Discussion on Session V

MR M.B. SNELL, Royal Aircraft Establishment,

Farnborough

In Paper 21, the testing of CFRP reinforced

light alloy specimens is described in paragraph

14 and a failed beam is shown in Fig. 8. Would

the Author give details of the maximum stresses

achieved in the CFRP reinforcement at failure.

What percentage of the ultimate material strength did the Authors of Paper 22 use as a local and overall buckling design value for the ship's panels and what detailed changes were they able to make as a result of the finite element analysis, or was it used more as a check on the initial design?