| 主权项 |
1. An aircraft frame comprising:
a first partial aircraft frame configured to be attached to a first aircraft fuselage segment; and a second partial aircraft frame configured to be attached to a second aircraft fuselage segment, the first partial aircraft frame and the second partial aircraft frame configured to be connected to each other to be in a connected configuration, and the first partial aircraft frame and the second partial aircraft frame are configured to establish the connected configuration such that the first fuselage segment and the second fuselage segment are connectable; wherein the first partial aircraft frame and the second partial aircraft frame are configured to form the aircraft frame in the connected configuration; wherein the first partial aircraft frame comprises a first stringer coupling section, and the second partial aircraft frame comprises a second stringer coupling section; wherein the first stringer coupling section is integrally formed within the first partial aircraft frame and the second stringer coupling section is integrally formed within the second partial aircraft frame; wherein the first stringer coupling section is configured to receive and engage with a first stringer of the first aircraft fuselage segment and to receive longitudinal loads from the first stringer attached to the first stringer coupling section; wherein the second stringer coupling section is configured to receive and engage with a second stringer of the second aircraft fuselage segment and to receive longitudinal loads from the second stringer attached to the second stringer coupling section; wherein the first partial aircraft frame comprises a first outer flange, a first web, and a first inner flange defining a first section of the first partial aircraft frame, and the second partial aircraft frame comprises a second outer flange, a second web, and a second inner flange defining a second section of the second partial aircraft frame; wherein the first partial aircraft frame and the second partial aircraft frame are configured to be attached to each other via the first web and the second web; wherein the first stringer coupling section is located between the first inner flange and the first outer flange and the second stringer coupling section is located between the second inner flange and the second outer flange; and wherein the first stringer coupling section comprises a first wall which extends from the first web into the first section of the first partial aircraft frame, and the second stringer coupling section comprises a second wall, which extends from the second web into the second section of the second partial aircraft frame. |
