PROBLEM TO BE SOLVED: To provide an improved composite structural member and an improved aircraft fuselage, which eliminate circumferential splices in the most highly loaded section of the fuselage, eliminate keel splice components, provide concentrated stiffness and strength where needed, decrease aircraft weight, and simplify fuselage assembly.SOLUTION: A structural member cores 208, 308 include alternating layers of boron fiber reinforced plies 202, 302a-302c, 206a-206d, 306a-306j and interior carbon fiber reinforced plies 204a-204c, 304a-304c. The boron fiber reinforced plies are oriented in a longitudinal direction, and the interior carbon fiber reinforced plies are oriented diagonally, perpendicularly and parallel to the boron fiber reinforced plies. A structural member casings 212, 312 include exterior carbon fiber reinforced plies that substantially totally surround structural member cores 208, 308.SELECTED DRAWING: None
【課題】胴体の最も荷重の大きいセクションの周方向スプライス(繋ぎ板)を無くし、キール(機体下面)スプライス部品を無くし、必要な箇所の剛性及び強度を集中させることができ、航空機重量を軽くし、そして胴体アセンブリを簡易にする改良型複合材構造部材、及び改良型航空機胴体を提供する。【解決手段】ホウ素繊維強化プライ202,302a〜302c,206a〜206d,306a〜306j及び内部炭素繊維強化プライ204a〜204c,304a〜304cを交互に重ねた層を含む構造部材コア208,308。ホウ素繊維強化プライは前後方向に向いており、そして内部炭素繊維強化プライは、ホウ素繊維強化プライに対して対角方向に、直交方向に、そして平行に向いている。構造部材ケーシング212,312は、構造部材コア208,308の全体を略取り囲む外部炭素繊維強化プライを含む。【選択図】なし
BORON FIBER REINFORCED STRUCTURAL COMPONENTS
ホウ素繊維強化構造部品
2017-11-24
Patent
Elektronische Ressource
Japanisch
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