Fuselage shield for an aircraft with an unducted engine
AssigneeGeneral Electric Company
InventorsDavid William Crall, Nicholas Joseph Kray, Douglas Duane Ward, Brandon Wayne Miller
Life of this patent
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Abstract
In an aspect of the present disclosure, an aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; a single unducted rotor engine mounted at a location spaced from the fuselage of the aircraft, the single unducted rotor engine comprising an unducted rotor assembly having a single stage of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the single stage of rotor blades of the unducted rotor assembly along the lateral direction.
Claims21
An aircraft defining a longitudinal direction and a lateral direction, the aircraft comprising:
- a fuselage;
- a single unducted rotor engine mounted at a location spaced from the fuselage of the aircraft, the single unducted rotor engine comprising an unducted rotor assembly having a single stage of rotor blades;
- and
- a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the single stage of rotor blades of the unducted rotor assembly along the lateral direction.
A fuselage shield assembly for use with a fuselage of an aircraft having a single unducted rotor engine, the aircraft defining a longitudinal direction and a lateral direction, the fuselage shield assembly comprising:
- a body configured to be attached to or formed integrally with the fuselage of the aircraft at a location in alignment with the single unducted rotor engine along the lateral direction, body comprising a plurality of zones configured to be arranged along a circumference of the fuselage when coupled to the fuselage of the aircraft, wherein an impact resistance of the fuselage shield varies between each of the adjacent zones.
Dependencies are inferred from the claim text.