公开(公告)号：US20240239473A1

公开(公告)日：2024-07-18

申请号：US18406989

申请日：2024-01-08

申请人： Airbus Operations GmbH

发明人： Dennis KREY ,  Steffen KLEEMIß ,  Christian JÜRDENS ,  Alexander HUBER

IPC分类号： B64C9/02 ,  B64C7/00

CPC分类号： B64C9/02 ,  B64C7/00

摘要： A wing 3 including a main wing 5, a slat 7, and a connection assembly 9 movably connecting the slat 7 to the main wing 5, wherein the slat 7 moves between a retracted position and an extended position, wherein the front spar 37 includes an aperture 41 for a slat track 17 and the main wing 5 comprises a track housing assembly 43 including a track housing 45 and a mounting device 47, wherein the track housing 45 is mounted to the front spar 37 at the aperture 41 by the mounting device 47 and extending from the front spar 37 to the interior 42 of the wing box 35, the track housing 45 receives the slat track 17.

公开(公告)号：US12017769B2

公开(公告)日：2024-06-25

申请号：US18109570

申请日：2023-02-14

申请人： Advanced Aircraft Company

发明人： William J. Fredericks ,  Weston M. Lewis

IPC分类号： B64C39/02 ,  B64C7/00 ,  B64C29/00 ,  B64D27/02 ,  B64D27/04 ,  B64D27/24 ,  B64U10/13 ,  B64U30/20 ,  B64U50/19 ,  F16F15/08

CPC分类号： B64C39/024 ,  B64C7/00 ,  B64C29/0033 ,  B64D27/02 ,  B64D27/04 ,  B64D27/24 ,  B64D27/026 ,  B64D2221/00 ,  B64U10/13 ,  B64U30/20 ,  B64U50/19 ,  F16F15/08

摘要： An unmanned aerial vehicle capable of VTOL operation can include: a vehicle body defining longitudinal and transverse directions and opposing longitudinal sides; a first support boom coupled to the vehicle body at a first transverse axis and extending outwardly from the opposing longitudinal sides; a second support boom coupled to the vehicle body at a second transverse axis positioned rearward from the first transverse axis and extending outwardly from the opposing longitudinal sides; a plurality of electric motors coupled to a one of the first and second support booms, at least two electric motors of the plurality of electric motors positioned on each of the first and second support booms, a rotation axis of each of the at least two electric motors coupled to the second support boom offset in a transverse direction from a rotation axis of each of the at least two adjacent electric motors coupled to the first support boom; a plurality of rotors; and a propulsion system.

公开(公告)号：US11976226B2

公开(公告)日：2024-05-07

申请号：US17652048

申请日：2022-02-22

申请人： The Boeing Company

发明人： Eric K. Moyer

IPC分类号： C09J7/35 ,  B29C65/48 ,  B32B37/12 ,  B32B38/00 ,  B32B38/10 ,  B64C7/00 ,  C09J5/06 ,  C09J7/10 ,  C09J7/40

CPC分类号： C09J7/35 ,  B64C7/00 ,  C09J5/06 ,  C09J7/10 ,  C09J7/401 ,  B29C65/485 ,  B32B37/12 ,  B32B37/1207 ,  B32B38/0004 ,  B32B38/10 ,  B32B2605/18 ,  C09J2203/35 ,  C09J2427/005 ,  C09J2481/00 ,  C09J2483/00 ,  C09J2483/005

摘要： Described herein are methods of forming uncured sealant assemblies and also methods of forming seals between various parts using such assemblies. In some examples, an uncured sealant assembly comprises two protective layers and an uncured sealant layer, disposed in between. The uncured sealant assembly is stored and provided at a cure-inhibiting temperature, selected to minimize the curing rate of the uncured sealant layer. The size and the shape of the uncured sealant layer are specifically selected to ensure the complete coverage of the faying surfaces, filling of all gaps and voids between the faying surfaces, and controlling the shape and size of uncured sealant squeeze out between the faying surfaces. In some examples, the size and shape of the uncured sealant layer maybe be specifically selected to have no uncured sealant squeeze out between parts.

