WO2013172804A1 - Mécanisme de verrouillage de porte - Google Patents

Mécanisme de verrouillage de porte Download PDF

Info

Publication number
WO2013172804A1
WO2013172804A1 PCT/TR2013/000145 TR2013000145W WO2013172804A1 WO 2013172804 A1 WO2013172804 A1 WO 2013172804A1 TR 2013000145 W TR2013000145 W TR 2013000145W WO 2013172804 A1 WO2013172804 A1 WO 2013172804A1
Authority
WO
WIPO (PCT)
Prior art keywords
door
latch
shaft
identified
handle
Prior art date
Application number
PCT/TR2013/000145
Other languages
English (en)
Inventor
Ertong Lütfi̇
Yanginlar Süleyman
Kiziltan Ender
Ti̇moçin Burak
Varlik Erci̇yes Ömer
Şeran Onur
Original Assignee
Tusaş-Türk Havacilik Ve Uzay Sanayii A.Ş.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Tusaş-Türk Havacilik Ve Uzay Sanayii A.Ş. filed Critical Tusaş-Türk Havacilik Ve Uzay Sanayii A.Ş.
Publication of WO2013172804A1 publication Critical patent/WO2013172804A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B64C1/1407—Doors; surrounding frames
    • E—FIXED CONSTRUCTIONS
    • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
    • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
    • E05B15/00—Other details of locks; Parts for engagement by bolts of fastening devices
    • E05B15/0086—Toggle levers
    • E—FIXED CONSTRUCTIONS
    • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
    • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
    • E05B17/00—Accessories in connection with locks
    • E05B17/0025—Devices for forcing the wing firmly against its seat or to initiate the opening of the wing
    • E—FIXED CONSTRUCTIONS
    • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
    • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
    • E05B53/00—Operation or control of locks by mechanical transmissions, e.g. from a distance
    • E—FIXED CONSTRUCTIONS
    • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
    • E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
    • E05C9/00—Arrangements of simultaneously actuated bolts or other securing devices at well-separated positions on the same wing
    • E05C9/08—Arrangements of simultaneously actuated bolts or other securing devices at well-separated positions on the same wing with a rotary bar for actuating the fastening means

