Broad-scale area change of a non-porous surface while maintaining resistance to aerodynamic loading was demonstrated through the development of a passive elastomeric matrix composite morphing skin. The combined system includes an elastomer-fiber-composite surface layer that is supported by a flexible honeycomb structure, each of which exhibit a near-zero in-plane Poisson’s ratio. A number of elastomers, composite arrangements, and substructure configurations were evaluated and characterization testing led to the selection of the most appropriate components for prototype development. The complete prototype morphing skin demonstrated 100% uniaxial extension accompanied by a 100% increase in surface area. Results from out-of-plane pressure loading showed that out-of-plane deflection of less than 0.1 in. (2.5 mm) can be maintained at various levels of area change under pressures of up to 200 psf (9.58 kPa). Applications to wing span morphing UAVs are also discussed.
Agarwal, B.D., Broutman, L.J. and Chandrashekhara, K.2006. Analysis and Performance of Fiber Composites, John Wiley & Sons, Hoboken.
2.
Anderson, J.D.1985. Introduction to Flight, 2nd edn, McGraw-Hill, Inc., New York .
3.
Bae, J.S., Seigler, T.M. and Inman, D.J.2005. ‘‘Aerodynamic and Static Aeroelastic Characteristics of a Variable-Span Morphing Wing,’’ Journal of Aircraft, 42:528-534.
4.
Blondeau, J.E. and Pines, D.J.2004. ‘‘Pneumatic Morphing Aspect Ratio Wing,’’ In: 45th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics & Materials Conference, 19-22 April, Palm Springs, CA, Paper No. AIAA2004-1808.
5.
Buseman, A.1935. ‘‘Aerodynamic Lift at Supersonic Speeds,’’Ae. Techl. 1201, Report No. 2844 (British ARC, February 3, 1937), Bd. 12, Nr. 6, October, pp. 210-220.
6.
Bye, D.R. and McClure, P.D.2007. ‘‘Design of a Morphing Vehicle,’’ In: 48th AIAA Structures, Structural Dynamics, and Materials Conference, 23-26 April, Honolulu, HI, Paper No. AIAA2007-1728.
7.
Chaves, F.D., Avila, J. and Avila, A.F.2003. ‘‘A Morphological Study on Cellular Composites with Negative Poisson’s Ratios,’’ In: Proceedings of 44th AIAA Structures, Structural Dynamics, and Materials Conference , 7-10 April, Norfolk, VA, Paper No. AIAA2003-1951.
8.
Flanagan, J., Strutzenberg, R., Myers, R. and Rodrian, J.2007. ‘‘Development and Flight Testing of a Morphing Aircraft, the NextGen MFX-1,’’ In: Proceedings of 48th AIAA Structures, Structural Dynamics, and Materials Conference , 23-26 April, Honolulu, HI, Paper No. AIAA2007-1707.
9.
Gern, F.H., Inman, D.J. and Kapania, R.K.2002. ‘‘Structural and Aeroelastic Modeling of General Planform Wings with Morphing Airfoils,’’ AIAA Journal, 40:628-637.
Gibson, L.J. and Ashby, M.F.1988. Cellular Solids: Structure and Properties, Pergamon Press, Oxford.
12.
Henry, J.J.2005. ‘‘Roll Control for UAVs by Use of a Variable Span Morphing Wing,’’ Master’s Thesis, Department of Aerospace Engineering, University of Maryland, College Park, MD.
13.
Hetrick, J.A., Osborn, R.F., Kota, S., Flick, P.M. and Paul, D.B.2007. ‘‘Flight Testing of Mission Adaptive Compliant Wing,’’ In: Proceedings of 48th AIAA Structures, Structural Dynamics, and Materials Conference, 23-26 April, Honolulu, HI, Paper No. AIAA2007-1709.
14.
Kikuta, M.T.2003. ‘‘Mechanical Properties of Candidate Materials for Morphing Wings,’’ MS Thesis, Virginia Polytechnic Institute and State University, Blacksburg, VA.
15.
Munk, M.M.1924. ‘‘Note on the relative Effect of the Dihedral and the Sweep Back of Airplane Wings,’’NACA Technical Note177.
16.
Murray, G., Gandhi, F. and Bakis, C.2007. ‘‘Flexible Matrix Composite Skins for One-Dimensional Wing Morphing,’’ In: Proceedings of 48th AIAA Structures, Structural Dynamics, and Materials Conference , 23-26 April, Honolulu, HI, Paper No. AIAA2007-1737.
17.
Olympio, K.R.2006. ‘‘Design of a Passive Flexible Skin for Morphing Aircraft Structures,’’ MS Thesis, Pennsylvania State University.
18.
Olympio, K. and Gandhi, F.2007. ‘‘Zero-ν Cellular Honeycomb Flexible Skins of One-dimensional Wing Morphing,’’ In: Proceedings of 48th AIAA Structures, Structural Dynamics, and Materials Conference , 23-26 April, Honolulu, HI, Paper No. AIAA2007-1735.
19.
Parker, H.J.1920. ‘‘The Parker Variable Camber Wing,’’ Report #77 Fifth Annual Report, National Advisory Committee for Aeronautics, Washington, DC.
20.
Perkins, D.A., Reed, J.L. and Havens, E.2004. ‘‘Morphing Wing Structures for Loitering Air Vehicles,’’ In: 45th AIAA Structures, Structural Dynamics & Materials Conference, 19-22 April, Palm Springs, CA, Paper No. AIAA2004-1888.
Shigley, J., Mishke, C. and Budynas, R.2004. Mechanical Engineering Design, McGraw-Hill , New York.
23.
Thill, C., Etches, J., Bond, I., Potter, K. and Weaver, P.2008. ‘‘Morphing Skins,’’ The Aeronautical Journal, 112:117-139.
24.
Toensmeier, P.A.2005. Morphing Aircraft Could Bring Multi-Role Capability to Next Generation Aircraft, Aviation Weekly, May, pp. 72-73.
25.
Wereley, N.M. and Kothera, C.S.2007. ‘‘Morphing Aircraft Using Fluidic Artificial Muscles,’’ In: Proceedings of the International Conference on Adaptive Structures and Technologies, 2-5 October, Ottawa, ON, Paper ID 171.
