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Distributed actuation concepts for a morphing aileron device

Part of: Smart Aircraft

Published online by Cambridge University Press:  07 June 2016

G. Amendola ,
I. Dimino ,
M. Magnifico  and
R. Pecora
G. Amendola*
Affiliation:
CIRA, The Italian Aerospace Research Centre, Smart Structures and Vibroacoustics Laboratory, Via Maiorise, Italy
I. Dimino
Affiliation:
CIRA, The Italian Aerospace Research Centre, Smart Structures and Vibroacoustics Laboratory, Via Maiorise, Italy
M. Magnifico
Affiliation:
University of Naples“Federico II” – Department of Industrial Engineering, Aerospace Division, Via Claudio, Naples, Italy
R. Pecora
Affiliation:
University of Naples“Federico II” – Department of Industrial Engineering, Aerospace Division, Via Claudio, Naples, Italy
*
[email protected]
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Abstract

The actuation mechanism is a crucial aspect in the design of morphing structures due to the very stringent requirements involving actuation torque, consumed power, and allowable size and weight.

In the framework of the CRIAQ MD0-505 project, novel design strategies are investigated to enable morphing of aeronautical structures. This paper deals with the design of a morphing aileron with the main focus on the actuation technology. The morphing aileron consists of segmented 'finger-like' ribs capable of changing the aerofoil camber in order to match target aerodynamic shapes. In this work, lightweight and compact actuation kinematics driven by electromechanical actuators are investigated to actuate the morphing device. An unshafted distributed servo-electromechanical actuation arrangement is employed to realise the transition from the baseline configuration to a set of target aerodynamic shapes by also withstanding the aerodynamics loads. Numerical investigations are detailed to identify the optimal actuation architecture matching as well as the system integratability and structural compactness.

Keywords

Actuation systemmorphing aileronnumerical model
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1231 , September 2016 , pp. 1365 - 1385
Copyright
Copyright © Royal Aeronautical Society 2016 

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References

REFERENCES

1. Kothera, C., Wereley, N.M. and Woods, B.K.S. Fluidic artificial muscle actuation system for trailing-edge flap, Patent US20110266391A1, 2011.Google Scholar
2. The Boeing Company, Control system incorporating structural feedback. Patent US4725020, 1988.Google Scholar
3. Dimino, I., Flauto, D., Diodati, G., Concilio, A. and Pecora, R. Actuation system design for a morphing wing trailing edge, Recent Patents on Mech Engineering, 2014, 7, pp 138–148.Google Scholar
4. Dimino, I., Flauto, D., Diodati, G., Schüller, M. and Gratias, A. Adaptive shape control architecture for morphing wings, 6th ECCOMAS Conference on Smart Structures and Materials, SMART2013, Politecnico di Torino, 24-26 June 2013.Google Scholar
5. Hetrick, J.A., Ervin, G.F. and Kota, S. Compliant structure design for varying surface contours, US Patent No. 8814101, 26 August 2014.Google Scholar
6. Kota, S. and Hetrick, J. Adaptive compliant wing and rotor system, US Patent No. 20060186269, 24 August 2006.Google Scholar
7. Iannuzzo, G., Riccio, M., Russo, S., Calvi, E., Pecora, R., Lecce, L., Barbarino, S., Concilio, A. and Ameduri, S. An actuator device based on a shape memory alloy, and a wing flap assembly fitted with such an actuator device, European Patent No. EP 2 147 856 B1, 12 October 2011.Google Scholar
8. Pecora, R., Iannuzzo, G., Riccio, M., Russo, S., Calvi, E., Lecce, L., Barbarino, S., Concilio, A. and Ameduri, S. Actuator device based on a shape memory alloy, and a wing flap assembly fitted with such an actuator device, US Patent No. 8348201 B2, 8 January 2013.Google Scholar
9. Wang, Q., Xu, Z. and Zhu, Q. Structural design of morphing trailing edge actuated by SMA, Frontiers of Mech Engineering, 2013, 8, (3), pp 268–275.Google Scholar
10. Friswell, M.I., Baker, D., Herencia, J.E., Mattioni, F. and Weaver, P.M. Compliant structures for morphing aircraft, Proceedings of the ICAST2006, Taipei, Taiwan, 16-19 October 2006.Google Scholar
11. Ameduri, S., Brindisi, A., Tiseo, B., Concilio, A. and Pecora, R. Optimization and integration of shape memory alloy (SMA)-based elastic actuators within a morphing flap architecture, J Intelligent Material Systems and Structures, 2012, 23, (4), pp 381–396.Google Scholar
12. Pecora, R., Barbarino, S., Concilio, A., Lecce, L. and Russo, S. Design and functional test of a morphing high-lift device for a regional aircraft, J Intelligent Material Systems and Structures, 2011, 22, pp 1005–1023.Google Scholar
13. Barbarino, S., Pecora, R., Lecce, L., Concilio, A., Ameduri, S. and De Rosa, L. Aerofoil structural morphing based on S.M.A. actuator series: numerical and experimental studies, J Intelligent Material Systems and Structures, 2011b, 22, pp 987–1003.Google Scholar
14. Pecora, R., Amoroso, F., Amendola, G. and Concilio, A. Validation of a smart structural concept for wing flap camber morphing, Smart Structures and Systems, 2014, 14, (4), pp 659–678.Google Scholar
15. Kammegne, M.J.T., Botez, M.R., Mamou, M., Mebarki, Y., Koreanschi, A., Gabor, O.S. and Grigorie, T.L. Experimental wind tunnel testing of a new multidisciplinary morphing wing model, Proceedings of the 18th International Conference on Mathematical Methods, Computational Techniques and Intelligent Systems (MAMECTIS 2016).Google Scholar
16. Diodati, G., Concilio, A., Ricci, S., De Gasperi, A., Huvelin, F., Dumont, A. and Godard, J. Estimated performances of an adaptive trailing edge device aimed at reducing fuel consumption on a medium-size aircraft, Proc. SPIE 8690, Industrial and Commercial Applications of Smart Structures Technologies, March 2013, San Diego, California, US.Google Scholar
17. Dimino, I., Concilio, A., Schueller, M. and Gratias, A. An adaptive control system for wing TE shape control, Proc. SPIE 8690, Industrial and Commercial Applications of Smart Structures Technologies, March 2013, San Diego, California, US, March 2013.Google Scholar
18. Bolonkin, A. and Gilyard, , , G.B. Estimated benefits of variable-geometry wing camber control for transport aircraft, NASA/TM-1999-206586, October 1999.Google Scholar
19. MSC-MD/NASTRAN® , Software Package, Ver. R3-2006, “Reference Manual”.Google Scholar
20. Iko Nippon Precision linear slide Catalogue. US Patent No. 5076715, 31 December 1991. http://www.ikont.eu.Google Scholar