Fiber-reinforced aircraft component and aircraft comprising same
OwnerMichael J. Klineinventor
Life of this patent
Estimating the term…
Abstract
An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.
Claims18
An aircraft component selected from the group consisting of an engine nacelle, a fuselage, and a nose cone, the aircraft component comprising an outer skin, the outer skin comprising a fore end region and an aft end region relative to an intended direction of travel of an aircraft comprising the aircraft component, the fore end region presenting a first angle of incidence, and the aft end region presenting a second angle of incidence, the first angle of incidence being more direct relative to the intended direction of travel than the second angle of incidence, wherein the fore end region of the outer skin comprises a first thickness relative to the intended direction of travel, and the aft end region of the outer skin comprises a second thickness relative to the intended direction of travel, and the first thickness is greater than the second thickness, and wherein the fore end region of the outer skin further comprises a first impact strength, and the aft region of the outer skin comprises a second impact strength, and the first impact strength is greater than the second impact strength, and wherein the outer skin further comprises a fiber-reinforced composite material.
An aircraft including an aircraft component comprising a wing, a tail section, an engine nacelle, an air inlet cowl, a windshield, an air inlet deflector, a fuselage or a nose cone, the aircraft component comprising an outer skin, the outer skin comprising a fore end region and an aft end region relative to an intended direction of travel of the aircraft, the fore end region presenting a first angle of incidence, and the aft end region presenting a second angle of incidence, the first angle of incidence being more direct relative to the intended direction of travel than the second angle of incidence, wherein the fore end region of the outer skin comprises a first thickness relative to the intended direction of travel, and the aft end region of the outer skin comprises a second thickness relative to the intended direction of travel, and the first thickness is greater than the second thickness, and wherein the fore end region of the outer skin comprises a first impact strength, and the aft end region of the outer skin comprises a second impact strength, and the first impact strength is greater than the second impact strength, and wherein the outer skin further comprises a fiber-reinforced composite material.
A method of fabricating an aircraft component comprising molding an outer skin of a wing, a tail section, an engine nacelle, an air inlet cowl, a windshield, an air inlet deflector, a fuselage, or a nose cone, the outer skin comprising a molded, unitary piece, the outer skin further comprising a fiber-reinforced composite material and a fore end region and an aft end region relative to an intended direction of an airstream impacting the outer skin, the fore end region presenting a first angle of incidence, and the aft end region presenting a second angle of incidence, the first angle of incidence being more direct relative to the intended direction of an airstream than the second angle of incidence, the method comprising molding the fore end region with a first impact strength, the fore end region of the outer skin comprising a first thickness relative to the intended direction of travel, and the aft end region of the outer skin comprises a second thickness relative to the intended direction of travel, and the first thickness is greater than the second thickness, and molding the aft end region with a second impact strength, wherein the first impact strength is greater than the second impact strength.
Dependencies are inferred from the claim text.