公开(公告)号：US12162600B2

公开(公告)日：2024-12-10

申请号：US17298501

申请日：2020-05-13

Applicant: AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATIONS GmbH

Inventor： Chris Heaysman ,  John Martin Gaitonde ,  Hauke Seegel

IPC: B64C3/18 ,  B64C1/00 ,  B64C1/06 ,  B64C3/20 ,  B64C3/26 ,  B64C3/34 ,  B64F5/10 ,  B29C70/42 ,  B29C70/84 ,  B29D99/00

Abstract: An aircraft panel assembly with a panel and a plurality of stiffeners on the panel is disclosed. Each stiffener has an attachment part attached to the panel and a structural part spaced apart from the panel. A rib foot beam crosses the stiffeners at a series of intersections. At each intersection the rib foot beam is located between the panel and the structural part of a respective one of the stiffeners.

公开(公告)号：US20240375762A1

公开(公告)日：2024-11-14

申请号：US18313668

申请日：2023-05-08

Applicant: EMBRAER S.A.

Inventor： Valdir José Augusto DE OLIVEIRA JUNIOR ,  Odair CORÁ

IPC: B64C3/26 ,  B64C3/34

Abstract: Access cover panel assemblies are provided that are especially useful to cover access openings of aircraft wing fuel tanks and include an inner cover plate and an outer cover plate spaced from the inner cover plate which defines a circumferentially spaced-apart plurality of apertures. A circumferentially spaced-apart plurality of generally U-shaped floating nut plates dependently extend from the inner cover plate toward the outer cover plate with each nut plate being in alignment with a respective one of the apertures. A corresponding plurality of attachment bolts extend through each of the apertures of the outer cover plate and are threadably coupled to a respective one of the floating nut plates to thereby removably secure the inner and outer cover plates to one another and to the surrounding structure defining the access opening.

公开(公告)号：US20240174372A1

公开(公告)日：2024-05-30

申请号：US18522340

申请日：2023-11-29

Applicant: Airbus Operations Limited

Inventor： Dylan Vignola

IPC: B64D37/00 ,  B64C3/34

CPC classification number: B64D37/005 ,  B64C3/34

Abstract: An aircraft including a wing, a first pressure sensor and a second pressure sensor, wherein each pressure sensor is configured to measure pressure of a liquid within the wing and has a known position within the wing. The aircraft includes a processing system configured to receive first pressure data from the first pressure sensor, receive second pressure data from the second pressure sensor, and determine a bending state of the wing based on the first pressure data, the second pressure data, and the known positions of the first and second pressure sensors within the wing.

公开(公告)号：US11952146B2

公开(公告)日：2024-04-09

申请号：US17699770

申请日：2022-03-21

Applicant: ZSM HOLDINGS LLC

Inventor： Jason C. Bell ,  Etan D. Karni ,  Scott David Rewerts ,  Ravi Singh

IPC: B64C1/20 ,  B64C1/06 ,  B64C1/14 ,  B64C1/22 ,  B64C3/32 ,  B64C3/34 ,  B64C17/08 ,  B64D9/00 ,  B64D37/04 ,  B64F1/32 ,  F03D13/40

CPC classification number: B64D9/003 ,  B64C1/0683 ,  B64C1/1415 ,  B64C1/20 ,  B64C1/22 ,  B64C3/32 ,  B64C3/34 ,  B64C17/08 ,  B64D9/00 ,  B64D37/04 ,  B64F1/32 ,  F03D13/40 ,  B64D2009/006 ,  F05B2260/02

Abstract: Systems and methods for loading a cargo aircraft are described. The system includes at least one rail disposed in an interior cargo bay of a cargo aircraft that extends at an angle relative to an interior bottom contact surface of a forward portion of the interior cargo bay, through a kinked portion and an aft portion of the interior cargo bay. Payload-receiving fixtures are described that can be used in conjunction with the rail system, allowing for large cargo, such as wind turbine blades, to be transported by aircraft. Methods of loading a cargo aircraft can include advancing the large payload into the interior cargo bay of the aircraft such that at least one of the payload-receiving fixtures rises relative to a plane defined by the interior bottom contact surface of the forward portion of the interior cargo bay. Various systems, methods, components, and related tooling are also provided.

