COMPOSITE MATERIAL STRUCTURE, AND AIRCRAFT WING AND FUSELAGE PROVIDED THEREWITH
摘要
<p>Provided is a composite material structure that enables weight reduction, with consideration given to stress concentrations in areas around holes. A wing (1), which is the composite material structure, is a composite material made of fiber reinforced plastic extending in one direction and in which access holes (5) are formed. A lower outer plate (3) on the wing (1) is subjected to a tensile load in the longitudinal direction. The longitudinal tensile stiffness of peripheral regions (3a) of the access holes (5) is smaller than the longitudinal tensile stiffness of other regions (3b) surrounding the peripheral regions (3a).</p>
申请公布号
WO2012105691(A1)
申请公布日期
2012.08.09
申请号
WO2012JP52517
申请日期
2012.02.03
申请人
MITSUBISHI HEAVY INDUSTRIES, LTD.;TANAKA, YUYA;YOSHIDA, SHINICHI;TANAKA, HIDEAKI;SUZUKI, HIDEYUKI;ABE, TOSHIO;KASHIWAGI, MASAHIRO