Definitions

  • This invention relates to a latch mechanism that allows for safe opening and closing of doors in aircraft during flight or at parking position.
  • latching mechanisms for doors opening inwards of an aircraft.
  • doors open outwards of the aircraft.
  • door handles are located in such a way to facilitate inwards of the aircraft's interior and cargo area, in the aircraft's section.
  • the door includes a latching system, a lock monitoring system, an up-lock used to secure the door in an open position, and an actuating system that assists in at least either of opening or closing the door.
  • the latching system works with the movement of the latching system components.
  • the latching system includes a monitoring device that prevents the aircraft from being pressurized in case of a malfunction in the latching system.
  • the latching system includes a lock system that prevents operation of the latch handle accidentally or by ground loading or flight forces.
  • the systems of the door are preferably manually operated, and utilize rigid elements. The purpose of this invention has been to access the cargo area of the aircraft, externally. The system is complicated and the gears have been utilized to transmit the motion of the mechanism.
  • the door includes a multitude of interconnecting components both at fuselage and door sides.
  • Each fuselage interconnecting component incorporates a pin and an eccentric rotary cylinder which can be attached to this pin.
  • Each door connection part includes an eccentric rotary handle, designed to wrap around at least one section of the rotary cylinder.
  • This document describes a lock mechanism that is used to open the aircraft door outwardly.
  • the latching system is employed at one side of the door and direct manual operation or electric motor can be used as moving mechanism.
  • the cylinders of the doors are needed to be pushed side wards, to allow complete latching.
  • the present invention provides latching with a much simpler mechanism, thanks to its design which is superior in many aspects than the above mentioned patent documents. As it is designed for use under literally any condition, it doesn't need any particular auxiliary mechanism. It is able to better respond to the door operator's needs, compared to those systems forming subject of the above mentioned inventions, in respect of latching safety. It does not pose any danger and risks to the user in respect of operation.
  • the preamble with this invention is to realize a door latch system that fully operates by mechanical means and yet facilitates operation under any circumstances, including but not limited to cases of emergency.
  • Another purpose intended with this invention is to realize a door latch system that can easily be manipulated in case of a malfunction, due to the simple system and parts design.
  • a further purpose of this invention is to realize a door latch system which eliminates all safety problems associated with pressurized doors.
  • a further purpose of this invention is to realize a door latch system that creates no risks for the door operator.
  • a further purpose of this invention is to realize a door latch system, wherein the door handle equipped uses the door surface instead of the cargo area.
  • Another purpose of this invention is to realize a door latch system that facilitates for detachment in order to enable coping up with the problem of icing on doors.
  • Another purpose of this invention is to realize a door latch system that enables the opening of the door getting stuck in position due to harsh ambient conditions, from its external surface by the use of manually applied force.
  • a door latch system realized to reach at the core purpose of this invention is shown in the attached figures, which include:
  • Figure 1- The perspective view of the door latch system.
  • Figure 2- The exploded view of the latching mechanism.
  • Figure 3- The front view of the latching mechanism on the door.
  • Figure 4- Perspective view of the latch and the latch guide.
  • FIG. 5 Perspective view of the latch mechanism inside the aircraft.
  • Figure 6- Front view of the outer handle from outside of the aircraft.
  • Figure 7 Side view of the latch mechanism in both latched and unlatched position.
  • Figure 8 Front view of the inner handle in unlatched inside the aircraft.
  • the components in the figures are individually enumerated, and the defined below on respective number basis.
  • the door latch mechanism (1) enabling safe opening and closing of doors in aircraft, which forms the subject of the present invention, includes:
  • At least one inner handle (2) enabling the opening of door with application of force from inside the aircraft, at least one Quick Release Pin (3) that prevents the door from being opened externally,
  • At least one outer handle (4) enabling the opening of door with application of force from outside the aircraft
  • At least one inner handle assembly (5) to which the inner handle (2) and outer handle (4) are attached reciprocally,
  • At least one sensor rod (6) that provides door open or closed warning signals and is attached to the inner handle assembly (5),
  • At least one inner handle assembly (7) which transmits the movements of the inner handle (2) and outer handle (4) to the sensor mechanism and is attached to the sensor rod (6),
  • At least one handle overcentering spring (8) attached to the Inner handle assembly (5), to force the inner handle (2) towards closing position first and opening position next, when the door is opening, and, towards opening position first and closing position next, when it is closing,
  • the latching system (9) that ensures the door's remaining sealed without getting affected by any mechanical failures and malfunctions as may occur during flight and is attached to the inner handle assembly (5) by mechanism rod,
  • At least one mechanism rod (10) that transmits the rotary motion generated by the inner handle assembly (5) to the latch assembly (9) through the inner (2) and outer handles (3) and interconnects the inner handle assembly (5) and the latch assembly (9),
  • At least one latch shaft (11) which is connected to the inner handle assembly (5) by shaft lever (14) and mechanism rod(10 at least one latch shaft bearing (12) that pulls all the stresses created during installation of the latch shaft (1 1) on the door frame and the use of it after that, at least one latch shaft bearing fitting (13) which attaches the latch shaft bearing (12) on to the door frame, - at least one shaft lever (14) that transmits the motion of inner handle (2) or outer handle (4) it receives through the mechanism rod (10) onto the latch shaft (1 1),
