公开(公告)号：US11949267B2

公开(公告)日：2024-04-02

申请号：US17322886

申请日：2021-05-17

Applicant: NXP Aeronautics Research, LLC

Inventor： Steven J. Syracuse ,  Chad D. Tillman

IPC: 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 classification number: 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

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 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

Applicant: CANON KABUSHIKI KAISHA

Inventor： Shinji Obana ,  Ayumu Nemoto

IPC: 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 classification number: 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

Abstract: 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

Applicant: Airbus Operations Limited

Inventor： Benjamin BISHOP

IPC: B64C25/10

CPC classification number: B64C25/10

Abstract: 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

Applicant: HILL GROUP TECHNOLOGIES LIMITED

Inventor： Jason HILL

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

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

Abstract: 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

Applicant: Airbus Operations Limited

Inventor： Fraser Wilson

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

CPC classification number: B64C25/34 ,  B64C25/001 ,  B64C25/10 ,  B64C25/60 ,  B64C2025/008

Abstract: 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

Applicant: Goodrich Corporation

Inventor： Richard A. Himmelmann ,  Stephen E. Tongue

IPC: 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 classification number: 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

Abstract: 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：US20180346103A1

公开(公告)日：2018-12-06

申请号：US15997241

申请日：2018-06-04

Applicant: Airbus Operations Limited

Inventor： Robert Ian THOMPSON

IPC: B64C25/20 ,  B64C25/62 ,  B64C25/12

CPC classification number: B64C25/34 ,  B64C25/10 ,  B64C25/62

Abstract: An aircraft landing gear 2 is disclosed having a first arm 6a configured to have one or more wheels 8a mounted at one end, the first arm 6a being configured for mounting to a pivot 10a. The landing gear 2 includes a second arm 6b configured to have one or more wheels 8b mounted at one end, the second arm 6b being configured for mounting to a pivot 10b. The landing gear 2 further includes a first link 18a pivotally coupled to the first arm 6a, a second link 18b pivotally coupled to the second arm 6b; and a main link 20 pivotally coupled to each of the first and second links 18a, 18b and to a shock absorber 22 arranged to provide a biasing force via (i) the main linkage 20 and the first link 18a which opposes rotation of the first arm 6a about the pivot 10a and (ii) the main linkage 20 and the second link 18b which opposes rotation of the second arm 6b about the pivot 10b.

公开(公告)号：US20180244372A1

公开(公告)日：2018-08-30

申请号：US15445652

申请日：2017-02-28

Applicant: The Boeing Company

Inventor： Mark Nicholas Simpson ,  Mitchell Loren Ray Mellor ,  James E. Cusworth ,  Justin Cottet ,  Richard Kevin Johnson ,  George Sonnenburg

IPC: B64C25/20 ,  B64C25/26 ,  B64C25/14 ,  B64C25/34 ,  B64C25/60

CPC classification number: B64C25/20 ,  B64C25/10 ,  B64C25/14 ,  B64C25/26 ,  B64C25/34 ,  B64C25/60 ,  B64C2025/008

Abstract: An aircraft landing gear structure according to the present disclosure includes a strut assembly and a wheel assembly operatively coupled to the strut assembly. The strut assembly includes an upper tubular housing and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing such that the overall length of the strut assembly is transitioned between an extended configuration and a retracted configuration for stowage during flight. The wheel assembly includes a forward link pivotally coupled to the upper tubular housing and a truck beam that is pivotally coupled to the lower tubular housing such that translation of the lower tubular housing with respect to the upper tubular housing causes pivoting of the forward link and the truck beam with respect to one another, thereby tilting and/or raising a wheel of the wheel assembly with respect to the upper tubular housing.

公开(公告)号：US10011351B2

公开(公告)日：2018-07-03

申请号：US15200244

申请日：2016-07-01

Applicant: Bell Helicopter Textron Inc.

Inventor： John Richard McCullough ,  Paul K. Oldroyd

IPC: G05D1/00 ,  G05D3/00 ,  G06F7/00 ,  G06F17/00 ,  B64C29/02 ,  G05D1/10 ,  G08G5/00 ,  B64D1/22 ,  B64D1/10 ,  B64D17/02

CPC classification number: B64C29/02 ,  B64C11/28 ,  B64C25/04 ,  B64C25/10 ,  B64C27/30 ,  B64C37/00 ,  B64C39/024 ,  B64C39/04 ,  B64D1/10 ,  B64D1/22 ,  B64D17/025 ,  B64D17/80 ,  G08G5/0034 ,  G08G5/0039 ,  G08G5/0052 ,  G08G5/0056 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/025

Abstract: In some embodiments, a passenger pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a passenger pod assembly having a current location and a destination; upload a flight plan to a flight control system of a flying frame including an airframe and a propulsion system; dispatch the flying frame to the current location of the passenger pod assembly; couple the flying frame to the passenger pod assembly at the current location of the passenger pod assembly; transport the passenger pod assembly by air from the current location of the passenger pod assembly to the destination of the passenger pod assembly; and decouple the passenger pod assembly from the flying frame at the destination of the passenger pod assembly.

公开(公告)号：US10000282B2

公开(公告)日：2018-06-19

申请号：US15156820

申请日：2016-05-17

Applicant: Safran Landing Systems UK Ltd

Inventor： Robert Kyle Schmidt

IPC: B64C25/10 ,  B64C25/62 ,  B64C25/34 ,  B64C25/60 ,  F16F13/00

CPC classification number: B64C25/62 ,  B64C25/10 ,  B64C25/34 ,  B64C25/60 ,  F16F9/0218 ,  F16F9/3292 ,  F16F9/54 ,  F16F13/007 ,  F16F2226/04 ,  F16F2230/0023

Abstract: An aircraft landing gear assembly includes a mechanical structural linkage having a shock absorber and a linkage abutment which are biased apart by a mechanical spring. The force required to deform the spring sufficiently to place the linkage abutment at a predefined distance with respect to the shock absorber abutment is less than the breakout force of the shock absorber.