Hostname: page-component-6b989bf9dc-mbg9n Total loading time: 0 Render date: 2024-04-14T21:42:47.327Z Has data issue: false hasContentIssue false
  • English
  • Français

Benefits and design challenges of adaptive structures for morphing aircraft

Part of: Smart Aircraft

Published online by Cambridge University Press:  03 February 2016

D. Moorhouse ,
B. Sanders ,
M. von Spakovsky  and
J. Butt
D. Moorhouse
Affiliation:
US Air Force Research Laboratory, Wright-Patterson AFB, Ohio, USA
B. Sanders
Affiliation:
US Air Force Research Laboratory, Wright-Patterson AFB, Ohio, USA
M. von Spakovsky
Affiliation:
Virginia Polytechnic Institute and State University, Virginia, USA
J. Butt
Affiliation:
Virginia Polytechnic Institute and State University, Virginia, USA
Get access Rights & Permissions [Opens in a new window]

Abstract

The purpose of this paper is to discuss the future of adaptive structures leading towards the concept of a fully morphing aircraft configuration. First, examples are shown to illustrate the potential system-level mission benefits of morphing wing geometry. The challenges of design integration are discussed along with the question of how to address the optimisation of such a system. This leads to a suggestion that non-traditional methods need to be developed. It is suggested that an integrated approach to defining the work to be done and the energy to be used is the solution. This approach is introduced and then some challenges are examined in more detail. First, concepts of mechanisation are discussed as ways to achieve optimum geometries. Then there are discussions of non-linearities that could be important. Finally, the flight control design challenge is considered in terms of the rate of change of the morphing geometry. The paper concludes with recommendations for future work.

Type
Research Article
Information
The Aeronautical Journal , Volume 110 , Issue 1105 , March 2006 , pp. 157 - 162
Copyright
Copyright © Royal Aeronautical Society 2006 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

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.Google Scholar
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.Google Scholar
3. Mattingly, J.D., Heiser, W.H. and Pratt, D.T., Aircraft Engine Design, 2002, AIAA Education Series, Washington, DC, USA.Google Scholar
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.Google Scholar
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.Google Scholar
6. Moorhouse, D.J., A proposed system-level multidisciplinary analysis technique based on exergy methods, AIAA J Aircr, January 2003, 40, (1).Google Scholar
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.Google Scholar
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.Google Scholar
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.Google Scholar
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.Google Scholar
11. Dunne, J., Pitt, D., White, E. and Garcia, E., Ground demonstration of the smart inlet, 2000, 41st Structures, Structural Dynamics and Materials Conference, 3–6 April 2000, Atlanta, GA.Google Scholar
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.Google Scholar
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.Google Scholar
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.Google Scholar
15. Norton, W.J., Balancing modelling and simulation with flight test in military aircraft development, AGARD-CP-593, December 1997.Google Scholar
16. Hoenlinger, H., Zimmermann, H., Sensburg, O. and Becker, J., Structural aspects of active control technology, AGARD-CP-560, January 1995.Google Scholar
17. Snyder, 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.Google Scholar
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.Google Scholar
19. Chandler, P., Pachter, M. and Sears, M., System identification for adaptive and reconfigurable control, AIAA J Guidance, Control and Dynamics, 1995, 18, (3).Google Scholar
20. Anon, Military Specification, Flying Qualities of Piloted Airplanes, MIL-F-8785C, November 1980.Google Scholar