公开(公告)号：US12202591B2

公开(公告)日：2025-01-21

申请号：US17727551

申请日：2022-04-22

Applicant: Baxter Aerospace LLC.

Inventor： Jeffrey Baxter ,  Michael Baxter

IPC: B64C29/02 ,  B64C1/16 ,  B64C9/08 ,  B64C15/12 ,  B64C29/00

Abstract: An aircraft may include a fuselage, a propulsion assembly configured to produce thrust for the aircraft, and a gimballing mechanism articulatably coupling the propulsion assembly to the fuselage and configured to rotate the propulsion assembly about a first axis of rotation defined through a center of mass of the propulsion assembly, and rotate the propulsion assembly about a second axis of rotation defined through the center of mass of the propulsion assembly. The first axis of rotation may be perpendicular to the second axis of rotation. The first axis of rotation may be perpendicular to the second axis of rotation.

公开(公告)号：US20250002148A1

公开(公告)日：2025-01-02

申请号：US18731094

申请日：2024-05-31

Applicant: Thomas W. Melcher

Inventor： Thomas W. Melcher

IPC: B64D1/22 ,  B64C3/38 ,  B64C9/02 ,  B64C29/02 ,  B64C37/00 ,  B64D27/24 ,  B64F1/36 ,  B64G1/40 ,  B64U10/20 ,  B64U30/12 ,  B64U30/26 ,  B64U50/19 ,  B64U101/60

Abstract: An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

公开(公告)号：US20240367789A1

公开(公告)日：2024-11-07

申请号：US18773469

申请日：2024-07-15

Applicant: Ivan ERMANOSKI

Inventor： Ivan ERMANOSKI

IPC: B64C39/02 ,  B64C3/10 ,  B64C11/46 ,  B64C29/02 ,  B64D9/00 ,  B64D27/24 ,  B64D41/00 ,  B64U10/20 ,  B64U30/10 ,  B64U50/10 ,  B64U101/60 ,  G05D1/46

Abstract: An unmanned aerial vehicle (UAV) for gas transport is disclosed. The UAV includes a fuselage enclosing a volume, and a gas reservoir enclosed within the fuselage, filling at least a majority of the volume. The gas reservoir is configured to receive and store a gas at a pressure no greater than 100 bar. The UAV also includes a propulsion system having at least one engine, each of the at least one engine coupled to a prop that is driven by the at least one engine using energy derived from the gas stored in the gas reservoir. The UAV also includes a control system communicatively coupled to the propulsion system and configured to operate the unmanned aerial vehicle to autonomously transport the gas. The UAV may have a footprint while on the ground, and the footprint of the UAV may be no larger than three standard parking spaces.

公开(公告)号：US12097947B2

公开(公告)日：2024-09-24

申请号：US18001617

申请日：2021-06-14

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Jean-Louis Robert Guy Besse ,  Camel Serghine

IPC: B64C27/50 ,  B64C11/06 ,  B64C11/28 ,  B64C27/28 ,  B64C29/02 ,  B64D29/00 ,  B64C29/00

CPC classification number: B64C11/28 ,  B64C11/06 ,  B64C27/28 ,  B64C27/50 ,  B64C29/02 ,  B64D29/00 ,  B64C29/0008

Abstract: A propulsion unit with a propeller includes a nacelle; a propeller rotatably mounted in the nacelle by means of a hub. The propeller has blades mounted in a blade cuff that is pivotable about a pitch axis relative to the hub. Each blade is pivotable relative to the cuff about a folding axis. A folding device includes an actuator for folding the blades. The folding device includes a control member rotationally affixed to the blade cuff and driven by the actuator. A connecting rod is pivotably mounted, on the one hand, on a root the associated blade and, on the other hand, on the movable control member.

公开(公告)号：US12077286B2

公开(公告)日：2024-09-03

申请号：US17652705

申请日：2022-02-28

Applicant: Matthew W. Townsend

Inventor： Matthew W. Townsend

IPC: B64C29/02 ,  B64C3/40 ,  B64C17/02 ,  B64U10/25 ,  B64U40/20 ,  B64U30/12 ,  B64U101/60

CPC classification number: B64C29/02 ,  B64C3/40 ,  B64C17/02 ,  B64U40/20 ,  B64U10/25 ,  B64U30/12 ,  B64U2101/60

Abstract: A drone can be used to carry a payload. The drone can include at least two wings extending from a fuselage and propellers that allow the drone to fly in a horizontal orientation. The drone can takeoff and land from a vertical orientation via landing rods at the rear of the fuselage. The drone also includes an adjustable center of gravity and/or an adjustable center of lift. The center of gravity can be adjusted by changing the weight of payload located fore and aft of the center of gravity or moving at least a portion of the payload fore or aft along the fuselage. The center of lift can be adjusted by swinging the wings away from or towards the fuselage or sliding the wings fore or aft along the fuselage such that the center of lift is adjacent to the center of gravity.