公开(公告)号：US11932376B2

公开(公告)日：2024-03-19

申请号：US18081204

申请日：2022-12-14

申请人： BOMBARDIER INC.

发明人： Stephen Colavincenzo ,  Mark Huising ,  Stephane Brunet

IPC分类号： B64C1/40 ,  B64C7/00 ,  G10K11/172

CPC分类号： B64C1/403 ,  B64C7/00 ,  G10K11/172

摘要： A noise attenuating device for reducing acoustic resonance in a cavity of an aircraft with an opening in a skin of the aircraft defining a first surface area and an opening peripheral edge includes a connection mechanism for securing the noise attenuating device in proximity to the opening in the skin of the aircraft and an exterior surface. The exterior surface defines a second surface area that is less than the first surface area of the opening and a device peripheral edge, which has a first section having an edge profile complimentary to at least a portion of the opening peripheral edge and a second section having an indented edge profile in relation to the first section such that when the noise attenuating device is secured within the opening, at least one gap is formed between the device peripheral edge and the opening peripheral edge.

公开(公告)号：US11891237B2

公开(公告)日：2024-02-06

申请号：US17202167

申请日：2021-03-15

申请人： Biosphere Aerospace, LLC

发明人： Elie Helou, Jr.

IPC分类号： B65D88/00 ,  B65D90/00 ,  B65D88/14 ,  B64D9/00 ,  B65D88/02 ,  B60P3/00 ,  B64C1/06 ,  B64C1/22 ,  B64C7/00 ,  B60P1/64 ,  B64C1/00

CPC分类号： B65D88/005 ,  B60P3/00 ,  B64C1/064 ,  B64C1/22 ,  B64C7/00 ,  B64D9/00 ,  B64D9/003 ,  B65D88/022 ,  B65D88/14 ,  B65D90/0026 ,  B60P1/6418 ,  B64C2001/0045 ,  B64C2211/00 ,  B65D90/0013

摘要： Disclosed are apparatus, systems, and methods, including a cargo transport system comprising a spine assembly, a container assembly, and an outer fairing. The spine assembly comprises a rigid spine and a plurality of mounts arranged on the rigid spine in a plurality of mount rows. The container assembly comprises a plurality of containers secured to the spine assembly using at least a subset of the plurality of mounts. The outer fairing at least partially encloses the container assembly. Each container of the plurality of containers comprises a plurality of fittings for securing the container to the spine assembly and/or another container of the container assembly. The container assembly is enclosed within a pressurization space for pressurizing the container assembly.

公开(公告)号：US20230365256A1

公开(公告)日：2023-11-16

申请号：US18227310

申请日：2023-07-28

申请人： Joby Aero, Inc.

发明人： Gregor Veble Mikic ,  Alex Stoll ,  JoeBen Bevirt

IPC分类号： B64C29/00 ,  B64C7/00 ,  B64C27/52 ,  B64C3/38

CPC分类号： B64C29/0033 ,  B64C3/38 ,  B64C7/00 ,  B64C27/52 ,  B64C1/068

摘要： The aircraft can include: an airframe, a tilt mechanism, a payload housing, and can optionally include an impact attenuator, a set of ground support members (e.g., struts), a set of power sources, and a set of control elements. The airframe can include: a set of rotors and a set of support members. By utilizing a larger rotor blade area (and/or larger rotor disc area) and adjusting the blade pitch and RPM, the rotors can augment the lift generated by the aerodynamic profile of the aircraft in the forward flight mode in addition to providing forward thrust. Variants generating lift with the rotors can reduce or eliminate additional control surfaces (e.g., wing flaps, ailerons, ruddervators, elevators, rudder, etc.) on the aircraft since the thrust and motor torque is controllable (thereby indirectly controlling lift) at each rotor, thereby enabling pitch, yaw, and/or roll control during forward flight.

