Patent ID: 9216810
Filing Date: 2015-12-22
Classification: B64C

Abstract:
1. A frame located at a tail fuselage section of an aircraft that receives external loads, the frame comprising: a first arcuate sector of a load frame, the first sector extending along an upper portion of a perimeter of said fuselage section, wherein said first sector of the load frame spans transversely to a longitudinal axis of said aircraft and along a cross-section of said fuselage section, and wherein the first sector is joined to a skin of said fuselage section, the first sector being configured to withstand the external loads received by said fuselage section; and a second arcuate sector of the load frame, the second sector extending along the remaining portion of the perimeter of said fuselage section, wherein said first sector includes the following structural elements: a) an upper foot piece joined to the skin of said fuselage section; b) a lower head piece; c) a web including one or more fitting-pieces that receive said external loads and a plurality of X-shaped pieces in the form of unitary sets, with each X-shaped piece comprising two rods of equal length joined at their midpoints and extending between the foot piece and the head piece, the X-shaped pieces being connected at their ends to said foot piece and said head piece; and d) two connecting pieces connecting ends of said foot piece and said head piece with the second sector of the load frame.