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Research Papers

Aeroelastic Analysis of Membrane Microair Vehicles—Part I: Flutter and Limit Cycle Analysis for Fixed-Wing Configurations

[+] Author and Article Information
Peter J. Attar

School of Aerospace and Mechanical Engineering, The University of Oklahoma, Norman, OK 73019peter.attar@ou.edu

Raymond E. Gordnier

 Air Force Research Laboratory, Wright-Patterson AFB, OH 45433-7913

Jordan W. Johnston, William A. Romberg, Ramkumar N. Parthasarathy

School of Aerospace and Mechanical Engineering, The University of Oklahoma, Norman, OK 73019

J. Vib. Acoust 133(2), 021008 (Mar 17, 2011) (8 pages) doi:10.1115/1.4002129 History: Received August 31, 2009; Revised June 07, 2010; Published March 17, 2011; Online March 17, 2011

This is the first of two papers concerning the fluid and structural dynamic characteristics of membrane wing microair vehicles. In this paper, a (three) batten-reinforced fixed-wing membrane microair vehicle is used to determine the effect of membrane prestrain on flutter and limit cycle behavior of fixed-wing membrane microair vehicles. For each configuration tested, flutter and subsequent limit cycle oscillations are measured in wind tunnel tests and predicted using an aeroelastic computational model consisting of a nonlinear finite element model coupled to a vortex lattice solution of the Laplace equation and boundary conditions. Agreement between the predicted and measured onset of limit cycle oscillation is good as is the prediction of the amplitude of the limit cycle at the trailing edge of the lower membrane. A direct correlation between levels of strain and the phase of the membranes during the limit cycle is found in the computation and thought to also occur in the experiment.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 13

Dominant MMAV structural response frequency versus flow velocity for 5% prestrain model at 0 deg angle of attack

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Figure 14

Computed spatial configuration (mode) of MMAV at 4 points in time during the limit cycle period for 5% prestrain model at 0 deg angle of attack at 8.0 m/s

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Figure 15

Contours of z deflection for structural modes of interest as generated with finite element modal analysis for the 5% prestrain model

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Figure 16

Deflection of MMAV versus flow velocity for 7% prestrain model at 0 deg and 2 deg (experiment only) angle of attack

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Figure 17

Root mean square of MMAV y normal strain versus flow velocity for 7% prestrain model at 0 deg and 2 deg (experiment only) angle of attack

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Figure 18

Dominant MMAV structural response frequency versus flow velocity for 7% prestrain model at 0 deg and 2 deg (experiment only) angle of attack

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Figure 19

Computed spatial configuration (mode) of MMAV at 4 points in time during the limit cycle period for 7% prestrain model at 0 deg angle of attack at 4.50 m/s and 5.00 m/s

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Figure 20

Limit cycle oscillation onset velocity versus level of membrane prestrain for 0 deg angle of attack

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Figure 21

Limit cycle oscillation dominant frequency at onset velocity versus level of membrane prestrain for 0 deg angle of attack

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Figure 1

Photograph of three batten experimental model

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Figure 2

Computational mesh used for structural dynamics

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Figure 3

Deflection of MMAV versus flow velocity for 2% prestrain model at 0 deg angle of attack

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Figure 4

Root mean square of MMAV y normal strain versus flow velocity for 2% prestrain model at 0 deg angle of attack

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Figure 5

Dominant MMAV structural response frequency versus flow velocity for 2% prestrain model at 0 deg angle of attack

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Figure 6

Experimentally measured response of y normal strain versus time for 2% prestrain model at 0 deg angle of attack and 4.0 m/s

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Figure 7

Computed spatial configuration (mode) of MMAV at 4 points in time during the limit cycle period for 2% prestrain model at 0 deg angle of attack at 2.0 m/s

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Figure 8

Computed spatial configuration (mode) of MMAV at 4 points in time during the limit cycle period for 2% prestrain model at 0 deg angle of attack at 6.0 m/s

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Figure 9

Computed spatial configuration (mode) of MMAV at 4 points in time during the limit cycle period for 2% prestrain model at 0 deg angle of attack at 8.0 m/s

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Figure 10

Contours of z deflection for structural modes of interest as generated with finite element modal analysis for the 2% prestrain model

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Figure 11

Deflection of MMAV versus flow velocity for 5% prestrain model at 0 deg angle of attack

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Figure 12

Root mean square of MMAV y normal strain versus flow velocity for 5% prestrain model at 0 deg angle of attack

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