公开(公告)号：US11807383B2

公开(公告)日：2023-11-07

申请号：US17556235

申请日：2021-12-20

申请人： ROLLS-ROYCE plc

发明人： Eric W Dean

IPC分类号： B64D37/04 ,  B64C7/00

CPC分类号： B64D37/04 ,  B64C7/00

摘要： A hydrogen-fuelled aircraft 200 comprises a fuselage, wings and a plurality of cylindrical elongate hydrogen storage tanks mounted on the exterior of the fuselage and disposed vertically above a plane containing the wing-tips of the aircraft. An aerodynamic fairing forms a continuous air-washed surface of the aircraft together with a lower portion of the fuselage. The hydrogen storage tanks extend generally parallel to the fuselage and are contained between the fairing and the fuselage. The aircraft provides for storage of a large volume of compressed hydrogen without compromising the volume of usable space within the fuselage. The aircraft is able to carry out flight missions comparable in range and payload to those of an equivalent conventionally-fuelled aircraft.

公开(公告)号：US20230340279A1

公开(公告)日：2023-10-26

申请号：US18345193

申请日：2023-06-30

申请人： THE BOEING COMPANY

发明人： Patrick J. KINLEN ,  Dimitris PRIFTIS

IPC分类号： C09D5/24 ,  C09D7/65 ,  C09D7/20 ,  B64C7/00 ,  C09D129/14 ,  C09D133/04 ,  C09D163/00 ,  C09D167/00 ,  C09D171/12 ,  C09D175/04 ,  C09D181/04

CPC分类号： C09D5/24 ,  C09D7/65 ,  C09D7/20 ,  B64C7/00 ,  C09D129/14 ,  C09D133/04 ,  C09D163/00 ,  C09D167/00 ,  C09D171/12 ,  C09D175/04 ,  C09D181/04 ,  B64D15/12

摘要： The present disclosure provides methods of coating a substrate. A method includes depositing a conductive coating including an electrically conductive material over the substrate to form a conductive layer having a sheet resistivity of about 10Ω/□ to about 1000Ω/□. The method includes depositing an anti-icing layer comprising nanomaterials over the conductive layer to form a coating system.

公开(公告)号：US11780584B2

公开(公告)日：2023-10-10

申请号：US17527493

申请日：2021-11-16

申请人： The Boeing Company

发明人： Steven Ellis Rhynard ,  Joe Files

IPC分类号： B64D11/00 ,  B64C7/00

CPC分类号： B64D11/003 ,  B64C7/00

摘要： An assembly configured to be mounted within an interior of a vehicle. The assembly includes a monument wall configured to be mounted in the interior of the vehicle. A panel is configured to attach to a support structure above the monument wall with the panel having a first edge and a second edge. A latch configured to be mounted to the panel between the first edge and the second edge. A pull member is attached to the panel and comprises an elongated member attached to the latch and a handle. A translating hinge is configured to be mounted to the second edge of the panel to provide for translating and pivoting movement of the panel within an access area between the monument wall and the support structure to connect and disconnect the panel from the support structure.

公开(公告)号：US20230312079A1

公开(公告)日：2023-10-05

申请号：US17713773

申请日：2022-04-05

申请人： Rohr, Inc.

发明人： Rosa Gonzalez ,  Aleksandar Ratajac

IPC分类号： B64C7/00 ,  B64D27/26 ,  F16B5/01

CPC分类号： B64C7/00 ,  B64D27/26 ,  F16B5/01 ,  B64D2027/262

摘要： A wall structure is provided for an aircraft. This wall structure includes a first wall section, a second wall section and a fastener system fastening the second wall section to the first wall section. The second wall section includes an aperture extending axially along an axis through the second wall section. The second wall section is axially spaced from the first wall section. The fastener system includes a mount and a retainer. The mount is connected to the first wall section. The mount includes a post that projects axially into the aperture. The retainer includes a head and a spring clip connected to the head. The head axially engages the second wall section. The spring clip is disposed in the aperture and is mated with the post.