An aircraft frame comprising: a first partial aircraft frame configured to be attached to a first aircraft fuselage segment; a second partial aircraft frame configured to be attached to a second aircraft fuselage segment; 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; wherein 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 further comprises a first stringer coupling section configured to receive and engage with a first stringer of the first aircraft fuselage segment; wherein the first stringer coupling section is located between the first inner flange and the first outer flange; wherein the second partial aircraft frame further comprises a second stringer coupling section configured to receive and engage with a second stringer of the second aircraft fuselage segment; wherein the second stringer coupling section is located between the second inner flange and the second outer flange; wherein the first partial aircraft frame and the second partial aircraft frame are configured to be connected to each other via the first web and the second web to be in a connected configuration; wherein 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; and wherein the first partial aircraft frame and the second partial aircraft frame are configured to form the aircraft frame in the connected configuration. a first partial aircraft frame configured to be attached to a first aircraft fuselage segment; a second partial aircraft frame configured to be attached to a second aircraft fuselage segment; 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; wherein 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 further comprises a first stringer coupling section configured to receive and engage with a first stringer of the first aircraft fuselage segment; wherein the first stringer coupling section is located between the first inner flange and the first outer flange; wherein the second partial aircraft frame further comprises a second stringer coupling section configured to receive and engage with a second stringer of the second aircraft fuselage segment; wherein the second stringer coupling section is located between the second inner flange and the second outer flange; wherein the first partial aircraft frame and the second partial aircraft frame are configured to be connected to each other via the first web and the second web to be in a connected configuration; wherein 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; and wherein the first partial aircraft frame and the second partial aircraft frame are configured to form the aircraft frame in the connected configuration.