Patent ID: 8418963

Claim:
An aircraft load frame ( 1 ) made of a composite material, comprising two side elements ( 2 , 3 ) and a base element ( 7 ), the side elements ( 2 , 3 ) being joined at an inner part of the frame ( 1 ) by the base element ( 7 ) and each of the side elements ( 2 , 3 ) comprising a leg ( 4 ), a web ( 5 ), and a lower flange ( 6 ) joining the web ( 5 ) and the base element ( 7 ), wherein the base element ( 7 ) is formed by layers of unidirectional tape, stacked with different orientations, such tapes being predominantly in a longitudinal direction and extending continuously along the frame ( 1 ) such that the base element ( 7 ) has a high modulus of elasticity in the longitudinal direction, the leg ( 4 ) and the inner flange ( 6 ) each have unidirectional fiber reinforcements ( 20 , 21 ) at 0° with respect to the longitudinal direction of the leg ( 4 ) and the inner flange ( 6 ), respectively, the unidirectional fiber reinforcements ( 20 , 21 ) longitudinally extending along the frame ( 1 ) continuously, and the web ( 5 ) has continuous or local reinforcements ( 22 ) in any direction.