公开(公告)号：US20240351697A1

公开(公告)日：2024-10-24

申请号：US18643483

申请日：2024-04-23

Applicant: Airbus Operations SAS

Inventor： Laurent CAZEAUX ,  Laurent CALIMAN ,  Nicolas CHARTON

IPC: B64D29/02

CPC classification number: B64D29/02

Abstract: An internal fixed structure for a nacelle, comprising end panels, an intermediate panel in the form of a half-cylinder between the end panels, splice plates between the intermediate panel and each end panel, wherein each splice plate is made up of a skin with an inner face fastened to the panels and at least one indentation protruding with respect to an outer face, and a pad fastened to each fastening surface of an indentation, wherein each pad of the upper splice plate bears against a surface of an engine pylon, and wherein each pad of the lower splice plate bears against a pad of a lower splice plate of another internal fixed structure.

公开(公告)号：US20240228053A1

公开(公告)日：2024-07-11

申请号：US18235311

申请日：2023-08-17

Applicant: JETOPTERA, INC.

Inventor： Andrei Evulet

IPC: B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C39/02 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  B64U30/00 ,  B64U30/10 ,  F02C3/04 ,  F02C6/04 ,  F02K1/00 ,  F02K1/36

CPC classification number: B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C23/005 ,  B64C39/024 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  F02C3/04 ,  F02C6/04 ,  F02K1/002 ,  F02K1/36 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/16 ,  B64D2033/0273 ,  B64U30/00 ,  B64U30/10 ,  F05D2220/90 ,  Y02T50/10 ,  Y02T50/30 ,  Y02T50/40

Abstract: A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

公开(公告)号：US12006052B2

公开(公告)日：2024-06-11

申请号：US17972919

申请日：2022-10-25

Applicant: General Electric Company ,  General Electric Deutschland Holding GmbH

Inventor： Satish Prabhakaran ,  Mohamed Osama

IPC: B64D27/02 ,  B64D27/12 ,  B64D29/02 ,  B64D31/00

CPC classification number: B64D31/00 ,  B64D27/12 ,  B64D29/02 ,  B64D27/026 ,  B64D2221/00

Abstract: A vehicle includes a gas turbine engine having at least two spools and an associated power system. The power system includes two independent power subsystems, including a first power subsystem for managing power transfer between spools and a second power subsystem for supplying a base power load to the vehicle. The first power subsystem has a first electric machine mechanically coupled with a first spool of the gas turbine engine and a second electric machine mechanically coupled with a second spool. The second electric machine is electrically coupled with the first electric machine such that electrical power is transmittable therebetween. The second power subsystem has a third electric machine mechanically coupled with one of the spools. The third electric machine is electrically coupled with a load positioned offboard the gas turbine engine. The first power subsystem and the second power subsystem are electrically decoupled from one another.

公开(公告)号：US20240174369A1

公开(公告)日：2024-05-30

申请号：US18514928

申请日：2023-11-20

Applicant: Rolls-Royce Deutschland Ltd & Co KG

Inventor： Johannes Gabriel Bauer

IPC: B64D29/02 ,  B64C29/00 ,  B64D33/08

CPC classification number: B64D29/02 ,  B64C29/0033 ,  B64D33/08 ,  B64D27/24

Abstract: A nacelle apparatus for a vertical take-off and landing (VTOL) aircraft includes a drive apparatus connected to a wing of the VTOL aircraft via a pylon apparatus and is configured to be pivoted relative to the pylon apparatus about a rotation axis between a propulsion position and a lift position. The nacelle apparatus further includes an air-conducting device having a first inlet opening on the pylon apparatus arranged in the region in which the first air flow strikes the pylon apparatus and a second inlet opening arranged on the nacelle apparatus and/or on the pylon apparatus so that a second air flow is configured to flow in through the second inlet opening in the propulsion position. The air-conducting device further includes an air distribution device with which the flowing air quantities from the first and second inlet openings are configured to be controlled inside the nacelle apparatus.

公开(公告)号：US20240010349A1

公开(公告)日：2024-01-11

申请号：US18037429

申请日：2022-04-21

Applicant: LEONARDO S.P.A.

Inventor： Franco Alfio DI MARIA

IPC: B64D29/02 ,  F16B5/02

CPC classification number: B64D29/02 ,  F16B5/02

Abstract: An assembly for removably mounting an underwing pylon to a rib of an aircraft wing is provided. The assembly has a prismatic body insertable into a prismatic cavity of the underwing pylon, a threaded retaining element having an upwardly tapered outer conical surface, and a vertical threaded pin inserted through a vertical through hole of the prismatic body. The assembly has an anti-rotation device for rotationally locking the threaded retaining element to the prismatic body relative to a vertical axis.

