Modeling and Testing of a Seamless Wing Trailing Edge Control Actuation System

Abstract:

This paper presents an investigation into the modeling and analysis of an innovative actuation system for a wing with a seamless flexible trailing edge control surface. Research was started with the study of aerodynamic behavior and advantage of the wing in smooth variable chamber shape under control. Based on the concept and design, an experimental wing section integrated with the actuation mechanism was built and tested. The main effort was then made to the modeling of the internal actuation system for the purpose of obtaining the physical properties and accurate modeling of the whole wing structural system. To validate and update the numerical model of the system, vibration test of the actuation system including the mechanism and actuator was carried out. Some key parameters such as the stiffness of the actuation system were identified from vibration test data. The investigation demonstrated a practical approach to quantify some key parameters and update the numerical model of an actuation system.

• Periodical: Applied Mechanics and Materials (Volumes 195-196)
• Pages: 1089-1094
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.195-196.1089
• Online since: August 2012
• Authors: Yuan Yuan He, Li Liu
• Keywords: Actuation Mechanism, Actuation System, Flexible Trailing Edge Control Surface, Modeling Test, Seamless Wing, Vibration Test

References

[1] G. Andersen, E. Forster and R. Kolonay, Multiple control surface utilization in active aeroelastic wing technology, , Journal of Aircraft, vol. 34, no. 4, pp.552-557, July-Aug. (1997).

DOI: 10.2514/2.2208

[2] Ricci S. and Terraneo M., Conceptual design of an adaptive wing for a three-surfaces airplane, 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Austin, Texas, 18-21 April (2005).

DOI: 10.2514/6.2005-1959

[3] Jae-Sung, Seigler T. M., and Inman D. J., Aerodynamic and static aeroelastic characteristics of a variable-span morphing wing, Journal of Aircraft, vol. 42, no. 2, pp.528-534, (2005).

DOI: 10.2514/1.4397

[4] Forster E., Integrated structure/ actuation synthesis of strain actuated devices for shape control, 41st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Norfolk, Virginia, June (1999).

DOI: 10.2514/6.2005-2170

[5] Campanile L. F. and Anders S., Aerodynamic and aeroelastic amplification in adaptive belt-rib airfoils, Aerospace Science and Technology, Elsevier, vol. 9, Issue 1, pp.55-63, (2005).

DOI: 10.1016/j.ast.2004.07.007

[6] RicciS., ScottiA. andTerraneoM., Design, manufacture and preliminary test results of an adaptive wing camber model, 47thAIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, May (2006).

DOI: 10.2514/6.2006-2043

[7] Lt. Ben Boehm, Peter Flick. et al, Static aeroelastic response predictions of the active aeroelastic wing (AAW) flight research vehicle, 42nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, April (2000).

DOI: 10.2514/6.2001-1372

[8] M Perera, S Guo, Optimal design of a seamless aeroelastic wing structure, Proc. IMechE, Part G: J. Aerospace Eng. 223 (2009): 1141-1151. DOI: 10. 1243/09544100JERO493.

DOI: 10.1243/09544100jaero493

[9] M. Perera, Y. He and S. Guo, Structural and dynamic analysis of a seamless aeroelastic wing, the 51st AIAA/ ASME/ASCE /AHS/ASC Structures, Structural Dynamics, and Materials Conference, April (2010).

DOI: 10.2514/6.2010-2878

[10] R. Morishima, S. Guo and S. Ahmed, A composite wing with a morphing leading edge, the 51st AIAA/ ASME/ASCE /AHS/ASC Structures, Structural Dynamics, and Materials Conference, April (2010).

DOI: 10.2514/6.2010-3097

[11] N. Di Matteo, S. Guo, S. Ahmed, D. Li, Design and analysis of a morphing flap structure for high lift wing, the 51st AIAA/ ASME/ASCE /AHS/ASC Structures, Structural Dynamics, and Materials Conference, April (2010).

DOI: 10.2514/6.2010-3096