公开(公告)号：US12129030B2

公开(公告)日：2024-10-29

申请号：US16771473

申请日：2018-12-14

Applicant: Incaendium Initiative Corporation

Inventor： Michael S. Thomas

IPC: B64D1/16 ,  A62C3/02 ,  A62C37/00 ,  B64C1/00 ,  B64C1/38 ,  B64C1/40 ,  B64C9/00 ,  B64C15/14 ,  B64C19/02 ,  B64C39/02 ,  B64U20/60 ,  B64U50/18 ,  B64U50/34 ,  G01S19/42 ,  G05D1/00 ,  G05D1/10 ,  B64U101/47

CPC classification number: B64D1/16 ,  A62C3/0228 ,  A62C37/00 ,  B64C1/38 ,  B64C1/40 ,  B64C9/00 ,  B64C15/14 ,  B64C19/02 ,  B64U20/60 ,  B64U50/18 ,  B64U50/34 ,  G05D1/101 ,  B64C2001/0072 ,  B64C2009/005 ,  B64C2201/145 ,  B64U2101/47 ,  G01S19/42

Abstract: A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35° C. to 1,650° C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

公开(公告)号：US12043396B2

公开(公告)日：2024-07-23

申请号：US17412626

申请日：2021-08-26

Applicant: Farouk Dakhil

Inventor： Farouk Dakhil

IPC: B64D27/24 ,  B60L8/00 ,  B64C5/08 ,  B64C9/00 ,  B64D27/20 ,  H01L31/054 ,  H02S99/00 ,  B64D27/02 ,  B64D27/353

CPC classification number: B64D27/24 ,  B60L8/003 ,  B64C5/08 ,  B64C9/00 ,  B64D27/20 ,  H01L31/0543 ,  H02S99/00 ,  B64D27/026 ,  B64D27/353

Abstract: Methods, systems, and apparatuses for an electric aircraft may be shown and described. The electric aircraft may include a body; a first wing and a second wing, each of the first wing and the second wing having a plurality of stabilizers and a plurality of flaps; a cockpit; and at least one of a dielectric elastomer power generator, a wind turbine, an electric jet turbine, and a rotational electromagnetic power generator mounted on a central plane surface on the body.

公开(公告)号：US11964756B2

公开(公告)日：2024-04-23

申请号：US17367368

申请日：2021-07-04

Applicant: Aerhart, LLC

Inventor： Kevin Burns

IPC: B64C29/00 ,  B64C3/16 ,  B64C5/06 ,  B64C5/10 ,  B64C9/00 ,  B64C25/36 ,  B64C39/02 ,  B64C39/08 ,  B64D27/24 ,  B64D31/00 ,  B64U30/20 ,  B64U50/13 ,  B64U50/19 ,  G05D1/00

CPC classification number: B64C29/0033 ,  B64C3/16 ,  B64C5/06 ,  B64C5/10 ,  B64C9/00 ,  B64C25/36 ,  B64C39/024 ,  B64C39/08 ,  B64D27/24 ,  B64D31/00 ,  G05D1/102 ,  B64U30/20 ,  B64U50/13 ,  B64U50/19

Abstract: An aeronautical apparatus is disclosed that has two pairs of wings: an aft pair and a fore pair. Each wing has a thrust-angle motor. An assembly is coupled to each thrust-angle motor. Assemblies coupled to the fore wings have a propeller motor with a propeller and a landing element which is a wheel or a landing foot. When in forward flight, the propeller rotational axis is parallel to the longitudinal axis of the fuselage and the landing element is pointing toward the aft of the aeronautical apparatus to limit the drag presented by the landing element. When in vertical flight or hovering, the propeller rotational axis is perpendicular to the longitudinal and transverse axes of the fuselage and the landing element is deployed downward to facilitate landing.

公开(公告)号：US20240124128A1

公开(公告)日：2024-04-18

申请号：US18555961

申请日：2022-04-18

Applicant: Emilio MARTIN ALEXANDRE

Inventor： Emilio MARTIN ALEXANDRE

IPC: B64C11/48 ,  B64D27/02

CPC classification number: B64C11/48 ,  B64D27/02 ,  B64C9/00

Abstract: Consisting of a flap-type aerodynamic surface on the wing(s) (2) above the fuselage (1) of an aircraft with control surfaces (5) of the wing (2), the length of the device in the wing span direction being greater than or equal to the mid-chord of the flap, and comprising a thrust propeller engine (4), converting it into a propulsive flapper (3).

公开(公告)号：US11932412B2

公开(公告)日：2024-03-19

申请号：US17651514

申请日：2022-02-17

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nathan Krishnamoorthy ,  Vatsalya Surana ,  Ankur Mathur

IPC: B64D43/00 ,  B64C9/00 ,  B64D45/04

CPC classification number: B64D43/00 ,  B64C9/00 ,  B64D45/04

Abstract: Methods and systems for providing reduced flaps takeoff or landing advice in an aircraft. The methods and systems include a display device and a processor in operable communication with the display device. The processor is configured to execute program instructions. The program instructions are configured to cause the processor to receive takeoff or landing performance data including weather data and runway conditions data for a plurality of runways at a destination aerodrome, calculate values of takeoff or landing performance parameters for a plurality of flap configurations for each of the plurality of runways, and present, on the display device, at least one of the values of takeoff or landing performance parameters.

公开(公告)号：US20230348036A1

公开(公告)日：2023-11-02

申请号：US18214464

申请日：2023-06-26

Applicant: JETZERO, INC.