公开(公告)号：US11926434B2

公开(公告)日：2024-03-12

申请号：US17403134

申请日：2021-08-16

Applicant: ZSM HOLDINGS LLC

Inventor： Scott David Rewerts ,  Jason C. Bell ,  Mark Emil Lundstrom

IPC: B64D9/00 ,  B64C1/06 ,  B64C1/14 ,  B64C1/20 ,  B64C1/22 ,  B64C3/32 ,  B64C3/34 ,  B64C17/08 ,  B64D37/04 ,  B64F1/32 ,  F03D13/40

CPC classification number: B64D9/003 ,  B64C1/0683 ,  B64C1/1415 ,  B64C1/20 ,  B64C1/22 ,  B64C3/32 ,  B64C3/34 ,  B64C17/08 ,  B64D9/00 ,  B64D37/04 ,  B64F1/32 ,  F03D13/40 ,  B64D2009/006 ,  F05B2260/02

Abstract: A fixed-wing cargo aircraft having a kinked fuselage to extend the useable length of a continuous interior cargo bay while still meeting a tailstrike requirement is disclosed. The fuselage defines a continuous interior cargo bay along a majority of its length and a pitch axis about which the cargo aircraft rotates during takeoff while still on the ground. The fuselage includes a forward portion defining longitudinal-lateral plane of the cargo aircraft an aft portion extending aft from the pitch axis to the aft end and containing an aft region of the continuous interior cargo bay that extends along a majority of a length of the aft portion. The aft portion has a centerline extending above the forward upper surface of the aircraft.

公开(公告)号：US11834169B2

公开(公告)日：2023-12-05

申请号：US17652355

申请日：2022-02-24

Applicant: Airbus Operations Limited

Inventor： William Tulloch

IPC: B64C3/34 ,  B64C3/18 ,  B64D37/30

CPC classification number: B64C3/34 ,  B64C3/185 ,  B64D37/30

Abstract: An aircraft wingbox assembly is disclosed having a wingbox with an upper cover, a lower cover and a pair of spars; a plurality of ribs in the wingbox. The ribs divide the wingbox into bays. A fuel tank is in a first one of the bays. One of the spars includes a spar hole which is configured to enable the fuel tank to be removed from the first one of the bays through the spar hole.

公开(公告)号：US11713187B2

公开(公告)日：2023-08-01

申请号：US17343568

申请日：2021-06-09

Applicant: OMNI TANKER TECHNOLOGY PTY LTD (ACN 135 294 772)

Inventor： William Rodgers

IPC: B29C41/20 ,  B65D90/02 ,  B32B27/12 ,  B32B1/02 ,  B29C70/32 ,  B60P3/22 ,  B32B27/30 ,  B32B27/38 ,  B32B27/32 ,  B32B27/40 ,  B62D29/04 ,  B32B7/04 ,  B32B27/36 ,  B32B27/00 ,  B29C39/08 ,  B29C33/62 ,  B29C39/10 ,  B29C39/12 ,  B29C39/36 ,  B60K15/03 ,  B64C3/34 ,  B65D88/12 ,  B29L31/30 ,  B29L31/00 ,  B29C45/14

