A generic framework for morphing wing aeroelastic analysis and design is presented. The wing is discretised into an arbitrary number of wing segments. Two types of actuation mechanisms are identified: inter-rib mechanisms operating across a wing segment and intra-rib mechanisms acting between two adjacent wing segments. Virtually, any shape can be obtained by distributing four morphing modes over the entire morphing wing. Three are an intra-rib mechanism and one is an inter-rib mechanism. The intra-rib modes are wing shear, twist and extension, and the inter-rib mode is wing folding. The wing is modeled using a close coupling between a non-linear beam formulation and Weissinger aerodynamics. The framework is intended to aid quick preliminary design of morphing wings to trade-off contradictory requirements in a flight mission. The morphing wing can be optimized for discrete points in the flight mission, and for the entire flight mission. The framework can be used to predict aerodynamic performance, load distribution, aeroelastic deformations, and the required actuation forces and moments and corresponding actuation energy. Therefore, the performance gains of wing morphing can be weighed against the energy costs and weight penalties due to the presence of the actuators. The functionality of the framework is demonstrated by making use of a folding and sweeping wing test case.
Agte, J., Borer, N. and de Weck, O.2010. ‘‘A Simulation-Based Design Model for Analysis and Optimization of Multi-State Aircraft Performance,’’ In: Proceedings of the 51st AIAA/ ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Orlando, FL, 12-15 April.
2.
Battini, J.-M. and Pacoste, C.2002. ‘‘Co-rotational Beam Elements with Warping Effects in Instability Problems,’’ Computer Methods in Applied Mechanics and Engineering, 191:1755-1789.
3.
Bisplinghoff, R., Ashley, H. and Halfman, R.L.1996. Aeroelasticity, Dover Publications, Inc., New York.
4.
Bonnema, K.L. and Lokos, W.A.1989. ‘‘AFTI/F-111 Mission Adaptive Wing Flight Test Instrumentation Overview,’’ In: Instrumentation in the Aerospace Industry, Proceedings of the ISA Aerospace Instrumentation Symposium, Vol. 35, pp. 809-840.
5.
Culick, F.E.C.2003. ‘‘The Wright Brothers: First Aeronautical Engineers and Test Pilots,’’ AIAA Journal, 41:985-1006.
6.
De Breuker, R., Abdalla, M.M. and Gurdal, Z.2007. ‘‘Energy-Based Aeroelastic Optimisation of a Morphing Wing,’’ In: Proceedings of the 2nd European Conference for Aerospace Sciences, Brussels, Belgium, 1-6 June.
Frommer, J.B. and Crossley, W.A.2005. ‘‘Enabling Continuous Optimization for Sizing Morphing Aircraft Concepts,’’ In: Proceedings of the 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, 10-13 January.
9.
Gern, F.H., Inman, D.J. and Kapania, R.K.2005. ‘‘Computation of Actuation Power Requirements for Smart Wings with Morphing Airfoils,’’ AIAA Journal, 43:2481-2486.
10.
Gomes, A. and Suleman, A.2005. ‘‘Optimization of Aircraft Aeroelastic Response using the Spectral Level Set Method,’’ In: Proceedings of the 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Austin, TX, 18-21 April.
11.
Henderson, J.A.2002. ‘‘Global Optimization Methods for Aeroservoelastic Concepts,’’ In: Proceedings of the 43rd AIAA/ ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Denver, CO, 22-25 April.
12.
Kobayashi, M. and Pedro, H.T.C.2009. ‘‘On a Cellular Division Model for Topology Optimization,’’ In: Proceedings of the 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Palm Springs, CA, 4-7 May.
13.
Lee, D.H. and Weisshaar, T.A.2005. ‘‘Aeroelastic Studies on a Folding Wing Configuration,’’ In: Proceedings of the 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference.
14.
Love, M.H., Zink, P.S., Stroud, R.L., Bye, D.R. and Chase, C.2004. ‘‘Impact of Actuation Concepts on Morphing Aircraft Structures,’’ In: Proceedings of the 45th AIAA/ASME/ASCE/ AHS/ASC Structures, Structural Dynamics and Materials Conference, Palm Springs, CA, 19-22 April.
15.
Martin, E. and Crossley, W.2002. ‘‘Multiobjective Aircraft Design to Investigate Potential Geometric Morphing Features,’’ In: Proceedings of the AIAA Annual Aviation Technology Integration, and Operations (ATIO) Technical Forum, Los Angeles, CA, 1-3 October.
