Method for opening/closing an aircraft electric door for a pressurized airframe and door for implementing same

US9816307B2 · US · B2

Patent metadata
FieldValue
Publication numberUS-9816307-B2
Application numberUS-201314443080-A
CountryUS
Kind codeB2
Filing dateNov 14, 2013
Priority dateNov 16, 2012
Publication dateNov 14, 2017
Grant dateNov 14, 2017

How to read this patent

A practical reading order for non-experts. Skip the full description unless you need deep technical detail.

  1. Title

    What the patent document calls the invention.

  2. Abstract

    A short plain-language summary of the technical disclosure.

  3. Assignees and inventors

    Who owns or filed the patent and who is credited as inventor.

  4. Key dates

    Filing, priority, publication, and grant dates set the timeline.

  5. First independent claim

    The legal scope of protection — read this for what is actually claimed.

  6. CPC / IPC classifications

    Technology tags used to group this patent with similar filings.

  7. Citations and related patents

    Prior art links and similar publications in this corpus.

Abstract

Official abstract text for this publication.

An aircraft electric door including a locking system for actuating a safety catch for locking the door, a system for moving the door between open and closed positions, and a single electric motor for actuating both the locking system and the system for moving the door.

First claim

Opening claim text (preview).

The invention claimed is: 1. An aircraft electric door for a pressurized airframe ( 1 ) comprising: a locking system (S 4 ) for actuating a safety catch ( 43 , 4 a , 4 b ); a moving system for opening and closing the door ( 110 , 200 , 300 ); and a single electric motor ( 2 , 21 , 210 ) for actuating both the locking system and the moving system; the moving system is activated by a door computer ( 3 ) and includes a cylindrical support ( 50 , 501 , 502 ) and a fixed guide ( 9 , 91 , 92 ), the cylindrical support is rotated by the electric motor ( 2 ); wherein the support ( 50 ) has a guideway ( 51 , 511 , 512 ) linked to a door arm ( 6 ) of the door, the guideway ( 51 , 511 , 512 ) is partially helical along a vertical rotation axis (Z′Z) of the support ( 50 , 501 , 502 ); wherein the door arm ( 6 ) is supported by and pivots around a vertical hinge ( 61 ) and is linked with door lifting devices ( 7 a , 7 b , 8 , 62 ), the door lifting devices are mounted between a shaft of the safety catch ( 43 ) and the door arm ( 6 ); wherein the fixed guide ( 9 , 91 , 92 ) includes a vertical camway ( 9 v , 91 v , 92 v ) and a horizontal camway ( 9 h , 91 h , 92 h ) to guide the door arm ( 6 ) as the door is moved by the single motor between an open position and a closed position, the horizontal camway is configured to prevent the door arm ( 6 ) from being vertically lowered in at least one position of the door arm between the open and closed positions of the door, and the vertical camway is configured prevent the door arm ( 6 ) from pivoting in at least another position of the door arm between the open and closed positions of the door; and wherein the cylindrical support is a rotatable sleeve ( 50 ), the fixed guide surrounds the rotatable sleeve, and a pair of guiding sliders ( 63 a , 63 b ) operatively link the vertical and horizontal camways to the guideway. 2. The aircraft electric door as claimed in claim 1 , wherein the door lifting devices ( 7 a ) are engageable with lifting ramps ( 7 b ) for multiplying an initiating force for lifting the door ( 1 ). 3. The aircraft electric door as claimed in claim 2 , wherein lifting levers ( 40 ) are placed at distal ends of the safety catch shaft ( 43 ). 4. The aircraft electric door as claimed in claim 1 , further including a triggering device for unlocking the safety catch, the triggering device includes a handle ( 4 ) associated with a sensor (C 1 ) for detecting when the handle is in and end position and a push-button (B 4 ) for sending an electrical signal to the door computer ( 3 ). 5. The aircraft electric door as claimed in claim 4 , wherein the safety catch ( 43 , 4 a , 4 b ) comprises locks ( 41 ) mounted on a lock shaft ( 42 ), and the locks are engagable with counter-locks ( 44 ) mounted on the safety catch shaft ( 43 ). 6. The aircraft electric door as claimed in claim 1 , further including position sensors (C 2 , C 3 , C 4 ) linked with the door computer ( 3 ). 7. The aircraft electric door as claimed in claim 1 , wherein the horizontal camway ( 9 h ) of the fixed guide ( 9 ) is a raised edge of the fixed guide.

Assignees

Inventors

Classifications

  • for doors · CPC title

  • using electrical actuators · CPC title

  • Passenger doors · CPC title

  • B64C1/1407Primary

    Doors; surrounding frames · CPC title

  • Safety devices, e.g. detection of obstructions or end positions · CPC title

Patent family

Related publications grouped by family.

External sources

Frequently asked questions

Answers are generated from the same data shown on this page.

What does patent US9816307B2 cover?
An aircraft electric door including a locking system for actuating a safety catch for locking the door, a system for moving the door between open and closed positions, and a single electric motor for actuating both the locking system and the system for moving the door.
Who is the assignee on this patent?
Latecoere
What technology area does this patent fall under?
Primary CPC classification B64C1/1407. Mapped technology areas include Operations & Transport.
When was this patent published?
Publication date Tue Nov 14 2017 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
What related patents are in patentsdb?
We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).