| 摘要 |
The present invention relates to an aircraft load frame ( 1 ) made of a composite material, characterized in that it comprises two side elements ( 2, 3 ) and a base element ( 7 ), the side elements ( 2, 3 ) being joined at the inner part of the frame ( 1 ) by means of the base element ( 7 ) and each of the side elements ( 2, 3 ) comprising a leg ( 4 ) joining the frame ( 1 ) to the aircraft fuselage skin, a web ( 5 ) and a lower flange ( 6 ) joining the web ( 5 ) and the base element ( 7 ).
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