  • Teflon protection (16) which ensures that deflection of the latch shaft (11) remain in the safe range, when overload is applied from the inner handle (2) or outer handle (4) and is applied all around the latch shaft (1 1)
  • the latch (19) which functions as a lock in between the door and its frame through the latch shaft (1 1) and is fitted at both ends of the latch shaft (11), a lock warning piece (20) fitted at both ends of the latch shaft (11) which shows motion of inner handle (2) or outer handle (4) motions in open or closed status on the latch (19), and
  • the aircraft door latch mechanism (1) is found on the rear fuselage of the aircraft, so as to meet all kinds of ergonomic needs preplanned in its structure. Most aircraft employ doors opening outwards unlike the present invention, which open sliding inwards and then upwards.
  • the door latch mechanism (1) attaches the door frame to the aircraft fuselage at both sides of the door with a pair of latching assemblies (9). The latching process takes place in time of mechanical movement of the door. As the door latch mechanism (1) is automatically blocked under pressure, it eliminates all security concerns.
  • the door latch mechanism (1) facilitates for easy access and manipulation in case of a malfunction as well, due to its simple system and parts design.
  • This mechanism (1) enables opening of the door from its external surface when outer handle (4) is jammed/covered by ice due to harsh environmental conditions, by application of hand force.
  • the door latch mechanism (1) in its most generic embodiment, consists of two door handles one located internally and the other externally (2, 4), a latch shaft (1 1), two latch shaft bearings (12) and two latch guide (22) aligned opposite to each other.
  • the inner handle (2) rotates 90° clockwise.
  • the outer handle (4) does not rotate.
  • both the inner and outer handles (2, 4) move together.
  • the quick Release pin (3) is used to lock the mechanism (1) and prevent its future inadvertent operation, when the aircraft is at parking position. Before a flight, the quick release pin (3) should be removed from its place.
  • the door latch mechanism (1) is actuated by the inner handle (2), the latch (12) moves and takes latched position accordingly inside the latch guide (22).
  • the Inner handle assembly (5) transfers the rotational motion of the inner handle (2) or outer handle (4) to the latch assembly (9).
  • the sensor rod (6) is the component which triggers the motion of the sensor mechanism that provides the "door open” or “door closed” signals.
  • the target lever (7) is the component, which enables transfer of the movements of inner and outer handles (2, 4) to the sensor mechanism.
  • the handle overcentering spring (8) guarantees the door to be in position at either open or closed status. This handle overcentering spring (8) is always loaded with compression load.
  • the inner or outer handle (2, 4) shows the tendency of keeping the door in closed position if it's angle in the direction of opening the door is at or below 45° or, in open position if it's angle in the same direction is between 45° and 90°.
  • the handle overcentering spring (8) is the safety component that prevents the door from opening inadvertently, due to vibrations.
  • the mechanism rod (10) is a device that transmits the rotational motion produced by the motion of the inner handle assembly (5) from inner (2) or outer handle (4) to the latch shaft (11).
  • the latch shaft (1 1) ensures that movements of the latch assembly (1) are transferred to the latch (19).
  • the latch shaft bearing (12) carry the stresses as may occur both during the installation of the latch shaft (11) in its place on the door frame and during its use thereafter.
  • the latch shaft bearing fitting (13) is a U shaped member that wraps around the latch shaft bearing (12) and ensures that the bearing (12) fits firmly on the door frame.
  • the shaft lever (14) ensures that the door remains closed during a flight without being affected by mechanical failures, together with the centering spring (8).
  • the shaft lever (14) transmits the motion from the inner and outer handles (2, 4) that it receives from the mechanism rod (10) to the latch shaft (1 1).
  • the latch shaft overcentering spring (15) of the latch shaft is a safety component that prevents unintended opening of the door in time of flight, by ensuring the latch shaft (1 1) remain in locked position, in case the latch shaft (1 1) loses its connection with the inner or outer handles (2, 4).
  • the Teflon protection (16) is a system component that ensures that deflection of the latch shaft (1 1) to remain in a safe range, when jamming load is applied from the inner handle (2) or outer handle (4) and is transmitted through the latch shaft (1 1).
  • the side fitting (17) gets the stresses that the latch shaft (1 1) may form on the door frame and ensures successful housing of the latch shaft (1 1) on the door frame.
  • the centering ring (18) ensures axial centering of the latch shaft (11) on the door frame.
  • the bearing (12) inserted onto the latch shaft (1 1) is a component that transmits the motion inside the latch shaft bearing fitting (13).
  • the member which displays the open or closed position of the inner handle (2) and outer handle (4) over the latch (19) is a lock warning piece (20).
  • the lock warning window (21) attached on the door frame shows open or closed status of the door latch mechanism (1) above the lock warning piece (20).
  • the latch guide (22) guides and aligns movements of the latch (19).
  • the latch mechanism (1) is the only need for latching the door.
  • the inner handle (2) stays in horizontal position and when the door is in unlatched position, the inner handle (2) stays in vertical position.
  • the door latch mechanism (1) is designed so as not to allow water ingress and/or icing to take place inside the aircraft, howsoever.
  • the outer handle (4) is a critical part in respect of providing a sound level of proofing and insulation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Lock And Its Accessories (AREA)