CPC classification number: B65D90/022 ,  B29C33/62 ,  B29C39/08 ,  B29C39/10 ,  B29C39/123 ,  B29C39/36 ,  B29C41/20 ,  B29C70/323 ,  B32B1/02 ,  B32B7/04 ,  B32B27/00 ,  B32B27/12 ,  B32B27/302 ,  B32B27/304 ,  B32B27/306 ,  B32B27/308 ,  B32B27/32 ,  B32B27/36 ,  B32B27/38 ,  B32B27/40 ,  B60K15/03 ,  B60P3/2205 ,  B62D29/043 ,  B62D29/046 ,  B64C3/34 ,  B65D88/12 ,  B29C2045/14319 ,  B29L2031/3085 ,  B29L2031/7126 ,  B29L2031/7172 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2439/40 ,  B32B2605/00 ,  B32B2605/18 ,  B60K2015/03032 ,  B60K2015/03046 ,  B65D88/128 ,  Y02T50/40 ,  Y10T428/1362 ,  Y10T428/249921 ,  Y10T428/3154 ,  Y10T428/31511 ,  Y10T428/31544 ,  Y10T428/31587 ,  Y10T428/31797 ,  Y10T442/387 ,  Y10T442/3854 ,  Y10T442/3878 ,  Y10T442/3886 ,  Y10T442/59

Abstract: An article manufactured in a mould and which comprises a structural composite of plastics layers, the article having a wall defining an internal space for holding contents therein; wherein, the wall is formed from at least two layers of plastics materials; wherein a first of said layers comprises a thermoplastics material and at least a second layer comprises a thermosetting resin and a fibrous layer.

公开(公告)号：US20230081133A1

公开(公告)日：2023-03-16

申请号：US17473701

申请日：2021-09-13

Applicant: The Boeing Company

Inventor： Justin Albright

IPC: B64C3/34 ,  B64C3/18 ,  B64C3/26 ,  B64D37/32

Abstract: Aircraft fuel tank joints and related methods. The aircraft fuel tank joints comprise a first structural member comprising a first joint face, a second structural member comprising a second joint face that is spaced apart from the first joint face by a gap, a sealant dam compressed between the first and second joint faces and defining the gap, a first sealant zone on a first side of the sealant dam within the gap, and a second sealant zone on a second side of the sealant dam within the gap. The sealant dam and the first and second zones of sealant substantially fill, and form three independent seals within, the gap. The methods comprise substantially filling the gap with the sealant dam, the first zone of sealant, and the second zone of sealant, and compressing the sealant dam between the first and second faces to the compressed thickness.

公开(公告)号：US20220388628A1

公开(公告)日：2022-12-08

申请号：US17340837

申请日：2021-06-07

Applicant: Textron Innovations Inc.

Inventor： Bradley P. Regnier ,  Zachary E. Dailey ,  Aaron Alexander Acee ,  Brian J. Cox

IPC: B64C3/34 ,  B64C29/00 ,  B64C3/18 ,  B64D37/30 ,  B64D37/04 ,  B64C1/06 ,  B64C1/18

Abstract: An aircraft includes a fuselage airframe and a wing airframe that is subject to flight loads. The fuselage airframe includes fore/aft floor beams having a plurality of floor intercostals laterally extending therebetween and fore/aft roof beams with a plurality of roof intercostals laterally extending therebetween. Each of a plurality of cabin frames extends generally vertically between respective floor and roof beams. The wing airframe includes forward and aft wing spars with a plurality of wing ribs extending therebetween. At least one fuel tank, that is configured to contain a pressurized fuel such as pressurized hydrogen fuel, integrally forms at least a portion of one of the beams, the intercostals, the frames, the spars and/or the ribs such that the fuel tank is subject to the flight loads.

公开(公告)号：US11352147B2

公开(公告)日：2022-06-07

申请号：US16533239

申请日：2019-08-06

Applicant: SHORT BROTHER PLC

Inventor： Stephen Walters ,  David Chivers

IPC: B64D37/32 ,  H01B17/38 ,  B64C3/34

Abstract: An isolator fitting for an opening in a metallic rib of an aircraft wing. The isolator fitting has first isolator mountable to the rib to position a first isolator opening in alignment with the opening of the rib. A second isolator is mountable to the rib and has a nut housing segment defining a second isolator opening to be positioned in alignment with the opening of the rib. A conduit extends between a first end and a second end, and a nut is mountable about an outer surface of the conduit to abut against the first isolator and mount the conduit thereto. The conduit is positionable to extend through the opening of the rib and through the first and second isolator openings to position the nut within the nut housing segment of the second isolator such that the nut housing segment is positioned between the nut and the rib.