| 摘要 |
A frame of a door that is provided at an opening made in a fuselage of an aircraft that is delimited by a skin, whereby the frame that includes an upper longitudinal stiffener and a lower longitudinal stiffener provides the connection between two vertical substructures (62) that are arranged on both sides of the opening, at the level of which (5) there is provided at least one stop (56) that provides the uptake of radial forces exerted by the door, characterized in that each vertical substructure (62) includes at least three walls made of composite material that are connected to one another to form a closed and hollow profile in such a way as to obtain a box structure.
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