Analysis of Wind Tunnel Unsteady Aerodynamic Data of Flexible Micro Air Vehicle Wings

Albertani, Roberto; Babcock, Judson

doi:10.2514/6.2008-6249

Cited by 9 publications

(6 citation statements)

References 7 publications

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“…Wing AOA was controlled with a pitch–plunge rig, where the main components are a pair of Trilogy ironless magnetic linear motors (Parker Automation) with Aries Servo Drivers (AR20AE; Parker Automation), and controlled by a DMC-2020 model motion controller (Galil Motion Control). For further description of the pitch–plunge rig, see Albertani and Babcock (2008). Wing inclination was measured with an SCA121T-D03 inclinometer (VTI Technologies).…”

Section: Methodsmentioning

confidence: 99%

Aerodynamic control of micro air vehicle wings using electroactive membranes

Hays

Morton

Dickinson

et al. 2012

Journal of Intelligent Material Systems and Structures

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Dielectric elastomer materials are ideal candidates for developing high-agility micro air vehicles due to their electric field–induced deformation. Consequently, the aero-structural response and control authority of the dielectric elastomer material, VHB 4910, are characterized on an elliptical membrane wing. An experimental membrane wing platform was constructed by stretching VHB 4910 over a rigid elliptical wing-frame. The low Reynolds number (chord Reynolds number < 106) and aerodynamics of the elliptical wing were characterized when different electrostatic fields were applied to the membrane. We observe an overall increase in lift with maximum gains of 20% at an applied voltage of 4.5 kV and demonstrate the ability to delay stall. The time-averaged aerodynamic surface pressure is also investigated by comparing sting balance data and membrane deformation measured using visual image correlation. The experimental results are compared to a nonlinear finite element membrane model to further understand the effects of aerodynamic load and electric fields on membrane displacements. Model predictions of surface pressure provide insight into how the electrostrictive constitutive relations influence the fluid–structure interactions of the membrane. This is validated by comparing lift predictions from the model with time-averaged wind tunnel lift measurements near stall.

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Section: Methodsmentioning

confidence: 99%

Aerodynamic control of micro air vehicle wings using electroactive membranes

Hays

Morton

Dickinson

et al. 2012

Journal of Intelligent Material Systems and Structures

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“…From this figure, we can infer that as long as the complex part of the LTV poles is non-zero, the LTV poles remain bounded. However, the instant the complex part of the LTV poles drops to zero, it then remains zero for all future time (this can also be seen by substituting p2i=0 in Eqn (15) and noticing that it leads to making dp2i/dt=0), and the real part of the LTV poles subsequently goes to negative 00. Now the case when the frozen time roots change from real to complex, and vice-versa with an example wherein ai(t) = 3-t; ao(t) = 0.2 for t=[0,5] will be illustrated.…”

Section: Now If Dmentioning

confidence: 99%

Research Institute for Autonomous Precision Guided Systems

Rogacki¹,

Ukeiley²,

Dixon³

et al. 2008

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense. Washington Headquarters Services. Directorate for Information Under the leadership of Dr. Rogacki and Dr. Albertani there was significant progress made in delivering a hardware-in-the-loop rapid prototyping capability at the UF-REEF. Embedded systems are designed to control complex plants such as land vehicles, satellites, spacecrafts, unmanned aerial vehicles (UAVs), aircrafts, weapon systems, marine vehicles, and jet engines. They generally require a high level of complexity within the embedded system to manage the complexity of the plant under control. Hardware-in-the-Loop (HIL) simulation is a technique that is used increasingly in the development and test of complex real-time embedded systems.The purpose of HIL simulation is to provide an effective platform for developing and testing real-time embedded systems. HIL simulation provides an effective platform by adding the complexity of the plant under control to the test platform. The complexity of the plant under control is included in test and development by adding a mathematical representation of all related dynamic systems. These mathematical representations are referred to as the "plant simulation.'" The UF-REEF has established a HIL simulation capability for MAV's that will lead to a rapid prototyping capability.The Task 1 research plan included testing the visual based control system running on the cluster PCs in the REEF Visualization Lab by flying a relatively stable off the shelf slow flier (similar to MAV flight regime) in the small REEF wind tunnel and later in the large wind tunnel. The general layout of the test bed is illustrated in Fig. 2.

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“…3b, in which the pitch angle is varied during the plunge in relationship to the plunge acceleration, resulting in a constant AOA during the plunge. A proof of this experimental technique was the focus of previous research [29], and the current work will extend the experimental technique to determine the relationship between the relevant aerodynamic parameters and the rate of change of AOA and pitch angle.…”

Section: Methodsmentioning

confidence: 98%

Experimental Estimation of the Rotary Damping Coefficients of a Pliant Wing

Babcock

Albertani

Abate

2012

Journal of Aircraft

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This paper describes the experimental estimation of the rotary-damping coefficients of micro air vehicle (MAV) wings using a novel system for dynamic wind-tunnel testing. Two geometrically identical Zimmerman wings are used, one rigid and one flexible. The flexible wing consists of a perimeter-reinforced latex membrane with three levels of prestrain. A two-degrees-of-freedom motion rig permits the control of the two individual components of the rotary-damping moment. A modern design of experiments methodology was used to elucidate the correlation between the wings' elastic membrane prestrain state and the aerodynamic characteristics. For the flexible wing, elastic deformations are measured using visual image correlation and evaluated using a dimensionless parameter. The resulting aerodynamic model compares well with static reference data. The presence of dynamic changes in the angle of attack or pitch angle has a significant effect on the response of the rigid and flexible MAV wings, particularly on the pitching moment coefficient. At the current levels of the dimensionless membrane wing elastic prestrain, the pretension strain did not exhibit any correlation with the rotary-damping moment coefficients, whereas the pretension strain level does appear as a factor in the rotary-damping drag coefficient. Nomenclature

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Analysis of Wind Tunnel Unsteady Aerodynamic Data of Flexible Micro Air Vehicle Wings

Cited by 9 publications

References 7 publications

Aerodynamic control of micro air vehicle wings using electroactive membranes

Aerodynamic control of micro air vehicle wings using electroactive membranes

Research Institute for Autonomous Precision Guided Systems

Experimental Estimation of the Rotary Damping Coefficients of a Pliant Wing

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