On the Dynamic Model of a Functionally Graded Spinning Structural Element of an Aircraft Appendage


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The use of advanced materials in automotive, aerospace and communication technologies has called for re-assessment of classical models of many structural elements. The primary objective of this study relates to the use of a higher-order continuum model for discerning the contribution of certain geometric and material properties on wave propagation behavior of a spinning appendage of an aircraft appendage. The spinning appendage is characterized by a through-thickness functional material gradation and subjected to an axial dead load. The foundation of the present model rests on the trio of the mechanics of functionally graded solid structures, the extended Hamilton’s principle and the thin beam theory. Numerical results from the wave mechanics analyses reveal the noticeable influence of axial dead load and attendant wave splitting effect caused by the gyroscopic moment of the system. The wave mechanics result paves the way for the non-destructive damage testing of the element.



Edited by:

R. Varatharajoo, F.I. Romli, K.A. Ahmad, D.L. Majid and F. Mustapha




K. B. Mustapha, "On the Dynamic Model of a Functionally Graded Spinning Structural Element of an Aircraft Appendage", Applied Mechanics and Materials, Vol. 629, pp. 89-94, 2014

Online since:

October 2014




* - Corresponding Author

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