16.
Maute, K. and Reich, G.W.2006. ‘‘Integrated Multidisciplinary Topology Optimization Approach to Adaptive Wing Design,’’ Journal of Aircraft, 43:253-263.
17.
McGowan, A.-M.R.2008. ‘‘Overview: Morphing Activities in the USA,’’Advanced Course on Morphing Aircraft, Materials, Mechanisms and Systems Presentation, Lisbon, Portugal, 17-20 November.
18.
McGowan, A.-M.R., Horta, L.G., Harrison, S. and Raney, D.L.1999. ‘‘Research Activities within NASA’s Morphing Program,’’ In: Research and Technology Agency.
19.
McGowan, A.-M.R., Washburn, A.E., Horta, G., Bryant, R.G., Cox, E., David, E., Siochi, E.J., Sharon, P.L. and Holloway, N.M.2002. ‘‘Recent results from NASA’s Morphing Project,’’ In: Proceedings of the SPIE Conference on Smart Structures and Materials, Vol. 4698, pp. 97-111, San Diego, CA.
20.
Namgoong, H., Crossley, W.A. and Lyrintzis, A.S.2007. ‘‘Aerodynamic Optimization of a Morphing Airfoil Using Energy as an Objective,’’ AIAA Journal, 45:2113-2124.
21.
Padula, S., Rogers, J. and Raney, D.2000. ‘‘Multidisciplinary Techniques and Novel Aircraft Control Systems,’’ In: Proceedings of the 8th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and OptimizationLong Beach, CA, 6-8 September.
22.
Patil, M. and Hodges, D.2000. ‘‘On the Importance of Aerodynamic and Structural Geometrical Nonlinearities in Aeroelastic Behavior of High-Aspect-Ratio Wings,’’ In: Proceedings of the 41st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Atlatna, GA, 3-6 April.
23.
Pendleton, E., Griffin, K.E., Kehoe, M.W. and Perry, B.1996. ‘‘A Flight Research Program for Active Aeroelastic Wing Technology,’’ In: Proceedings of the 37th AIAA/ASME/ASCE/ AHS/ASC Structures, Structural Dynamics and Materials Conference, Salt Lake City, UT, 15-17 April.
24.
PerryIII, B. , Cole, S.R. and Miller, G.D.1992. ‘‘A Summary of the Active Flexible Wing Program,’’NASA Technical Memorandum, NASA/TM-1992-107655.
25.
Prandtl, L.1923. ‘‘Applications of Modern Hydrodynamics to Aeronautics,’’ Technical report 116, NACA.
26.
Raymer, D.2001. ‘‘Vehicle Scaling Laws for Multidisciplinary Optimization,’’ In: Proceedings of the 39th AIAA Aerospace Sciences MeetingSylmar, CA, 8-11 January.
27.
Ricci, S. and Terraneo, M.2006. ‘‘Application of MDO Techniques to the Preliminary Design of Morphed Aircraft,’’ In: Proceedings of the 11th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Portsmouth, VA, 6-8 September.
28.
Sanders, B., Crowe, R. and Garcia, E.2004. ‘‘Defense Advanced Research Projects Agency-Smart Materials and Structures Demonstration Program Overview,’’ Journal of Intelligent Material Systems and Structures, 15:227-233.
29.
Skillen, M.D. and Crossley, W.A.2008. ‘‘Conceptual Morphing Aircraft Sizing Using a Multi-level Optimization Strategy,’’ In: Proceedings of the 46th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, 7-10 January.
Weisshaar, T.2006. ‘‘Morphing Aircraft Technology - New Shapes for Aircraft Design,’’ Technical report RTO-MP-AVT-141, NATO.
32.
Weissinger, J.1947. ‘‘The Lift Distribution of Swept-Back Wings,’’ Technical Memorandum 1120, NACA.
33.
Willaert, M. and Abdalla, M.2010. ‘‘A Simple Finite Element Cross-Sectional Modelling of Thin-Walled Beams,’’ In: Proceedings of the 2nd Aircraft Structural Design Conference, London, UK, 26-28 October.
34.
Wilson, J.R.2004. ‘‘Morphing UAVs Change the Shape of Warfare ,’’ Aerospace America, 42:28-29.