公开(公告)号：US11814184B2

公开(公告)日：2023-11-14

申请号：US17532813

申请日：2021-11-22

Applicant: Airbus Operations SAS

Inventor： José Goncalves

IPC: B64D29/06 ,  B64D29/08 ,  F16B5/02 ,  B64D29/00 ,  B64D7/02 ,  B64D29/02

CPC classification number: B64D29/06 ,  B64D29/08 ,  F16B5/0208 ,  F16B5/0266 ,  B64D7/02 ,  B64D29/00 ,  B64D29/02

Abstract: An assembly of a pylon and of a nacelle of an aircraft, wherein the nacelle has a structure, a visor, two centering systems and two tensioning systems. Each tensioning system comprises a first fitting, which is attached to the structure and has an engagement wall through which an orifice passes, a second fitting, which is attached to the visor, a threaded rod that is articulated on the second fitting and passes through the orifice, a spring element fitted on the threaded rod against the opposite face of the engagement wall from the second fitting, and an arresting means that blocks the spring element. Each centering system comprises a first fitting, which is attached to the structure and has a bore, and a second fitting, which is attached to the visor and bears a shaft that is accommodated in the bore.

公开(公告)号：US11781482B2

公开(公告)日：2023-10-10

申请号：US17465959

申请日：2021-09-03

Applicant: The Boeing Company

Inventor： John F. Summers

IPC: F02C7/20 ,  B64D27/18 ,  B64D29/02 ,  B64D33/04 ,  F02C7/24

CPC classification number: F02C7/20 ,  B64D27/18 ,  B64D29/02 ,  B64D33/04 ,  F02C7/24 ,  F05D2220/323 ,  F05D2260/231

Abstract: A heat shield assembly for use with an aircraft engine. The heat shield assembly includes a structural member, a heat shield panel adapted for exposure to aircraft engine exhaust, an index joint coupling the heat shield panel to the structural member in a fixed positional location, and a plurality of slip joints coupling the heat shield panel to the structural member. Each slip joint includes at least one wear buffer coupled to the heat shield panel, and a slip fastener insertable through a slip joint hole in the heat shield panel with a clearance fit. A gap defined by the clearance fit is sized to provide a tolerance for expansion and contraction of the heat shield panel relative to the fixed positional location, and the at least one wear buffer is engageable by the slip fastener during expansion and contraction of the heat shield panel.

公开(公告)号：US11772806B2

公开(公告)日：2023-10-03

申请号：US17262631

申请日：2019-07-10

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Geoffrey Richard Williams ,  Ross Salisbury ,  Antony Peacock

IPC: B64D29/02 ,  B64C7/02 ,  B64D27/18 ,  B64D33/02

CPC classification number: B64D29/02 ,  B64C7/02 ,  B64D27/18 ,  B64D33/02 ,  B64D2033/0226 ,  B64D2033/0273

Abstract: An aircraft engine nacelle for coupling to a wing of an aircraft is disclosed having a fore end, and an aft end that is immoveable relative to the fore end. The aft end includes a major axis Mj and a minor axis Mi, and the nacelle is configured such the minor axis Mi is closer to vertical V than the major axis Mj when the nacelle is coupled to the wing and the aircraft is stationary on the ground. An aircraft system and an aircraft are disclosed each including the aircraft engine nacelle.

公开(公告)号：US11753174B2

公开(公告)日：2023-09-12

申请号：US16878580

申请日：2020-05-19

Applicant: Pratt & Whitney Canada Corp.

Inventor： Pierre Bertrand ,  Jean Thomassin

IPC: B64D27/24 ,  B64D27/12 ,  B64D29/02 ,  B64D27/02

CPC classification number: B64D27/24 ,  B64D27/12 ,  B64D29/02 ,  B64D2027/026

Abstract: The aircraft includes a fuselage and at least one wing extending from the fuselage. The wing includes first and second original portions and a plug portion positioned between the first and second original portions. A propulsion system is positioned on the at least one wing. The propulsion system includes at least one electric powerplant and at least one combustion powerplant. Each powerplant delivers power to a respective air mover for propelling the aircraft. The electric powerplant and/or the combustion powerplant is positioned outboard from the plug portion. A method for retrofitting an aircraft includes segmenting a wing of an aircraft into two original portions, positioning a plug portion between the two original portions, and connecting the plug portion to one of the two original portions, the first nacelle and/or the second nacelle.

公开(公告)号：US11718403B2

公开(公告)日：2023-08-08

申请号：US14687277

申请日：2015-04-15

Applicant: Northrop Grumman Systems Corporation

Inventor： Kyle Rahrig ,  Geoffrey Sommer ,  Barnaby S. Wainfan

IPC: B64C39/06 ,  B64C11/00 ,  B64D29/02 ,  F02K1/34 ,  B64C15/14 ,  B64D35/08

CPC classification number: B64C39/066 ,  B64C11/001 ,  B64C15/14 ,  B64D29/02 ,  B64D33/06 ,  B64D35/08 ,  Y02T50/40 ,  Y02T50/60

Abstract: An extremely quiet short take-off and landing (STOL) aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage in an orientation that is rotated relative to the typical orientation on a helicopter. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; channel shrouds surrounding at least one of the engine systems; and a ducted fan thruster positioned on the fuselage. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system, the engine system comprising two engine dual packs; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage.