公开(公告)号：US11949267B2

公开(公告)日：2024-04-02

申请号：US17322886

申请日：2021-05-17

申请人： NXP Aeronautics Research, LLC

发明人： Steven J. Syracuse ,  Chad D. Tillman

IPC分类号： H02J7/00 ,  B60L5/00 ,  B60L53/12 ,  B60L53/14 ,  B60L53/30 ,  B60L53/38 ,  B60L53/60 ,  B60M3/00 ,  B64C25/10 ,  B64C39/02 ,  B64C39/04 ,  B64C39/08 ,  G01C9/00 ,  H02G1/02 ,  H02J50/00 ,  H02J50/05 ,  H02J50/10 ,  H04L67/12 ,  H04W4/02 ,  H04W4/029 ,  B64U10/10 ,  B64U10/13 ,  B64U10/25 ,  B64U30/20 ,  B64U50/19 ,  B64U50/34 ,  B64U101/30

CPC分类号： H02J7/0068 ,  B60L5/005 ,  B60L53/12 ,  B60L53/14 ,  B60L53/30 ,  B60L53/38 ,  B60L53/60 ,  B60M3/00 ,  B64C25/10 ,  B64C39/024 ,  B64C39/04 ,  B64C39/08 ,  G01C9/005 ,  H02G1/02 ,  H02J50/001 ,  H02J50/05 ,  H02J50/10 ,  H04L67/12 ,  H04W4/025 ,  H04W4/029 ,  B60L2200/10 ,  B64U10/10 ,  B64U10/13 ,  B64U10/25 ,  B64U30/20 ,  B64U50/19 ,  B64U50/34 ,  B64U2101/30 ,  H02J7/0044 ,  Y02T10/70 ,  Y02T10/7072 ,  Y02T90/12 ,  Y02T90/14 ,  Y02T90/16

摘要： 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 detect 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：US11831970B2

公开(公告)日：2023-11-28

申请号：US17718348

申请日：2022-04-12

申请人： CANON KABUSHIKI KAISHA

发明人： Shinji Obana ,  Ayumu Nemoto

IPC分类号： H04N23/54 ,  H04N23/68 ,  H02N2/00 ,  G03B15/00 ,  G03B17/56 ,  H02N2/10 ,  H04N23/51 ,  H04N23/55 ,  H04N23/57 ,  H04N23/66 ,  B64C25/10 ,  F16M11/38 ,  H04N7/18 ,  G01C21/18

CPC分类号： H04N23/54 ,  B64C25/10 ,  F16M11/38 ,  G03B15/006 ,  G03B17/561 ,  H02N2/001 ,  H02N2/0055 ,  H02N2/0085 ,  H02N2/103 ,  H04N7/185 ,  H04N23/51 ,  H04N23/55 ,  H04N23/57 ,  H04N23/66 ,  H04N23/68 ,  G01C21/18

摘要： An image pickup apparatus is capable of decreasing a space capacity occupied by component elements and being downsized compared to a case where an actuator is arranged independently of a supporting unit. The image pickup apparatus has an image pickup unit driven by the actuator, a base unit, and the supporting unit provided in a standing manner from the base unit and rotatably supports the image pickup unit. The actuator has a piezoelectric element and an oscillator including a transmission unit which transmits driving force caused by vibration excited by the piezoelectric element. The transmission unit is arranged in the supporting unit so that it is in pressure contact with the image pickup unit. The image pickup unit has a transmitted plane with which the transmission unit is brought into pressure contact, and the vibration excited by the oscillator causes the transmitted plane to move relatively to the oscillator.

公开(公告)号：US20230373613A1

公开(公告)日：2023-11-23

申请号：US18320619

申请日：2023-05-19

申请人： Airbus Operations Limited

发明人： Benjamin BISHOP

IPC分类号： B64C25/10

CPC分类号： B64C25/10

摘要： An aircraft is disclosed having a landing gear with a main support supporting one or more wheels. The landing gear has at least two sidestays by which landing gear loads can be propagated from the landing gear to the body of the aircraft. The sidestays are attached at one end to a rotatable yoke via joints which allow relative movement between the sidestays and the yoke so that the yoke can rotate about a yoke axis. Rotation of the yoke about the yoke axis, permitted by the joints, can help distribute loads between the two sidestays and/or combat negative effects resulting from an unfavourable tolerance stack during assembly, for example.

公开(公告)号：US20230356831A1

公开(公告)日：2023-11-09

申请号：US18022506

申请日：2021-08-23

申请人： HILL GROUP TECHNOLOGIES LIMITED

发明人： Jason HILL

IPC分类号： B64C27/06 ,  B64C25/10 ,  B64D41/00 ,  B64C1/00 ,  B64C25/52 ,  B64C27/605 ,  B64D27/02

CPC分类号： B64C27/06 ,  B64C25/10 ,  B64D41/00 ,  B64C1/00 ,  B64C25/52 ,  B64C27/605 ,  B64D27/02 ,  B64D2041/005 ,  B64C2001/0072

摘要： A light helicopter typically for 5 occupants is disclosed which achieves a hitherto unprecedented combination of range, speed and payload by adopting a novel approach to construction and positioning of components which affect overall aerodynamics in forward flight at speeds in excess of 70 metres per second and mass distribution and management of centre of gravity as fuel is consumed, load bearing strength and drag.

