to the maple seed. It is essentially a single, asymmetric helicopter blade, powered by a tip propeller. High-fidelity simulation of such a vehicle is challenging, but of great importance to efficient design. A multi-scale simulation methodology is presented, utilizing Computational Fluid Dynamics (CFD)-based predictions of the aerodynamic behavior, coupled to the more CPU-efficient blade element and free-wake vortex ring models. The resulting simulation is suitable for engineering analysis and design of monocopters, but nevertheless captures the relevant physical phenomena at low Reynolds number flight regime.

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“…ANY researches are made around the world in the new challenge field related to the morphing aircraft, with the purpose to improve operational efficiency, particularly by reducing fuel consumption [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16] . Therefore, a lot of architecture were and are still imagined, designed, studied and developed, for this new concept application.…”

Section: Introductionmentioning

confidence: 99%

Control strategies for an experimental morphing wing model

Grigorie

Попов

Botez

2014

AIAA Atmospheric Flight Mechanics Conference

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The paper presents the control strategies used in an experimental morphing wing model starting from the open loop architecture until a real time optimized closed loop architecture. Three control methods are exposed here, methods designed to obtain and maintain some optimized airfoils during the wind tunnel tests. Also, for all designed architectures the experimental control results are shown. First method uses a database stored in the computer memory, database which contains some optimized airfoils correlated with the airflow cases as combinations of Mach numbers and angles of attack. The method is based on a controller that takes as reference value the necessary displacement of the actuators from the database in order to obtain the morphing wing optimized airfoil shape. The second method uses a similar controller as the first method but the control loop is built around the changes of the Cp values calculated by XFoil software in two fixed positions along the chord of the wing, positions associated to two Kulite sensors linked through aerodynamic interdependence with the actuators positions. The third control method is based on the pressure information received from the sensors and on the transition point position estimation. It includes, as inner loop, the first control method of the actuation lines. The method uses an optimizer code which finds the best actuators configuration in order to maximize the position of the transition, i.e. at the end of optimization sequence the transition should be found nearest possible to the trailing edge. Nomenclature c f = cam factor C D = drag coefficient C L = lift coefficient C p = pressure coefficient dY 1 = vertical deflection of the flexible skin in the first actuation line dY 2 = vertical deflection of the flexible skin in the second actuation line dY 1opt = optimal vertical displacement of actuator 1 dY 2opt = optimal vertical displacement of actuator 2 M = Mach number x tr = transition point position α = angle of attack

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Modeling of Dynamic Loading of Morphing Wing Aircraft

Cited by 11 publications

References 11 publications

Experimental Investigation into the Control and Load Alleviation Capabilities of Articulated Winglets

Experimental Investigation into the Control and Load Alleviation Capabilities of Articulated Winglets

A Multi-Scale Simulation Methodology for the Samarai Monocopter ?UAV

Control strategies for an experimental morphing wing model

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