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EP1366985B1 - Mécanisme de blocage d'une porte - Google Patents

Mécanisme de blocage d'une porte Download PDF

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Publication number
EP1366985B1
EP1366985B1 EP03010526A EP03010526A EP1366985B1 EP 1366985 B1 EP1366985 B1 EP 1366985B1 EP 03010526 A EP03010526 A EP 03010526A EP 03010526 A EP03010526 A EP 03010526A EP 1366985 B1 EP1366985 B1 EP 1366985B1
Authority
EP
European Patent Office
Prior art keywords
locking
locking mechanism
arrangement according
actuator
stop
Prior art date
Legal status (The legal status 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 status listed.)
Expired - Lifetime
Application number
EP03010526A
Other languages
German (de)
English (en)
Other versions
EP1366985A2 (fr
EP1366985A3 (fr
Inventor
Wolfgang Buchs
Thangaraju Nithyanandam
Holger Schreitmüller
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Helicopters Deutschland GmbH
Original Assignee
Eurocopter Deutschland GmbH
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 Eurocopter Deutschland GmbH filed Critical Eurocopter Deutschland GmbH
Publication of EP1366985A2 publication Critical patent/EP1366985A2/fr
Publication of EP1366985A3 publication Critical patent/EP1366985A3/fr
Application granted granted Critical
Publication of EP1366985B1 publication Critical patent/EP1366985B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • E—FIXED CONSTRUCTIONS
    • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
    • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
    • E05B47/00—Operating or controlling locks or other fastening devices by electric or magnetic means
    • E05B47/06—Controlling mechanically-operated bolts by electro-magnetically-operated detents
    • E05B47/0657—Controlling mechanically-operated bolts by electro-magnetically-operated detents by locking the handle, spindle, follower or the like
    • E—FIXED CONSTRUCTIONS
    • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
    • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
    • E05B47/00—Operating or controlling locks or other fastening devices by electric or magnetic means
    • E05B47/0001—Operating or controlling locks or other fastening devices by electric or magnetic means with electric actuators; Constructional features thereof
    • E05B2047/0014—Constructional features of actuators or power transmissions therefor
    • E05B2047/0018—Details of actuator transmissions
    • E05B2047/002—Geared transmissions
    • E05B2047/0022—Planetary gears
    • E—FIXED CONSTRUCTIONS
    • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
    • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
    • E05B47/00—Operating or controlling locks or other fastening devices by electric or magnetic means
    • E05B47/0001—Operating or controlling locks or other fastening devices by electric or magnetic means with electric actuators; Constructional features thereof
    • E05B47/0012—Operating or controlling locks or other fastening devices by electric or magnetic means with electric actuators; Constructional features thereof with rotary electromotors

