Vertical Takeoff and Landing Airframe

• US 20190225333A1
• Filed: 04/02/2019
• Published: 07/25/2019
• Est. Priority Date: 04/27/2017
• Status: Active Grant

• Current Assignee: PteroDynamics Inc.
• Original Assignee: PteroDynamics Inc.
• Inventors: Petrov, Val
• Granted Patent: US 10,556,679 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 25/34 wheeled type, e.g. multi-wheeled bogies
• CPC Class Codes: B64C 25/54 Floats
• CPC Class Codes: B64C 27/26 characterised by provision of fixed wings
• CPC Class Codes: B64C 27/28 with forward-propulsion propellers pivotable to act as lifting rotors
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 3/38 Adjustment of complete wings or parts thereof
• CPC Class Codes: B64C 3/42 Adjusting about chordwise axes
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 37/00 Convertible aircraft
• CPC Class Codes: B64D 27/12 within, or attached to, wings
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

Claims

1-30. -30. (canceled)

31. 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, and

wherein the at least one engine has a propeller with a plurality of blades configured for at least one of a cyclic pitch variation and a collective pitch variation.

32. The aircraft according to claim 31, wherein the rotation axis is non-perpendicular and transverse to a longitudinal axis of the fuselage.

33. The aircraft according to claim 31, wherein the at least a portion of each opposed wing including the at least one engine rotates relative to the fuselage between a first configuration adapted for vertical take-off and landing, and a second configuration adapted for horizontal flight.

34. The aircraft according to claim 33, wherein the at least one engine provides lift to the aircraft in the first configuration.

35. The aircraft according to claim 33, wherein the at least one of the cyclic pitch variation and the collective pitch variation of the plurality of propeller blades allows hovering in the first configuration of the opposed wings.

36. The aircraft according to claim 33, wherein the at least one of the cyclic pitch variation and the collective pitch variation of the plurality of propeller blades allows forward flight in the first configuration of the opposed wings.

37. The aircraft according to claim 31, wherein output of each engine is independently adjustable.

38. The aircraft according to claim 31, wherein each of the opposed wings includes a fixed portion extending from the fuselage and a rotating portion outboard of the fixed portion.

39. The aircraft according to claim 38, wherein a leading edge of the rotating portion of each opposed wing faces upward in the first configuration of the opposed wings.

40. The aircraft according to claim 38, wherein each of the opposed wings has at least one actuator to control rotation of the rotating portion relative to the fixed portion.

41. The aircraft according to claim 40, wherein the at least one actuator is a linear actuator.

46. The aircraft according to claim 31, wherein each of the opposed wings includes a fixed portion extending from the fuselage and a rotating portion outboard of the fixed portion.

47. The aircraft according to claim 31, wherein a leading edge of the rotating portion of each opposed wing faces upward in the first configuration of the opposed wings.

42. An aircraft, comprising:

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, and

wherein an output of each engine is independently adjustable.

43. The aircraft according to claim 42, wherein the outlet of each engine is independently adjustable by varying a speed of each engine.

44. The aircraft according to claim 42, wherein the at least a portion of each opposed wing including the plurality of engines rotates relative to the fuselage between a first configuration adapted for vertical take-off and landing, and a second configuration adapted for horizontal flight.

45. The aircraft according to claim 44, wherein the plurality of engines provide lift to the aircraft in the first configuration.

48. A method of flying an aircraft, the method comprising:

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.

49. The method according to claim 48, further comprising rotating the rotated portion of the opposed wings having the at least one engine mounted thereto to orient the at least one engine and a leading edge of the wing horizontally for forward flight.

50. The method according to claim 48, further comprising pausing rotation of the rotated portion of the opposed wings such that the opposed wings and the at least one engine are between a vertical and a horizontal orientation to transition between hovering and forward flight.