公开(公告)号：US11787529B2

公开(公告)日：2023-10-17

申请号：US17510117

申请日：2021-10-25

申请人： Airbus Operations Limited

发明人： Fraser Wilson

IPC分类号： B64C25/34 ,  B64C25/10 ,  B64C25/60 ,  B64C25/00

CPC分类号： B64C25/34 ,  B64C25/001 ,  B64C25/10 ,  B64C25/60 ,  B64C2025/008

摘要： An aircraft landing gear is disclosed having a landing gear leg attachable at a first end to an aircraft, and an axle beam, both the landing gear leg and the axle beam being rotatably mounted. The axle beam is rotatable between a first position, in which a first end of the axle beam is a first (shorter) distance from the first end of the landing gear leg, and a second position, in which said first end of the axle beam is a second (longer) distance from the first end of the landing gear leg. A biasing member is configured to be able to bias the axle beam towards the second position. An aircraft, a blended wing body aircraft, and a method of operating an aircraft are also disclosed.

公开(公告)号：US11685520B2

公开(公告)日：2023-06-27

申请号：US16998823

申请日：2020-08-20

申请人： Goodrich Corporation

发明人： Richard A. Himmelmann ,  Stephen E. Tongue

IPC分类号： B23K9/04 ,  B33Y10/00 ,  B64C25/00 ,  B23K9/173 ,  B23K9/23 ,  B64C25/10 ,  B64C25/34 ,  B64C25/60 ,  B23K31/02 ,  B23K15/00 ,  B33Y80/00 ,  B23K101/00 ,  B23K103/10 ,  B23K103/14

CPC分类号： B64C25/00 ,  B23K9/044 ,  B23K9/173 ,  B23K9/23 ,  B23K15/0086 ,  B23K15/0093 ,  B23K31/02 ,  B33Y10/00 ,  B33Y80/00 ,  B64C25/10 ,  B64C25/34 ,  B64C25/60 ,  B23K2101/006 ,  B23K2103/10 ,  B23K2103/14 ,  B64C2025/003 ,  B64C2025/006

摘要： A thin-skin support member is provided. The thin-skin support member may include a semi-circular edge and a flat edge that define a hollow cavity. A cylindrical cavity may be adjacent the hollow cavity and at least partially defined by the semi-circular edge. The cylindrical cavity may be configured to retain a strut assembly. A mounting interface may be coupled to the semi-circular edge and the flat edge. A torsion interface may be disposed adjacent the cylindrical cavity and configured to receive a torsion link. The thin-skin support member may be made using additive manufacturing and thus may have a grain structure grown in the direction of material being added.

公开(公告)号：US20230088515A1

公开(公告)日：2023-03-23

申请号：US17990577

申请日：2022-11-18

申请人： General Atomics Aeronautical Systems, Inc.

发明人： Michael Joseph Allwein ,  Caleb Andrew Bartels ,  Brian Michel Shamblin ,  James Edward McMillen

IPC分类号： B64C25/10 ,  B64C25/26 ,  B64C25/20 ,  B64C25/12 ,  B64C25/14 ,  B64C25/18

摘要： A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

公开(公告)号：US20220315200A1

公开(公告)日：2022-10-06

申请号：US17712413

申请日：2022-04-04

申请人： Airbus Operations SAS

发明人： Benoit ORTEU ,  Damien SIRE

IPC分类号： B64C1/18 ,  B64C1/10 ,  B64C25/00 ,  B64C25/04 ,  B64C25/10

摘要： A landing gear bay including a bottom wall which includes longitudinal beams and at least one panel forming an airtight barrier between first and second zones disposed on either side of the panel. The panel has first and second longitudinal edges each linked to one of the longitudinal beams. The second zone is configured to sustain a pressure greater than that of the first zone. The panel has a profile that is substantially constant in the longitudinal direction and includes at least one central part offset toward the second zone with respect to its first and second longitudinal edges. This solution makes it possible to limit the vertical stresses applied to the longitudinal beams by virtue of the pressure difference between the first and second zones.

公开(公告)号：US20220289365A1

公开(公告)日：2022-09-15

申请号：US17572254

申请日：2022-01-10

申请人： Airbus Operations SAS

发明人： Benoit ORTEU ,  Damien SIRE

IPC分类号： B64C25/04 ,  B64C25/10

摘要： An aircraft including two main landing gears and also a main landing gear bay configured to house, on either side of a vertical median plane, the two main landing gears in a retracted position, the main landing gear bay including a rear transverse wall, a front transverse wall and also an end wall that is approximately perpendicular to the rear and front transverse walls. The main landing gear bay includes at least one strut connecting the rear or front transverse wall and the end wall, approximately positioned in the vertical median plane.

公开(公告)号：US11433992B2

公开(公告)日：2022-09-06

申请号：US16037198

申请日：2018-07-17

申请人： AIRBUS HELICOPTERS

发明人： Pierre Prud'homme Lacroix ,  Olivier Bistuer

IPC分类号： B64C25/10 ,  B64C25/34 ,  B64C25/36 ,  B64C25/32 ,  B64C25/00

摘要： A rotorcraft having an airframe, the airframe carrying at least one rotor that contributes to providing the rotorcraft with lift and/or propulsion, the rotorcraft having at least one undercarriage. The at least one undercarriage comprises at least one inclined wheel undercarriage, the inclined wheel undercarriage having an undercarriage leg carrying at least one axle, the at least one axle carrying at least one wheel, the at least one wheel not being in contact with any other wheel, the at least one wheel presenting positive or negative camber when the at least one wheel touches the ground and independently of forces exerted by said airframe on the inclined wheel undercarriage.