Single piece fuselage barrel
AssigneeThe Boeing Company
InventorsFrancis E. Andrews, Max U. Kismarton, William J. Koch, IV
Life of this patent
Estimating the term…
Abstract
In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.
Claims19
An aircraft fuselage nose section having a longitudinal axis, and comprising:
- a unitary circumferentially extending composite skin;
- a plurality of composite fiber stiffeners, each stiffener including at least one foot, at least one sidewall, and a cap;
- the at least one foot bonded to an interior circumference of the composite skin;
- each stiffener extending in a circumferential direction;
- said plurality of composite fiber stiffeners spaced orthogonally with respect to the longitudinal axis to define a spaced parallel array, each stiffener defining a continuous circumferential structural component of the nose section, the cap spaced apart from the skin;
- wherein the cap includes plies of carbon fibers that extend at an angle with respect to the circumferential direction;
- and
- wherein the cap further includes plies of glass fibers that extend orthogonally with respect to the longitudinal axis.
The aircraft fuselage nose section of claim 7, wherein the hat stiffener comprises a hat top connecting a pair of sidewalls, and wherein the cap is contained within the hat top.
A stringerless aircraft fuselage nose section having a longitudinal axis, and comprising:
- a unitary circumferentially extending composite skin;
- a plurality of composite fiber stiffeners, each stiffener including at least one foot, at least one sidewall, and a cap;
- the at least one foot bonded to an interior circumference of the composite skin;
- each stiffener extending in a circumferential direction;
- said plurality of composite fiber stiffeners spaced orthogonally with respect to the longitudinal axis to define a spaced parallel array, each stiffener defining a continuous circumferential structural component of the nose section, the cap spaced apart from the skin;
- wherein the cap includes plies of carbon fibers that extend at an angle with respect to the circumferential direction;
- wherein the cap further includes plies of glass fibers that extend orthogonally with respect to the longitudinal axis, and
- wherein the composite skin comprises a hybrid laminate.
A method of forming an aircraft fuselage nose section having a longitudinal axis;
- the method comprising the steps of:
- laying-up a unitary circumferentially extending composite skin;
- laying-up a plurality of composite fiber stiffeners, each stiffener including at least one foot, at least one sidewall, and a cap, with the at least one foot bonded to an interior circumference of the composite skin;
- forming each stiffener to extend in a circumferential direction;
- forming the plurality of composite fiber stiffeners orthogonally with respect to the longitudinal axis to define a spaced parallel array;
- forming each stiffener as a continuous circumferential structural component of the nose section,
- forming the cap to include plies of carbon fibers that extend at an angle with respect to the circumferential direction, and to include plies of glass fibers that extend orthogonally with respect to the longitudinal axis, and assuring that the cap is spaced apart from the skin;
- and
- co-curing the composite skin and the stiffeners to finish forming the aircraft fuselage nose section.
Dependencies are inferred from the claim text.