| 摘要 |
PROBLEM TO BE SOLVED: To provided a flex beam made optimum which satisfies the designing condition of the flex beam, and reduces the shearing stress between layers. SOLUTION: A pitch part PR of an optimum compound flex beam furnishes a core laminate 50 and face laminates 52. The core laminate 50 and the face laminates 52 decide 10 or more of aspect ratioes, and form chamfered end faces 54s. Each chamfered end face 54s forms the critical acute angleα. to the flap direction bending neutral axis XA, and decide side surface ends 54E provided at the vertical distance X from the flap direction bending neutral axis XA. The critical acute angleαis between about 14' and about 22 deg., and thn vertical distance X is about 12.5% to about 37.5% of the thickness size TPR of the pitch part PR. The helicopter body side transition part of the optimum compound flex beam includes the first and the second transition small areas.
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