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A Tapered TRIM 6 Element for the Matrix Displacement Method

Published online by Cambridge University Press:  04 July 2016

J. H. Argyris
J. H. Argyris*
Affiliation:
Imperial College of Science and Technology, University of London Institut für Statik und Dynamik der Luft-und Raumfahrtkonstruktionen, Univershät Stuttgart
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Extract

The success achieved in wing analysis and related problems through the introduction of triangular elements with six nodal points and a prescribed linearly varying strain or stress, naturally raised demands for a further sophistication in the idealisation process by triangularisation. In this context a practically important extension is concerned with the influence of taper in the thickness. We reproduce in what follows the theory for the special case of linear type. The paper may be considered as a generalisation of notes 2 and 3 of this series. However, the analysis is here based on the non-dimensional homogeneous triangular co-ordinates introduced in note 5, which simplify the argument considerably. A significant broadening of the applicability of the new element will be given in notes 9 and 10.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 70 , Issue 671 , November 1966 , pp. 1040 - 1043
Copyright
Copyright © Royal Aeronautical Society 1966

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References

1.Argyris, J. H.Triangular Elements with Linearly Varying Strain for the Matrix Displacement Method. Journal of the Royal Aeronautical Society, p. 711, Vol. 69, October 1965.CrossRefGoogle Scholar
2.Argyris, J. H.Reinforced Fields of Triangular Elements with Linearly Varying Strain; Effect of Initial Strains. Journal of the Royal Aeronautical Society, p. 799, Vol. 69, November 1965.CrossRefGoogle Scholar
3.Argyris, J. H.Tetrahedra Elements with Linearly Varying Strain for the Matrix Displacement Method. Journal of the Royal Aeronautical Society, p. 877, Vol. 69, December 1965.CrossRefGoogle Scholar
4.Archer, J. S.Consistent Mass Matrix for Distributed Mass Systems. Proc. ASCE, Journal of the Structural Division, Vol. 89, pp. 161–178, August 1963.CrossRefGoogle Scholar
5.Argyris, J. H. Some Results on the Free-Free Oscilla tions of Aircraft Type Structures, Revue de la Société Française de Mécanique, No. 3, 1965.Google Scholar