Benefits and design challenges of adaptive structures for morphing aircraft

Aeronautical Journal

Volumn 110, Issue 1105, 2006, Pages 157-162

  Moorhouse, D ^a   Sanders, B ^a   Von Spakovsky, M ^b   Butt, J ^b  

^a AIR FORCE RESEARCH LABORATORY   (United States)

^b VIRGINIA POLYTECHNIC INSTITUTE AND STATE UNIVERSITY   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

CONTROL NONLINEARITIES; GEOMETRY; OPTIMIZATION; PRODUCT DESIGN; PRODUCT DEVELOPMENT; WINGS;

FLIGHT CONTROL DESIGN; MECHANISATION; MORPHING AIRCRAFTS; MORPHING WING GEOMETRY;

AIRCRAFT;

EID: 33645657019     PISSN: 00019240     EISSN: None     Source Type: Journal    
DOI: 10.1017/S0001924000001135     Document Type: Article

References (20)

1. FLICK, P.M., LOVE, M.H. and ZINK, P.S. The impact of active aeroelastic wing technology on conceptual aircraft design, Structural Aspects of Flexible Aircraft Control, 2000, RTO-MP-36 (Paper 10), Ottawa, Canada.
2. PENDLETON, E., BESSETTE, D., FIELD, P., MILLER, G. and GRIFFIN, K. The active aeroelastic wing flight research program, 1998, 39th AIAA/ASME/ASCE/AHS/ ASC Structures, Structural Dynamics and Materials Conference, April 1998.
3. MATTINGLY, J.D., HEISER, W.H. and PRATT, D.T. Aircraft Engine Design. 2002, AIAA Education Series, Washington, DC, USA.
4. BUTT, J. A Study of Morphing Wing Effectiveness in Fighter Aircraft using Exergy Analysis and Global Optimization Techniques, 2005, MSc thesis. Advisor: VON SPAKOVSKY, M.R., M.E. Dept, Virginia Polytechnic Institute and State University, Blacksburg, VA, USA.
5. BOWMAN, J., SANDERS, B. and Weisshaar, T. Identification of military morphing aircraft missions and morphing technology assessment, 2002, SPIE-4698-62. Smart Structures and Integrated Systems, SPIE Smart Materials and Structures Conference, San Diego, CA, USA.
6. MOORHOUSE, D.J. A proposed system-level multidisciplinary analysis technique based on exergy methods, AIAA J Aircr, January 2003, 40, (1).
7. BONNEMA, K. and SMITH, S. AFTI/F-111 Performance flight test summary, 1988, AIAA Paper 88-2118, AIAA Fourth Flight Test Conference, San Diego, CA, USA.
8. NORMAN, D.K., GANGSAAS, D. and HYNES, R.J. An integrated maneuver enhancement and gust alleviation mode for the AFTI/F-11 MAW aircraft. 1983, AIAA Paper 83-2217, AIAA Guidance and Control Conference, August 1983, Gatlinburg, TN, USA.
9. KUDVA, J.N., MARTIN, C., SCHERER, L., JARDINE, A., MCGOWEN, A., LAKE, R., SENDECKYJ, G. and SANDERS, B. Overview of the DARPA/AFRL/NASA smart wing program, 1998, SPIE Conference on Industrial and Commercial Applications of Smart Structures Technologies, SPIE 3674.
10. FRANK, G.J., JOO, J.J., SANDERS, B.M., GARNER, D.M. and MURRAY, A.P. Mechanization of a high aspect ratio wing for aerodynamic control, 2004, International Conference on Adaptive Structures. October 2004, Bar Harbor, ME.
11. DUNNE, J., PITT, D., WHITF, E. and GARCIA., E. Ground demonstration of the smart inlet, 2000, 41st Structures, Structural Dynamics and Materials Conference, 3-6 April 2000, Atlanta, GA.
12. JOO, J., SANDERS, B. and FORSTER, E. Design of aerospace structures using a distributed energy approach, 2002, 13th International Conference on Adaptive Structures and Technologies. October 2002, Potsdam. Germany.
13. JOO, J., SANDERS, B., WASHINGTON, G. and ADAMS, J. Energy based efficiency of mechanized solid-state actuators, 2003, SPIE 10th Annual International Symposium on Smart Structures and Materials, 2-6 March 2003, San Diego, CA.
14. BLAIR, M., ROBERTS, R.W. and CANFIELD, R.A. Joined-wing aeroelastic design with geometric non-linearity, 2003, International Forum on Aeroelasticity and Structural Dynamics (IFASD). June 2003, Amsterdam, The Netherlands.
15. NORTON, W.J. Balancing modelling and simulation with flight test in military aircraft development, AGARD-CP-593, December 1997.
16. HOENLINGER, H., ZIMMERMANN, H., SENSBURG, O. and BECKER, J. Structural aspects of active control technology, AGARD-CP-560, January 1995.
17. SNYDFR, M.P., SANDERS, B., EASTEP, F.E. and FRANK, G.F. Sensitivity of flutter to fold orientation and spring stiffness of a simple folding wing, 2005, paper #IF-015, International Forum on Aeroelasticity and Structural Dynamics, June 2005.
18. JOHNSON, E., CALISE, A. and CORBAN, J. A six-degree-of-freedom adaptive flight control architecture for trajectory following, AIAA 2002-4776, August 2002.
19. CHANDLER, P., PACHTER, M. and SEARS, M. System identification for adaptive and reconfigurable control, AIAA J Guidance, Control and Dynamics, 1995, 18, (3).
20. ANON, Military Specification, Flying Qualities of Piloted Airplanes. MIL-F-8785C, November 1980.