This investigation targeted the development of flexible materials that when combined with mechanized structures can enable large rigid body deformations of aircraft structures while maintaining its aerodynamic shape. The solution presented in this work focuses on determining the distribution of material properties to design such a skin using topology optimization techniques. The matrix material selected in this research is a representative Shape Memory Polymer (SMP), which is embedded with a reinforcing fiber. The fiber plays a dual role in that in addition to serving as a reinforcing element it also provides the means to activate the material response (e.g., changing cross link density) via resistive heating. In depth heat transfer analysis and experiments were conducted to understand power requirements and minimum spacing of the fibers to activate the desired material response.

1.
TA Instruments ARES - RDA. 2005. TA Instruments. 24 May 2006 <http://www.tainstruments.com/product.asp?n=1&id=32>.
2.
Veriflex(R). 2006. CRG Industries, LLC. 24 May 2006 <http://www.crg-industries.com/veriflex.htm>.
3.
Bortolin, Robert Sebastian. “Characterization of Shape Memory Polymers for use as a Morphing Aircraft Skin Material.” (2005).
4.
DeCamp, Ronald W., Richard Hardy, Douglas K. Gould, “Mission-Adaptive Wing.” SAE International Pacific Air and Space Technology Conference, Melbourne, Australia, 1987.
5.
Dunne, J., D. Pitt, E. White, E. Garcia, 2000. “Ground Demonstration of the Smart Inlet.” AIAA 41st Structures, Structural Dynamics, and Materials Conference, Atlanta, Georgia, April 2000
6.
Hudson, Alvin & Rex Nelson., University Physics. New York: Harcourt Brace Jovanovich, Inc., 1982.
7.
Incropera, Frank P. and David P. DeWitt., Fundamentals of Heat and Mass Transfer.: John Wiley & Sons, Inc., 2002.
8.
Kudva
J. N.
Overview of the DARPA/AFRL/NASA Smart Wing Phase 2 Program
.”
Journal of Intelligent Material Systems and Structures
15
(
2004
):
261
267
.
9.
Ozlslk, M. Necati. Heat Conduction: Second Edition. New York: John Wiley & Sons, Inc., 1993.
10.
Perkins, David A., et al. “Morphing Wing Structures for Loitering Air Vehicles.” 45th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics & Materials Conference (2004).
11.
Sepe, M.P. (1998). Dynamic Mechanical Analysis for Plastics Engineering. William Andrew Publishing/Plastics Design Library. Online version available at: http://www.knovel.com/knovel2/Toc.jsp?BookID=380 & VerticalID=0
12.
Toensmeier, P.A., “Morphing Aircraft Could Bring Multi-Role Capability to Next Generation Aircraft, Aviation Week, May 2005, pg 72–73
This content is only available via PDF.
You do not currently have access to this content.