Abstract

La présente invention concerne un mécanisme de verrouillage de porte (1) qui permet d'ouvrir et de refermer en toute sécurité des portes d'un aéronef pendant le vol ou à une position de stationnement. En plus de sa capacité à être utilisé dans n'importe quelle circonstance comprenant, sans s'y limiter, les urgences, par un fonctionnement basé totalement sur des mouvements mécaniques, le mécanisme de verrouillage de porte (1) facilite l'accès et la manipulation également en cas de dysfonctionnement, en raison de son système simple et de la conception simple de ses pièces. Il permet que les opérateurs de la porte ne courent aucun danger, en raison de sa conception qui supprime tous les types de risques de sécurité et de problèmes associés aux portes pressurisées.
PCT/TR2013/000145 2012-05-16 2013-04-22 Mécanisme de verrouillage de porte WO2013172804A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR201205709 2012-05-16
TR2012/05709 2012-05-16

Publications (1)

Publication Number Publication Date
WO2013172804A1 true WO2013172804A1 (fr) 2013-11-21

Family

ID=48790569

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/TR2013/000145 WO2013172804A1 (fr) 2012-05-16 2013-04-22 Mécanisme de verrouillage de porte

Country Status (1)

Country Link
WO (1) WO2013172804A1 (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105667757A (zh) * 2016-04-05 2016-06-15 中航沈飞民用飞机有限责任公司 一种民用飞机双曲段半堵塞式货舱门
CN106677612A (zh) * 2017-01-06 2017-05-17 江苏美龙振华科技有限公司 一种手柄内锁机构
CN107724823A (zh) * 2017-11-21 2018-02-23 江苏美龙航空部件有限公司 一种口盖闩锁装置及一种口盖
EP3348486A1 (fr) * 2017-01-14 2018-07-18 Hamilton Sundstrand Corporation Mécanisme de libération
DE102017112870B3 (de) 2017-06-12 2018-10-25 Ralf Bange Vorrichtung zum Verriegeln eines in einer Schließstellung befindlichen Türblatts sowie Türsystem
CN110359799A (zh) * 2018-07-20 2019-10-22 中航沈飞民用飞机有限责任公司 一种客机舱门提升机构
CN110984752A (zh) * 2019-12-25 2020-04-10 中国航空工业集团公司西安飞机设计研究所 一种机门防下沉装置
CN112591071A (zh) * 2020-12-17 2021-04-02 中航沈飞民用飞机有限责任公司 一种舱门提升开启破冰机构
CN112963053A (zh) * 2021-03-12 2021-06-15 中航西飞民用飞机有限责任公司 一种舱盖的内外开启手柄及开启方法
EP3858726A1 (fr) * 2020-01-28 2021-08-04 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Système d'actionnement d'une porte actionnable
CN114278156A (zh) * 2021-12-28 2022-04-05 中国航空工业集团公司西安飞机设计研究所 一种飞机舱门带导向功能的闩机构
US11434673B2 (en) * 2018-10-30 2022-09-06 Airbus Operations Gmbh Aircraft door locking system and aircraft door arrangement
US12000179B1 (en) * 2019-03-14 2024-06-04 Wisk Aero Llc Lock with single-sided automatic locking

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5305969A (en) 1991-07-16 1994-04-26 The Boeing Company Aircraft door latch lock mechanism
US5337977A (en) * 1993-01-29 1994-08-16 The Boeing Company Vent-latch interlock assembly for an aircraft door
US5738303A (en) * 1995-05-15 1998-04-14 The Boeing Company Mechanism for arming, disarming and activating airplane emergency slide evacuation systems
US6457675B1 (en) * 2001-06-25 2002-10-01 The Boeing Company Hydraulic actuation system for cargo doors with cam-type latches
EP2031159A1 (fr) * 2007-08-28 2009-03-04 SFS intec Holding AG Dispositif de verrouillage et unité d'actionnement appropriée
WO2009051875A2 (fr) 2007-07-31 2009-04-23 B/E Aerospace, Inc. Porte d'avion et son procédé d'utilisation
US20110248514A1 (en) 2010-04-02 2011-10-13 Airbus Operations Gmbh Locking mechanism for an aircraft door and method for the locking of an aircraft door

