Drilling of Thick Composite Structure: State of the Art

Document Number: 2006-01-3172

Date Published: September 2006

Author(s):
Pierre Rahme - Laboratoire de Genie Mecanique

Abstract:
Aeronautic structure parts are increasingly manufactured using long fiber composite materials. A modification of the assembly hole drilling process is necessary to adapt it to the specific qualities of these materials. At the entry and at the exit of the part, delaminations are generated by the use of a conventional twist drill. The delamination of the composite materials is related directly to the thrust force (F\dZ) of the tool. So, it is interesting to study the drilling of thick plates for the composite assemblies. In this paper, several types of tools will be examined and an analytic model will be developed for the calculation of the critical thrust force (F\dZ) in drilling with a conventional twist drill. Finally, the present study can be used to choose the optimal tool that provokes the minimum of delamination in composite materials drilling.

File Size: 333K
Product Status: In Stock

See other papers presented at Aerospace Manufacturing and Automated Fastening Conference and Exhibition, September 2006, Toulouse, FRANC, Session: Advanced Forming, Machining and Modeling Part 2 of 2

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