公开(公告)号：US20200339271A1

公开(公告)日：2020-10-29

申请号：US16856346

申请日：2020-04-23

Applicant: Airbus Operations Limited

Inventor： William TULLOCH ,  Pat BROOMFIELD

IPC: B64D29/02 ,  F16B5/02

Abstract: A component which is configured to be joined to a further component in a preselected relative orientation is disclosed. The further component has an interface surface and the component is configured to contact the interface surface when joined to the further component. The component includes a surface disposed on a side of the component intended to face the interface surface when the components are joined, a plurality of recesses formed in the surface, and a plurality of spacer elements. Each recess has a preselected orientation relative to the component, the preselected orientation being selected in dependence on the preselected relative orientation. Each spacer element comprises a contact surface configured to contact the interface surface when the components are joined. Each spacer element is disposed in one of the recesses such that the orientation of a given contact surface is defined by the orientation of the corresponding recess.

公开(公告)号：US20200331589A1

公开(公告)日：2020-10-22

申请号：US16389686

申请日：2019-04-19

Applicant: Darold B. Cummings

Inventor： Darold B. Cummings

IPC: B64C15/00 ,  B64D27/26 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  B64D27/12 ,  B64D27/14 ,  B64C7/02

Abstract: An aircraft having a fuselage with a nose and a flat tail at opposite ends and a pair of wings extending therefrom. A pair of nacelles are detachably connected to the top of respective ones of the wings to be spaced from the fuselage to establish an air flow space therebetween, Each wing-mounted nacelle includes a plurality of fans, a corresponding plurality of electric motors to drive the fans, and dividers that separate the fans from one another. Each wing-mounted nacelle also includes a pair of rotatable air inlet slats at an air intake end and a pair of rotatable air exhaust flaps at an air exhaust end that are rotated relative to one another to control horizontal propulsive thrust, thrust vectoring and thrust reversing of the aircraft. A third nacelle is mounted on top of the flat tail of the fuselage between a pair of horizontal turbo generators.

公开(公告)号：US20200277061A1

公开(公告)日：2020-09-03

申请号：US16706996

申请日：2019-12-09

Applicant: Pratt & Whitney Canada Corp.

Inventor： Frank Becker ,  Xi Wang ,  Antonio Pizzi ,  Charles E. Lents

IPC: B64D27/02 ,  B64D27/24 ,  B60L50/60 ,  B64D29/02 ,  B64D37/04 ,  B60L50/64 ,  H01M2/10

Abstract: An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. The aircraft includes an electrical system having an electric storage. The electric storage is positioned within the fuselage.

公开(公告)号：US20200156799A1

公开(公告)日：2020-05-21

申请号：US16197096

申请日：2018-11-20

Applicant: ROHR, INC.

Inventor： Steven Micallef

IPC: B64D29/06 ,  E05B41/00 ,  E05C19/14 ,  B64D29/02

Abstract: A high visibility panel latch may comprise a latch handle coupled to a latch mechanism, wherein the latch handle comprises a visibility feature. The visibility features may comprise a portion of at least a first face and a second face of the latch handle. The visibility features may comprise a painted channel.

公开(公告)号：US20200070992A1

公开(公告)日：2020-03-05

申请号：US16539350

申请日：2019-08-13

Applicant: Airbus Operations S.A.S.

Inventor： Thierry Theron

IPC: B64D29/02 ,  B64F5/40

Abstract: A central fairing of a pylon of an aircraft including: at least one opening to allow access to beneath the central fairing, an articulated panel that is able to move between a closed position in which the articulated panel blocks the opening and an open position in which the articulated panel at least partially frees the opening, at least one articulation for permanently connecting the articulated panel to at least one fixed element, and—at least one locking system for holding the articulated panel in the closed position. Since the articulated panel is always connected to the aircraft, it can be made larger since it is no longer carried by the operator. Consequently, the opening can be blocked with a single articulated panel.

公开(公告)号：US20200062375A1

公开(公告)日：2020-02-27

申请号：US16546631

申请日：2019-08-21

Applicant: The Boeing Company

Inventor： Thomas J. Connelly ,  Linda M. Li

IPC: B64C3/36 ,  B64D29/02 ,  B64C1/12 ,  B64C1/40

Abstract: A method for stiffening a skin panel of a heat shield assembly comprises steps of forming a blank into a stiffener, which includes a base portion and a bead portion that protrudes from the base portion, and connects the base portion to the skin panel.

公开(公告)号：US10539180B2

公开(公告)日：2020-01-21

申请号：US15448136

申请日：2017-03-02

Applicant: Bell Helicopter Textron Inc.

Inventor： Nick Pravanh ,  Michael E. Rinehart ,  Bart Shafer ,  Clegg Smith ,  Jeffrey M. Williams

IPC: F16C29/00 ,  B64C29/00 ,  B64D29/02 ,  F01D15/12 ,  F01D15/02 ,  E05D15/06

Abstract: A door roller mechanism for cooperation with a roller track including a carriage member having a door attachment feature; at least one roller disposed for rotation on a first side of the carriage member when the carriage member moves in the rolling direction; at least one roller disposed for rotation on an opposite second side of the carriage member when the carriage member moves in the rolling direction; a first rub member disposed on the first side of the carriage; a second rub member disposed on the second side of the carriage; and at least one biasing element disposed on the carriage member for resiliently biasing the first rub member and the second rub member in opposite lateral directions so as to contact a respective first track surface and a second track surface in a manner to dampen lateral vibration of a door connected to the roller mechanism.

公开(公告)号：US10464668B2

公开(公告)日：2019-11-05

申请号：US15456450

申请日：2017-03-10

Applicant: Jetoptera, Inc.

Inventor： Andrei Evulet

IPC: B64C29/04 ,  B64C39/12 ,  B64D27/20 ,  B64C11/00 ,  B64C39/02 ,  B64C9/38 ,  B64C15/00 ,  B64C21/00 ,  B64C29/02 ,  B64D27/10 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04

Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

公开(公告)号：US10436150B2

公开(公告)日：2019-10-08

申请号：US16017774

申请日：2018-06-25

Applicant: Rohr, Inc.

Inventor： Michael Ray Aten ,  Sara Crawford

IPC: F02K1/82 ,  F02K1/72 ,  F02K1/56 ,  B64D29/02 ,  B64D33/04 ,  F02K1/54

Abstract: A nacelle is configured to be coupled to an underside of a wing and forms a clearance space between the nacelle and a leading edge slat of the wing. A portion of an outlet cowling moves longitudinally aft when a reverse thrust configuration is activated and the leading edge slat is deployed toward the nacelle. The outlet cowling also includes another portion located adjacent to the leading edge slat that does not move when the reverse thrust configuration is activated and thus maintains its clearance space from the leading edge slat.

公开(公告)号：US20190118958A1

公开(公告)日：2019-04-25

申请号：US16221397

申请日：2018-12-14

Applicant: JETOPTERA, INC.

Inventor： Andrei Evulet

IPC: B64D29/02 ,  B64C39/02 ,  B64C15/00 ,  B64C21/04 ,  B64D27/18 ,  B64D33/02 ,  B64D33/04 ,  B64C9/38 ,  B64D27/10 ,  B64C21/00

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.