公开(公告)号：US20240308655A1

公开(公告)日：2024-09-19

申请号：US18660775

申请日：2024-05-10

Applicant: Joby Aero. Inc.

Inventor： Ian Andreas Villa ,  Jacek Kawecki ,  Jalen Christian Doherty ,  Ryan Naru ,  Mark Moore ,  Alex Michael Gary ,  Adam Chase ,  Matthew William Derkach ,  Philipp Haban

IPC: B64C29/00 ,  B64C39/04 ,  B64F5/10

CPC classification number: B64C29/0033 ,  B64C29/0025 ,  B64C39/04 ,  B64F5/10 ,  B60L2200/10

Abstract: An aerial vehicle includes a fuselage supporting a pair of wings, with each of wings having a pair of booms attached thereto. A tilt rotor is positioned at each of the forward ends of each of the booms, to provide the aerial vehicle with at least four tilt rotors. A fixed rotor is positioned at and secured to the aft (or trailing) ends of each of the booms, to provide the aerial vehicle with at least four fixed rotors.

公开(公告)号：US11912404B2

公开(公告)日：2024-02-27

申请号：US16280021

申请日：2019-02-19

Applicant: DeLorean Aerospace, LLC

Inventor： Paul J. DeLorean

IPC: B64C29/00 ,  B64D27/24 ,  B64C39/12 ,  B64C39/10 ,  B64C39/04 ,  B64C27/32 ,  B64U10/25

CPC classification number: B64C29/0033 ,  B64C27/32 ,  B64C39/04 ,  B64C39/10 ,  B64C39/12 ,  B64D27/24 ,  B64U10/25 ,  Y02T50/10 ,  Y02T50/60

Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.

公开(公告)号：US11865926B2

公开(公告)日：2024-01-09

申请号：US16973426

申请日：2019-06-04

Applicant: NXP Aeronautics Research, LLC

Inventor： Steven J. Syracuse ,  Chad D. Tillman

IPC: B60L5/00 ,  H02J50/00 ,  B64U50/34 ,  B64C39/08 ,  B64C39/04 ,  H02J50/05 ,  B64U30/20 ,  B64U50/19

CPC classification number: B60L5/005 ,  B64C39/04 ,  B64C39/08 ,  H02J50/001 ,  H02J50/05 ,  B64U30/20 ,  B64U50/19 ,  B64U50/34

Abstract: An apparatus in which electric power is generated for an electrical load from differentials in electric field strengths within a vicinity of powerlines includes: a plurality of electrodes separated and electrically insulated from one another for enabling differentials in voltage resulting from differentials in electric field strength experienced there at; and electrical components electrically connected therewith and configurable to establish one or more electric circuits whereby voltage differentials cause a current to flow through the established electric circuit for powering the electrical load. Preferably, the apparatus includes a control assembly having one or more voltage-detector components configured to detected relative voltages of the electrodes; and a processor enabled to configure—based on the detected voltages and based on voltage and electric current specifications for powering the electrical load—one or more of the electrical components to establish an electric circuit for powering the electrical load.

公开(公告)号：US20230211878A1

公开(公告)日：2023-07-06

申请号：US17568906

申请日：2022-01-05

Applicant: Textron Innovations Inc.

Inventor： Steven Ryan Schafer

IPC: B64C29/02 ,  B64C5/18 ,  B64C39/04 ,  B64C9/00 ,  B64C25/32 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C5/18 ,  B64C39/04 ,  B64C9/00 ,  B64C25/32 ,  B64C39/024

Abstract: A telescoping tail assembly for use on an aircraft having a fore-aft length. The telescoping tail assembly includes a housing extending in an aftward direction, a tailboom slidable along the housing into various positions including an extended position and a retracted position and one or more control surfaces coupled to the tailboom. The tailboom increases the fore-aft length of the aircraft in the extended position and decreases the fore-aft length of the aircraft in the retracted position.

公开(公告)号：US11673643B2

公开(公告)日：2023-06-13

申请号：US16062973

申请日：2017-03-23

Applicant: JP AEROSPACE GROUP, INC.

Inventor： John K. Markley ,  Jason Russell ,  Paul Bartlett

IPC: B64C1/00 ,  B64C5/02 ,  B64C39/04 ,  B64C9/20 ,  B64C3/50 ,  B64C3/14 ,  B64C5/06 ,  B64C25/00 ,  B64C9/00

CPC classification number: B64C1/0009 ,  B64C3/14 ,  B64C3/50 ,  B64C5/02 ,  B64C5/06 ,  B64C9/20 ,  B64C39/04 ,  B64C2001/0045 ,  B64C2009/005 ,  B64C2025/003

Abstract: A low stall or minimum control speed aircraft comprising a fuselage that has vertically flat sides; wings with high a lift airfoil profile of constant chord section set at zero degree planform sweep, twin booms having inner vertically flat surfaces, twin vertical stabilizers, a flying horizontal stabilizer; preferably twin engines having propellers and wherein each engine preferably has a thrust-line that is inclined nose-up to a maximum of +8 degrees, and is parallel to the wing chord underneath wing mounts and landing gear doors that provide surfaces for channeling propeller wash in a rearward direction; all working in concert so that the airplane has an extremely low stall speed and minimum control speed. The engines may be diesel, hydrogen fuel cell, electric fuel cell, diesel-electric, gas turbine or combinations thereof. The propellers may be counter-rotating.

