Joint assembly and method of assembling same
AssigneeThe Boeing Company
InventorsSteven Paul Walker, Joanna Mara Sergiane Veit, Isaac G. Cambronero, Jr., James Donald Davis, Michael D. Pagliarini
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Abstract
A joint assembly for an aircraft is provided. The joint assembly includes a single main fitting including a first flange, a second flange, and a third flange, an external spar component coupled to the first flange using at least one fastener, an internal spar component coupled to the second flange using at least one fastener, and a body rib coupled to the third flange using at least one fastener.
Claims18
A joint assembly for an aircraft, said joint assembly comprising:
- a single main fitting comprising a first flange, a second flange, and a third flange, wherein said main fitting is elongate in a substantially vertical direction when positioned in the aircraft with a landing gear assembly contacting a substantially horizontal ground surface;
- an external spar component coupled to said first flange;
- an internal spar component coupled to said second flange;
- a body rib coupled to said third flange, said body rib extending away from said third flange towards a front of the aircraft;
- and
- an intermediate fitting configured to directly couple said main fitting to the landing gear assembly.
A joint for an aircraft, said joint comprising a single main fitting that comprises:
- a first flange configured to couple said main fitting to an external spar component of the aircraft;
- a second flange configured to couple said main fitting to an internal spar component of the aircraft;
- a third flange configured to couple said main fitting to a body rib of the aircraft such that the body rib extends away from said third flange towards a front of the aircraft, wherein said main fitting is elongate in a substantially vertical direction when positioned in the aircraft with a landing gear assembly contacting a substantially horizontal ground surface;
- and
- an intermediate fitting configured to directly couple said main fitting to the landing gear assembly.
A method of assembling a joint assembly of an aircraft, said method comprising:
- coupling an external spar component of the aircraft to a first flange of a single main fitting;
- coupling an internal spar component of the aircraft to a second flange of the main fitting;
- coupling a body rib of the aircraft to a third flange of the main fitting such that the body rib extends away from the third flange towards a front of the aircraft, wherein said main fitting is elongate in a substantially vertical direction when positioned in the aircraft with a landing gear assembly contacting a substantially horizontal ground surface;
- and
- directly coupling the main fitting to a landing gear assembly of the aircraft using an intermediate fitting.
Dependencies are inferred from the claim text.