公开(公告)号：US11975817B2

公开(公告)日：2024-05-07

申请号：US17175327

申请日：2021-02-12

Applicant: Bell Textron Inc.

Inventor： John R. Wittmaak, Jr. ,  Russell C. Peters ,  Nathaniel G. Lundie

IPC: G05D1/00 ,  B64C13/16 ,  B64C29/02 ,  B64F5/60

CPC classification number: B64C13/16 ,  B64C29/02 ,  B64F5/60

Abstract: A method for reducing form drag on a tailsitter aircraft during at least one of takeoff or landing includes vertically taking off from the ground in a tailsitter orientation. The method also includes determining an actual pitch of the tail sitter aircraft in the tailsitter orientation. The method also includes determining a difference between the actual pitch and a predetermined pitch. The method also includes adjusting a heading of the tailsitter aircraft based on the difference to minimize a pitch angle to reduce the form drag on the tailsitter aircraft.

公开(公告)号：US11851176B1

公开(公告)日：2023-12-26

申请号：US17190071

申请日：2021-03-02

Applicant: Wing Aviation LLC

Inventor： Adam Woodworth ,  Adem Rudin ,  Stephen Benson

IPC: B64C3/24 ,  B64C3/18 ,  B29C45/00 ,  B64C29/02 ,  B64C39/02

CPC classification number: B64C3/24 ,  B29C45/0053 ,  B64C3/18 ,  B29C2045/0079 ,  B29C2045/0093 ,  B64C29/02 ,  B64C39/024

Abstract: An example method of manufacturing a wing includes providing a wing frame. The wing frame includes a primary spar, a drag spar, a plurality of transverse frame elements having at least one spar joiner, and a plurality of mounting elements. The primary spar is coupled to the drag spar via the at least one spar joiner. The method further includes placing the wing frame into a mold, wherein the mold defines a shape of the wing. The method also includes injecting the mold with an air-filled matrix material, such that the air-filled matrix material substantially encases the wing frame and fills the defined shape of the wing, and such that the plurality of transverse frame elements provide torsional rigidity to the wing.

公开(公告)号：US11772789B2

公开(公告)日：2023-10-03

申请号：US16973307

申请日：2019-06-28

Applicant: LEONARDO S.P.A.

Inventor： Riccardo Bianco Mengotti

IPC: B64C29/02 ,  B64C9/00 ,  B64C25/32 ,  B64C27/54 ,  B64C39/02 ,  B64C39/06 ,  B64U10/00

CPC classification number: B64C29/02 ,  B64C9/00 ,  B64C25/32 ,  B64C27/54 ,  B64C39/024 ,  B64C39/068 ,  B64C2009/005 ,  B64U10/00

Abstract: A tail sitter aircraft includes a wing with a closed front section and a fuselage, from which the wing extends. The wing includes a first portion projecting from the fuselage and a second portion spaced from the first portion. The aircraft includes first and second connecting section that are interposed between the first and second portions. The fuselage extends parallel to a first axis and the first and second portions extend parallel to a second axis orthogonal to the first axis. The first axis is arranged, in use, vertically in a take-off/landing position and inclined with respect to the vertical direction in a cruising position.

公开(公告)号：US20230303248A1

公开(公告)日：2023-09-28

申请号：US18296565

申请日：2023-04-06

Applicant: Amazon Technologies, Inc.

Inventor： Gur Kimchi ,  Louis Leroi LeGrand, III ,  Dominic Timothy Shiosaki ,  Ricky Dean Welsh

IPC: B64C39/02 ,  B64C29/02 ,  B64C27/20 ,  B64C11/46 ,  B64C27/26 ,  B64C39/06

CPC classification number: B64C39/024 ,  B64C11/46 ,  B64C27/20 ,  B64C27/26 ,  B64C29/02 ,  B64C39/062 ,  B64U10/13

Abstract: Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation.

公开(公告)号：US20230234705A1

公开(公告)日：2023-07-27

申请号：US18160101

申请日：2023-01-26

Applicant: Wisk Aero LLC

Inventor： Neel Vora ,  Pranay Sinha

IPC: B64C29/00 ,  B64C29/02

CPC classification number: B64C29/0033 ,  B64C29/02

Abstract: Embodiments provide a VTOL aircraft including a plurality of tilting propeller assemblies each coupled to a support structure and configured to transition between a vertical flight and a forward flight position. Each tilting propeller assembly comprising a propeller and a movable fairing provided downstream of the propeller. The movable fairing is configured to extend along an axis of rotation of the propeller. When the tilting propeller assembly transitions between the vertical and forward flight position, the movable fairing is configured to swivel to extend parallel to the direction of resultant airflow over the tilting propeller assembly into a minimum drag orientation. The movable fairing is damped enough to prevent any oscillations from the propeller wake shedding, and at the same time, keep the propeller aligned in a minimum-drag orientation with the resultant flow.