高強度GFRP製ヘリコプタ・ロータ系統部品の許容欠陥の評価

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The allowable defect size for a helicopter rotor hub made of high strength glass fiber reinforced plastic (GFRP) was evaluated based on the damage tolerant design method. The threshold values of the energy release rate range, ΔG_<th>, for fatigue crack propagation were established under the pure and mixed modes of I, II and III for GFRP. An initial delamination crack was located at various positions in rotor hub. The energy release rate range, ΔG, was calculated for each position using the finite element method. The allowable defect size was determined from the threshold values and the energy release rate range, ΔG. The maximum energy release rate ranges of mode II and III, ΔG_<II>・nd ΔG_<III>, for an internal elliptic crack were generated at the crack front edge in the centrifugal direction, and in the perpendicular direction. The maximum value of ΔG_<II>, is large than that of ΔG_<III>, but the threshold value of mode III, ΔG_<IIIth>, is smaller than that of mode II. This suggests that, for an internal elliptic crack, the energy release range at the crack front edge in the centrifugal direction is critical for damage tolerant design. The region where the allowable defect size was determined to be the smallest corresponded to the position that showed the peak shear stress in the absence of cracking, which, for the hub in this study, was the center of the plate thickness at the thickness change division.
社団法人日本機械学会の論文
2007-02-25

高強度GFRP製ヘリコプタ・ロータ系統部品の許容欠陥の評価

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