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5305969A (en) 1991-07-16 1994-04-26 The Boeing Company Aircraft door latch lock mechanism
US5337977A (en) * 1993-01-29 1994-08-16 The Boeing Company Vent-latch interlock assembly for an aircraft door
US5738303A (en) * 1995-05-15 1998-04-14 The Boeing Company Mechanism for arming, disarming and activating airplane emergency slide evacuation systems
US6457675B1 (en) * 2001-06-25 2002-10-01 The Boeing Company Hydraulic actuation system for cargo doors with cam-type latches
WO2009051875A2 (fr) 2007-07-31 2009-04-23 B/E Aerospace, Inc. Porte d'avion et son procédé d'utilisation
EP2031159A1 (fr) * 2007-08-28 2009-03-04 SFS intec Holding AG Dispositif de verrouillage et unité d'actionnement appropriée
US20110248514A1 (en) 2010-04-02 2011-10-13 Airbus Operations Gmbh Locking mechanism for an aircraft door and method for the locking of an aircraft door

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105667757A (zh) * 2016-04-05 2016-06-15 中航沈飞民用飞机有限责任公司 一种民用飞机双曲段半堵塞式货舱门
CN106677612A (zh) * 2017-01-06 2017-05-17 江苏美龙振华科技有限公司 一种手柄内锁机构
CN106677612B (zh) * 2017-01-06 2021-12-31 江苏美龙振华科技有限公司 一种手柄内锁机构
US10370115B2 (en) 2017-01-14 2019-08-06 Hamilton Sundstrand Corporation Release mechanism
EP3348486A1 (fr) * 2017-01-14 2018-07-18 Hamilton Sundstrand Corporation Mécanisme de libération
DE102017112870B3 (de) 2017-06-12 2018-10-25 Ralf Bange Vorrichtung zum Verriegeln eines in einer Schließstellung befindlichen Türblatts sowie Türsystem
CN107724823A (zh) * 2017-11-21 2018-02-23 江苏美龙航空部件有限公司 一种口盖闩锁装置及一种口盖
CN107724823B (zh) * 2017-11-21 2023-01-03 江苏美龙航空部件有限公司 一种口盖闩锁装置及一种口盖
CN110359799B (zh) * 2018-07-20 2021-02-19 中航沈飞民用飞机有限责任公司 一种客机舱门提升机构
CN110359799A (zh) * 2018-07-20 2019-10-22 中航沈飞民用飞机有限责任公司 一种客机舱门提升机构
US11434673B2 (en) * 2018-10-30 2022-09-06 Airbus Operations Gmbh Aircraft door locking system and aircraft door arrangement
US12000179B1 (en) * 2019-03-14 2024-06-04 Wisk Aero Llc Lock with single-sided automatic locking
CN110984752B (zh) * 2019-12-25 2022-02-08 中国航空工业集团公司西安飞机设计研究所 一种机门防下沉装置
CN110984752A (zh) * 2019-12-25 2020-04-10 中国航空工业集团公司西安飞机设计研究所 一种机门防下沉装置
EP3858726A1 (fr) * 2020-01-28 2021-08-04 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Système d'actionnement d'une porte actionnable
US11801929B2 (en) 2020-01-28 2023-10-31 Airbus Helicopters Deutschland GmbH Actuating system for an actuatable door
CN112591071A (zh) * 2020-12-17 2021-04-02 中航沈飞民用飞机有限责任公司 一种舱门提升开启破冰机构
CN112963053A (zh) * 2021-03-12 2021-06-15 中航西飞民用飞机有限责任公司 一种舱盖的内外开启手柄及开启方法
CN114278156A (zh) * 2021-12-28 2022-04-05 中国航空工业集团公司西安飞机设计研究所 一种飞机舱门带导向功能的闩机构

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