复合材料非对称正交层合薄壳固化变形研究

ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 1996, Vol. 17 ›› Issue (S1): 129-131.

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RESEARCH ON THE CURED SHAPE OF CROSS PLY UNSYMMETRIC COMPOSITE LAMINATED SHELL

Ren Libo¹, Luo Xiaodong¹, Cui Degang²

1. Institute of Aircraft Design,Beijing University of Aeronautics and Astronautics, Beijing, 100083;2. Science and Technology Bureau, AVIC, Beijing, 100712

Received:1996-01-25 Revised:1996-04-25 Online:1996-11-25 Published:1996-11-25

Abstract

Abstract: An analytical model is established by means of Ritz method to calculate the cured shape of cross ply unsymmetric composite laminated shells.The influence of stacking sequence on the cured shape of a composite shell is discussed. The result of calculation correlates well with the experimental result. These results all show that the bifurcation phenomenon, which is very common in composite laminates, does not exist in composite shells. The conclusion is instructive to manufacture of composite laminated shells.

Key words: composite material, Ritz method bifurcation, thin shell

CLC Number:

V21418 V21413

Ren Libo;Luo Xiaodong;Cui Degang. RESEARCH ON THE CURED SHAPE OF CROSS PLY UNSYMMETRIC COMPOSITE LAMINATED SHELL[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1996, 17(S1): 129-131.

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RESEARCH ON THE CURED SHAPE OF CROSS PLY UNSYMMETRIC COMPOSITE LAMINATED SHELL

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