US 12,404,003 B2
CFRP fuselage frame with securement to vertical tail fin
Paul Diep, Bothell, WA (US); and Phiyen T. Pham, Lynnwood, WA (US)
Assigned to The Boeing Company, Chicago, IL (US)
Filed by THE BOEING COMPANY, Chicago, IL (US)
Filed on Jun. 28, 2021, as Appl. No. 17/360,356.
Claims priority of provisional application 63/064,711, filed on Aug. 12, 2020.
Prior Publication US 2022/0048610 A1, Feb. 17, 2022
Int. Cl. B64C 1/26 (2006.01); B64C 1/00 (2006.01); B64C 1/06 (2006.01); B64F 5/10 (2017.01)
CPC B64C 1/26 (2013.01) [B64F 5/10 (2017.01); B64C 2001/0072 (2013.01); B64C 1/061 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A securement assembly for securing a vertical tail fin assembly to an aircraft, comprising:
a first lug member secured to the vertical tail fin assembly; and
a first clevis member, wherein:
a first end portion of the first clevis member is engaged to the first lug member; and
a second end portion of the first clevis member is secured to a first fuselage frame, wherein the first fuselage frame is constructed of a composite material, wherein the second end portion of the first clevis member overlaps part of the first fuselage frame in which a first fastener extends through the second end portion of the first clevis member and the first fuselage frame in a first direction transverse to the first fuselage frame, wherein the composite material comprises a five-ply configuration which includes:
one ply having a nonlinear fiber configuration;
two plies having a first linear fiber configuration which extends within an angular range which includes plus or minus five degrees of plus thirty degrees of angular displacement from a radial axis of the nonlinear fiber configuration; and
another two plies having a second linear fiber configuration which extends within an angular range which includes plus or minus five degrees of minus thirty degrees of angular displacement from the radial axis of the nonlinear fiber configuration.