Vertical takeoff and landing airframe
First Claim
1. An aircraft, comprising:
- a fuselage;
opposed wings extending from opposed sides of the fuselage;
at least one engine mounted to each of the opposed wings;
wherein at least a portion of each opposed wing including the at least one engine rotates relative to the fuselage around a rotation axis, andwherein the at least one engine has a propeller with a plurality of blades configured for a cyclic pitch variation.
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Accused Products
Abstract
Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.
44 Citations
19 Claims
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1. An aircraft, comprising:
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a fuselage; opposed wings extending from opposed sides of the fuselage; at least one engine mounted to each of the opposed wings; wherein at least a portion of each opposed wing including the at least one engine rotates relative to the fuselage around a rotation axis, and wherein the at least one engine has a propeller with a plurality of blades configured for a cyclic pitch variation. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. An aircraft, comprising:
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a fuselage; opposed wings extending from opposed sides of the fuselage; a plurality of engines mounted to each of the opposed wings; wherein at least a portion of each opposed wing including the plurality of engines rotates relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage between a first configuration adapted for vertical take-off and landing, and a second configuration adapted for horizontal flight, and wherein an output of each engine is independently adjustable at least in the first configuration. - View Dependent Claims (13, 14, 15, 16)
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17. A method of flying an aircraft, the method comprising:
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rotating at least a portion of opposed wings relative to a fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage to orient a leading edge of each opposed wing vertically, the rotated portion of the opposed wings having at least one engine; actuating the at least one engine; and independently controlling an output of the at least one engine to hover the aircraft. - View Dependent Claims (18, 19)
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Specification