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Modelling and vibration of a non-classical tilt-rotor wing system

Published online by Cambridge University Press:  03 February 2016

O. Song ,
H. D. Kwon  and
L. Librescu
O. Song
Affiliation:
Department of Mechanical Engineering, Chungnam National University, Daejeon, South Korea
H. D. Kwon
Affiliation:
Department of Mechanical Engineering, Chungnam National University, Daejeon, South Korea
L. Librescu
Affiliation:
Department of Engineering Science and Mechanics, Virginia Polytechnic Institute and State University, Blacksburg, USA
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Abstract

Problems related with the mathematical modelling and eigenvibration of a tiltrotor aircraft-wing system built up of anisotropic composite materials are investigated. The wing-mounted rotor that can tilt from the vertical position to a horizontal one is modelled and analysed from the vibrational point of view. In this sense, its behaviour is analysed as a function of the mass size, mass moment of inertia, tilt angle and spin speed of the spinning rotor and of its location along the wing span. While the rotor is considered to be rigid, the aircraft wing is modelled as a thin-walled beam that features a doubly-symmetric cross-section contour and incorporates the elastic coupling between flap-lag-transverse shear, on one hand, and between extension-twist, on the other hand. Numerical simulations are provided and pertinent conclusions are outlined.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1119 , May 2007 , pp. 285 - 295
Copyright
Copyright © Royal Aeronautical Society 2007 

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References

1. Miller, D.G., Black, T.M. and Joglekar, M., Tilt rotor control law design for rotor loads alleviation using modern control techniques, American Control Conference, 1991, 3, pp 2488–2495.Google Scholar
2. Manimala, B., Padfield, G.D., Walker, D.J., Naddei, M., Verde, L., Ciniglio, U., Rollet, P. and Sandri, F., Load alleviation in tilt rotor aircraft through active control; modelling and control concepts, Aeronaut J, 2004, 108, (1082), pp 169–184.Google Scholar
3. Johnson, W., Optimum control alleviation of tilting proprotor gust response, J Aircr, March 1977, 14, (3), pp 301–308.Google Scholar
4. Johnson, W., Benton, H. and Bowles, J.V., Calculated performance, stability, and maneuverability of high speed tilting proprotor aircraft, Vertica, 1987, 11, Nos ½, pp 317–339.Google Scholar
5. Bauchau, O.A., Loewy, R.G. and Bryan, P.S., An approach to ideal twist distribution in tilt rotor VTOL blade designs, Resnesselaer Polytechnic Institute, RTC Report No D-86-2, 1986.Google Scholar
6. Lake, R.C., Nixon, M.W., Wilbur, M.L., Singleton, J.D. and Mirick, P.H., Demonstration of an elastically coupled twist control concept for tilt rotor blade application, AIAA J, 1994, 32, (7), pp 1549–1551.Google Scholar
7. Kvaternik, R.G., A review of some tilt-rotor aeroelastic research at NASA-Langley, J Aircr, May 1976, 13, (5), pp 357–363.Google Scholar
8. Nasu, K., Tilt-rotor flutter control in cruise flight, NASA TM 88315, December 1986.Google Scholar
9. Nixon, M.W., Parametric studies for tiltrotor aeroelastic stability in high speed flight, J American Helicopter Society, October 1993, 38, (4).Google Scholar
10. Srinivas, V., Chopra, I. and Nixon, M.W., Aeroelastic analysis of advanced geometry tiltrotor aircraft, AIAA-95-1454-CR.Google Scholar
11. Nixon, M.W., Aeroelastic Response and Stability of Tiltrotors with Elastically Coupled Composite Rotor Blades, PhD Dissertation, University of Maryland, College Park, Maryland, USA. 1993.Google Scholar
12. Popelka, D., Lindsay, D., Parham, T. Jr., Berry, V. and Baker, D.J., Results of an aeroelastic tailoring study for a composite tiltrotor wing, J American Helicopter Society, 42, (2), April 1998, pp 133–145.Google Scholar
13. Barkai, S. and Rand, O., The influence of composite induced couplings on tiltrotor whirl-flutter stability, J American Helicopter Society, 43, (2), April 1998, pp 133–145.Google Scholar
14. Soykasap, O. and Hodges, D.H., Aeroelastic optimization of a composite tilt rotor, AIAA Paper 98-1919, April 1998.Google Scholar
15. Song, O. and Librescu, L., Free vibration of anisotropic composite thin-walled beams of closed cross-section contour, J Sound Vibration, 1993, 167, (1), pp 129–147.Google Scholar
16. Librescu, L., Meirovitch, L. and Song, O., Refined structural modelling for enhancing vibrational and aeroelastic characteristics of composite aircraft wings, La Recherche Aerospatiale, 1, pp 23–35, 1996.Google Scholar
17. Song, O., Kwon, H. and Librescu, L., Modelling, vibration, and stability of elastically tailored composite thin-walled beams carrying a spinning tip rotor, J Acoust Soc Am, 2001, 110, (2), pp 877–886.Google Scholar
18. Librescu, L. and Song, O., Thin-Walled Composite Beams: Theory and Application, Springer, 2006.Google Scholar
19. Hughes, P.C., Spacecraft Attitude Dynamics, Wiley, New York, USA, 1986.Google Scholar
20. Librescu, L., Elastostatics and Kinetics of Anisotropic and Heterogeneous Shell-Type Structures, Noordhoff Interanational Publ, Leyden, 1975.Google Scholar
21. Meirovitch, L., Principles and Techniques of Vibration, Prentice-Hall, 1997.Google Scholar
22. Song, O., Jeong, N.H. and Librescu, L., Implications of conservative and gyroscopic forces on vibration and stability of elastically tailored rotating shaft modelled as composite thin-walled beams, J Acoustical Society of America, 2001, 109, (3), pp 972–981.Google Scholar