Inventor： Mark Allan Page

IPC: B64C1/06 ,  B64C39/10 ,  B64C9/00 ,  B64F5/10 ,  B64C39/00 ,  B64C7/02

CPC classification number: B64C1/069 ,  B64C39/10 ,  B64C9/00 ,  B64F5/10 ,  B64C39/00 ,  B64C7/02 ,  B64C2039/105 ,  B64C2211/00

Abstract: A system for modular aircraft includes at least a common component, wherein the at least a common component includes at least a flight component. The system includes at least a modular component, wherein the at least modular component includes at least a fuselage component and a collar component. The system includes at least an interface component, wherein the at least an interface component is configured to connect the at least a common component at a first end to the at least a modular component at a second end.

公开(公告)号：US20230312089A1

公开(公告)日：2023-10-05

申请号：US18175368

申请日：2023-02-27

Applicant: Odys Aviation, Inc.

Inventor： James Robert DORRIS ,  Alexander JEDINGER ,  Tadeh AVETIAN ,  Fabio CIAMPOLI ,  Uwe KIESEWETTER

IPC: B64C29/00 ,  B64C3/16 ,  B64C39/06 ,  B64C9/00 ,  B64C27/26 ,  G05D1/10

CPC classification number: B64C29/0008 ,  B64C3/16 ,  B64C9/00 ,  B64C27/26 ,  B64C39/068 ,  G05D1/102

Abstract: An aircraft is disclosed. The aircraft includes a first pair of wings, each wing in the first pair of wings including one or more actuating flaps configured to move to facilitate the aircraft transitioning between a forward cruise mode and a vertical hover mode, and operating in one of the forward cruise mode or the vertical hover mode. The aircraft further includes a second pair of wings, and one or more propellers coupled to the second pair of wings and oriented horizontally to provide upward lift.

公开(公告)号：US11760474B2

公开(公告)日：2023-09-19

申请号：US17340079

申请日：2021-06-06

Applicant: Xi Wang

Inventor： Xi Wang

IPC: B64C29/00 ,  B64C39/06 ,  B64C9/00 ,  B64C25/32 ,  B64C5/00 ,  B64C11/48 ,  B64C39/04

CPC classification number: B64C29/0033 ,  B64C5/00 ,  B64C9/00 ,  B64C11/48 ,  B64C25/32 ,  B64C39/04 ,  B64C39/068 ,  B64C2009/005

Abstract: A VTOL (vertical take-off and landing) box-wing aerial vehicle with multirotor to provide VTOL flight includes a detachable cabin, centered fuselage, a pair of first wings extending outward from the upper portion of the fuselage and a pair of second wings extending outwardly and from the lower portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joints the first wing and second wing at the tip to form the box-wing. The pylon includes heading control rudder. Secured to the wing or pylon or both wing and pylon, an overhead boom extending longitudinally to support a plurality of lift rotors or tiltable rotors for VTOL flight. Finally, the overhead boom mounted tiltable rotors propel the vehicle forward to generate lift from the wings. Furthermore, the wings are equipped with elevators and ailerons for flight control.

公开(公告)号：US11718393B2

公开(公告)日：2023-08-08

申请号：US17097463

申请日：2020-11-13

Applicant: AIRBUS HELICOPTERS

Inventor： Jacques Bellera ,  Nicolas Queiras

IPC: B64C27/00 ,  B64C27/57 ,  B64C13/04 ,  B64C9/00 ,  B64C25/36 ,  B64C25/52 ,  B64C27/06 ,  B64C27/08 ,  B64C27/82 ,  G05D1/08

CPC classification number: B64C27/57 ,  B64C9/00 ,  B64C13/0421 ,  B64C25/36 ,  B64C25/52 ,  B64C27/06 ,  B64C27/08 ,  B64C27/82 ,  G05D1/0858

Abstract: A method and a system for providing a rotorcraft with assistance in taking off from a slope. The rotorcraft includes at least one lift rotor provided with a plurality of blades, control devices for controlling the pitches of the blades, and landing gear provided with at least three ground contact members. The method comprises a step of measuring a piece of information relating to the forces to which each ground contact member is subjected during a landing phase for landing on the slope, a step of measuring at least one piece of information relating to the pitches of the blades during the landing phase, and a control step for controlling the pitches of the blades during the takeoff phase during which the rotorcraft takes off after the landing as a function of the measurements taken during the landing in order to enable a takeoff to be performed that is safe and simplified.

公开(公告)号：US20230242243A1

公开(公告)日：2023-08-03

申请号：US17591095

申请日：2022-02-02

Applicant: ROHR, INC.

Inventor： Anthony J. Lacko

IPC: B64C9/00 ,  B64F5/10 ,  B29C70/48

CPC classification number: B64C9/00 ,  B64F5/10 ,  B29C70/48 ,  B64C2009/005 ,  B29L2031/3076

Abstract: An aerostructure assembly that includes an aerostructure (e.g., a resin pressure molded structure) and a coupling assembly is disclosed. The aerostructure includes an outer shell and a female receiver located within an interior of the outer shell. The coupling assembly includes a coupling and a beam that extends from this coupling. The beam is disposed within the female receiver, including where at least part of the coupling is positioned beyond an open end of the outer shell. The shape of the female receiver may retain the aerostructure to the beam in at least one direction/dimension. One or more fasteners may be utilized to attach the aerostructure to the beam. The coupling may be formed from one or more metals, and in any case, accommodates attachment of the aerostructure assembly to a flight vehicle.