Design, fabrication and testing of a composite bracket for aerospace applications

Report (1997)
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Published Date

13-02-1997

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NLR Technical Publication 97068 L

Abstract

In this paper the results of a program, in which a composite bracket as replacement of a metal forging was developed, will be presented. The finite element method in combination with an optimization module was used to design the bracket. Compared to its metal counter part, the composite bracket demonstrated a weight reduction of 43%. Two composite brackets were fabricated by RTM. One bracket was loaded statically to 1.38 x Design Ultimate Load. The bracket did not fail at this load level.

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