초록 ▼

A fuselage comprising a skin assembly including an outer, laminate skin bonded to an inner, aluminum doubler. The fuselage also includes a support structure comprising a plurality of longitudinal stringer members and a plurality of annular frame members that are attached to, and cooperate to support

A fuselage comprising a skin assembly including an outer, laminate skin bonded to an inner, aluminum doubler. The fuselage also includes a support structure comprising a plurality of longitudinal stringer members and a plurality of annular frame members that are attached to, and cooperate to support, the skin assembly. The aluminum doubler provides additional structural support for the fuselage, and in particular, for the outer laminate skin of the skin assembly. The additional structural strength added by the aluminum doubler allows the use of an improved range of fasteners, such as knife-edge, countersink rivets and further allows the use of the laminate layer even in areas with a large number of cutouts, such as the window track of the fuselage. The members of the support structure may interconnected via a plurality of integral flanges, which, when combined with the skin, provide improved structural strength for the entire fuselage.

대표청구항 ▼

A fuselage comprising a skin assembly including an outer, laminate skin bonded to an inner, aluminum doubler. The fuselage also includes a support structure comprising a plurality of longitudinal stringer members and a plurality of annular frame members that are attached to, and cooperate to support

A fuselage comprising a skin assembly including an outer, laminate skin bonded to an inner, aluminum doubler. The fuselage also includes a support structure comprising a plurality of longitudinal stringer members and a plurality of annular frame members that are attached to, and cooperate to support, the skin assembly. The aluminum doubler provides additional structural support for the fuselage, and in particular, for the outer laminate skin of the skin assembly. The additional structural strength added by the aluminum doubler allows the use of an improved range of fasteners, such as knife-edge, countersink rivets and further allows the use of the laminate layer even in areas with a large number of cutouts, such as the window track of the fuselage. The members of the support structure may interconnected via a plurality of integral flanges, which, when combined with the skin, provide improved structural strength for the entire fuselage. T1≤Tmax≤(1+β)·SMT1 is satisfied, wherein SMT1 is said expected elapsed time, Tmax is said longest passage time, and β is a small tolerable error. 21. A code reading device as defined in claim 20, said information code is formed on an end surface of said winding core. 22. A code reading device as defined in claim 20, wherein said information code is formed on an inner surface of said winding core; further comprising: first and second holder bodies secured to respectively first and second ends of said winding core; first and second support shafts, disposed stationarily, for supporting respectively said first and second holder bodies in a rotatable manner; wherein said reading sensor is secured to said first support shaft. 23. A code reading device as defined in claim 14, wherein said information code is preprinted on said surface of said winding core. 24. A code reading device as defined in claim 14, wherein said recording material roll further comprises a code sticker previously provided with said information code, and secured to said surface of said winding core. 25. A code reading device as defined in claim 14, wherein a diameter of said recording material roll is changeable from a maximum diameter Dmax to a min