公开(公告)号：US11661191B2

公开(公告)日：2023-05-30

申请号：US17465365

申请日：2021-09-02

Applicant: Endurant Systems, LLC

Inventor： Gregory Leonard McAdoo

IPC: B64C39/02 ,  B64C27/08 ,  B64D27/24 ,  B64C27/26 ,  B64C29/00 ,  B64C39/04 ,  H02J7/14 ,  H02J7/34 ,  B64D45/00 ,  H02K7/18 ,  B64D27/02 ,  B64D27/04

CPC classification number: B64C39/024 ,  B64C27/08 ,  B64C27/26 ,  B64C29/0033 ,  B64C39/04 ,  B64D27/24 ,  B64D45/00 ,  H02J7/14 ,  H02J7/34 ,  H02K7/1815 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/141 ,  B64D27/04 ,  B64D2027/026 ,  B64D2045/0085 ,  B64D2221/00 ,  Y02T50/60

Abstract: UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

公开(公告)号：US20230150659A1

公开(公告)日：2023-05-18

申请号：US17528989

申请日：2021-11-17

Applicant: Bell Textron Inc.

Inventor： Steven R. Ivans ,  Robert Roe

IPC: B64C29/00 ,  B64C39/04

CPC classification number: B64C29/0033 ,  B64C39/04

Abstract: One embodiment is an aircraft including first and second fuselages; a wing assembly connecting the first and second fuselages, wherein the first and second fuselages are parallel to one another; first and second forward propulsion systems tiltably attached to forward ends of the first and second fuselages; and first and second aft propulsion systems fixedly attached proximate aft ends of the first and second fuselages.

公开(公告)号：US20230147045A1

公开(公告)日：2023-05-11

申请号：US17958722

申请日：2022-10-03

Applicant: John Galaz

Inventor： John Galaz

IPC: B64B1/30 ,  B64C39/04 ,  B64D27/24 ,  B64D27/10 ,  B60L8/00 ,  B64C1/26 ,  B64B1/20 ,  B64B1/22 ,  B64D47/08 ,  B64B1/14 ,  F02B61/04 ,  H01M10/46

CPC classification number: B64B1/30 ,  B64C39/04 ,  B64D27/24 ,  B64D27/10 ,  B60L8/003 ,  B64C1/26 ,  B64B1/20 ,  B64B1/22 ,  B64D47/08 ,  B64B1/14 ,  F02B61/04 ,  H01M10/465 ,  B64D2211/00 ,  B64D2027/026

Abstract: A solar powered airship includes a cabin, at least one fuselage having an interior volume filled with a volume of a lighter-than-air gas such as helium, and a wing affixed to the fuselage. A plurality of solar panels are affixed to the wing and to the fuselage. A plurality of rotors are affixed to the wing, wherein each rotor is powered via an electric motor having a battery that is operably connected to the plurality of solar panels, thereby allowing for continuous flight. The solar powered airship may further include propellors, which may also be powered via the solar panels, or which may include gasoline powered motors. The solar powered airship can include various configurations and numbers of fuselages, wings, rotors, and propellors.

公开(公告)号：US20180086446A1

公开(公告)日：2018-03-29

申请号：US15274040

申请日：2016-09-23

Applicant: Sikorsky Aircraft Corporation

Inventor： Mark R. Alber

IPC: B64C29/00 ,  B64C3/38

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C5/02 ,  B64C39/04 ,  B64D35/08

Abstract: A tiltwing aircraft includes a fuselage, an engine mounted stationary relative to the fuselage, and an opposed pair of wings. The wings are separated from each other with the fuselage therebetween, each wing independently mounted to the fuselage by a respective pivot system for rotation relative to the fuselage. An opposed pair of rotor assemblies is included, each operatively connected to a respective one of the wings for common rotation with the respective wing back and forth between a first position predominantly for lift to a second position predominantly for thrust.

公开(公告)号：US20160311545A1

公开(公告)日：2016-10-27

申请号：US15134938

申请日：2016-04-21

Applicant: Aurora Flight Sciences

Inventor： Robert W. Parks ,  Francesco Giannini

IPC: B64D31/00 ,  B64C5/02 ,  B64C3/42 ,  B64C3/00

CPC classification number: B64C3/42 ,  B64C3/38 ,  B64C5/02 ,  B64C23/072 ,  B64C29/0033 ,  B64C39/04 ,  B64D27/24 ,  B64D2211/00 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: The present invention is directed to a solar-powered aircraft comprising a fixed wing panel, a motor driven propeller, a plurality of secondary wing panels, and a tail assembly having a first tail panel and a second tail panel. Each secondary wing panel being configured to rotate about a first longitudinal pivot axis extending from a distal end of the fixed wing panel through a central transverse portion of the secondary wing panel. The secondary wing panels may comprise an array of solar panels on its surface. The first tail panel comprises a second array of solar panels located on a surface of the first tail panel, the first tail panel being configured to rotate about a second longitudinal pivot axis through a central transverse portion of the first tail panel.

Abstract translation: 本发明涉及一种太阳能飞行器，其包括固定翼板，马达驱动螺旋桨，多个次翼板和具有第一尾板和第二尾板的尾组件。 每个次翼板被构造成围绕从固定翼板的远端延伸穿过次翼板的中心横向部分的第一纵向枢转轴线旋转。 次翼板可以包括其表面上的太阳能电池板阵列。 第一尾板包括位于第一尾板的表面上的第二阵列的太阳能板，第一尾板被构造成围绕第一纵向枢转轴线旋转穿过第一尾板的中心横向部分。