Definitions

  • the present invention relates to a locking device of an outer door of an aircraft for locking a door kinematics and an aircraft door assembly with an outer door and such a locking device.
  • the locking device comprises a locking mechanism, which can be brought into a blocking position and an unlocked position, and a linear actuator for Actuation of the locking mechanism.
  • the linear actuator has a piston-like actuating rod.
  • the locking device comprises a control unit which activates the linear actuator in the presence of a control signal, so that this brings the locking mechanism in the locked position. Thereafter, the linear actuator or its drive is switched off.
  • the locking device is provided with an automatic return device in the form of two springs, which can bring the locking mechanism independently in the unlocked position.
  • the locking mechanism after switching off the linear actuator in the locked position but not immediately reset by this reset and thereby unlocked, must be kept in this known blocking position in this known locking device of the locking mechanism by means of an electromagnet.
  • a magnetic element is provided on a locking lever of the locking mechanism, which can be coupled to this with appropriate magnetization and activation of the electromagnet and exercises the holding function.
  • it is necessary to deactivate the electromagnet. Only then can the return device act.
  • WO-A-84 01 404 discloses a so-called anti-theft aircraft door assembly having an interior door to be opened and closed with a key and disposed between a cockpit and a passenger cabin of an aircraft.
  • the aircraft door arrangement has a locking device which comprises a rotatable actuator equipped with a restoring device in the form of a rotary magnet coil which, when an electric current is applied, brings a blocking element into a blocking position and holds it there with its holding torque.
  • a locking device which comprises a rotatable actuator equipped with a restoring device in the form of a rotary magnet coil which, when an electric current is applied, brings a blocking element into a blocking position and holds it there with its holding torque.
  • Object of the present invention is to provide a locking device of an outer door of an aircraft, to lock a door kinematics, which has a simpler, easier to manufacture structure, a low weight and the smallest possible installation volume, which requires a reduced tax expense, and an aircraft Still lock the outside door safely and if necessary, especially in an emergency, the blocking of the outside door can safely release again.
  • an aircraft door arrangement is to be provided with an outer door and such a locking device.
  • the locking device comprises a control unit, a rotary actuator for actuating a locking mechanism and an automatic reset device.
  • the locking device is further configured such that the control unit operates the rotary actuator in response to the presence of a predetermined signal to bring the locking mechanism in the locked position.
  • the automatic return device brings, if necessary, in particular in an emergency, the locking mechanism automatically in an unlocked position, so that the Airplane exterior door can be opened from the inside. Furthermore, the automatic return device ensures that in the absence of the predetermined control signal and a consequent failure of the holding torque of the rotary actuator and, for example, in case of failure of a single component of the locking device, the locking device is also returned to the unlocked state, so that the door kinematics for opening the Outside door can be operated.
  • a rotary actuator ensures a high operational reliability in a small space, especially with regard to the blocking during the flight, safe.
  • a brushless DC motor is used as a rotary actuator.
  • Such motors are compact, require only a small space and have only a low weight. Furthermore, such motors are largely maintenance-free and have a high reliability.
  • Another possibility for a rotary actuator is the use of a drive with a solenoid, through which a cost-effective drive can be provided, which, however, has a higher weight and a larger installation volume than a DC motor.
  • the predetermined signal in dependence of which the control unit actuates the rotary actuator, is a "flight" signal of the aircraft. This can ensure that the locking device always automatically locks the door kinematics during the flight of the aircraft.
  • Another preferred way to provide the predetermined signal is the provision of a switch, for example in the cockpit, wherein the predetermined signal is generated upon actuation of the switch and the locking device locks the door kinematics.
  • a switch can for example also be used for maintenance purposes or to check the function of the locking device on the ground.
  • the locking device further preferably comprises a gear, in particular a planetary gear.
  • the automatic return device is equipped with a spring element, whereby a particularly inexpensive return device of the locking device can be provided.
  • the automatic restoring device comprises at least two spring elements, each of which is individually capable of returning the locking mechanism from the locked position to the unlocked position. This allows a redundancy of the return device, whereby a failure of a spring element can be compensated. Thus, an even greater security for any necessary in an emergency provision of the locking mechanism is obtained.
  • the spring elements are preferably biased by the locking mechanism is brought into the locked position.
  • the restoring device is automatically transferred to its tensioned state automatically even when locking the door kinematics.
  • the spring force of the spring element is preferably selected so that the spring element is able to bring the locking mechanism in a period of a few seconds from the locking position to the unlocked position.
  • the rotary actuator is preferably designed such that it, de-energized, also acts as a brake when the locking mechanism is returned from the locking position to the unlocked position. This allows a damped return of the locking mechanism.
  • the locking mechanism advantageously comprises a hook and a fitting element with a recess, in which engages the hook in the locked state, thereby blocking the door kinematics.
  • a separate stop element is preferably provided, which defines a start and / or end position, without causing the hook is loaded.
  • control unit controls the rotary actuator in such a way that the speed is reduced when approaching the stop in order to achieve a gentle striking.
  • control unit controls the rotary actuator in such a way that, in the case of a suitable signal, the locking mechanism is actively driven in the direction of unlocking.
  • the locking device according to the invention is particularly suitable for retrofitting in already in use aircraft with appropriate modifications. Since the locking device according to the invention is very lightweight and compact, it can usually be easily installed between Mosspantsegmenten the outer door.
  • a locking device according to an embodiment of the present invention is shown.
  • Figs. 1 and 2 show the locked state of the locking device and Figs. 3 and 4, the unlocked state of the locking device.
  • the blocking device comprises a control unit 10, which is connected via a cable 14 to a rotary actuator 1.
  • the rotary actuator 1 comprises a brushless DC motor 2, which drives an output shaft 17.
  • the DC motor 2 is a reduction planetary gear 3 with a locking mechanism 18 or a Sperrkinematik, the / an actuator lever 5, a connecting element 6, about a hook rotation axis A (see Fig. 5) rotatable hook 7, two springs 8a, 8b and a fitting 9 comprises (see in particular Fig. 2 and 4).
  • the rotatable hook 7 engages in a fitting 9 formed Recess 16 with undercut (see Fig. 1).
  • the fitting 9 is mounted on a door inner lever 15 (shown only schematically), which is to be operated by a handle roller 12 by hand to open the aircraft exterior door in a known manner.
  • the locking device comprises a stop mechanism consisting of a first stop 11a, a second stop 11b and a stop lever 4 (see Fig. 3).
  • the stop lever 4 is connected to the output shaft 17 of the planetary gear 3 and thus restricts the adjustment of the rotatable hook 7.
  • By the stop mechanism prevents the rotatable hook 7 presses against the fitting 9 under load and thus possibly damaged.
  • an automatic return means two coil springs 8a and 8b are provided, which are tensioned in a movement of the locking mechanism in the locked position. This condition is shown in FIG. In the unlocked state, the springs 8a, 8b are relaxed to their interpretation according to bias. The restoring force of the springs 8a and 8b is in each case dimensioned such that they are each individually capable of automatically reset the locking mechanism from any position to the unlocked state. Thus, a redundant automatic reset device is given.
  • the locking device according to the invention between two door frame segments 13 of the aircraft exterior door can be mounted.
  • the function of the locking device according to the invention of the embodiment is as follows.
  • a so-called "flight” signal is automatically generated, which indicates the flying state of the aircraft.
  • This signal is supplied to the control unit 10, which controls the locking device.
  • the control device 10 controls the rotary actuator 1 by means of electrical signals via the line 14 such that the DC motor 2 drives the drive shaft 17 by voltage limitation in a regulated manner.
  • the speed of the drive shaft 17 is reduced in the planetary gear 3.
  • the output shaft 17 of the planetary gear 3 is connected to the actuator lever 5 by means of a toothing. 3 and 4, the rotatable hook 7 is thus moved upwards in the direction of the recess 16 about the hook rotation axis A (see FIG.
  • the rotatable hook 7 prevents the unlocking and unlocking of the door kinematics.
  • the control unit 10 shuts off the electronic commutation required to rotate the rotary actuator 1 by detecting a current pulse and a constant current in the DC motor 2 introduces. Thereby, overheating of the DC motor 2 in the end stop state can be prevented, and the demand of electric power for holding the position of the rotary hook 7 in the locked state is minimized. Furthermore, by the detection of the current pulse, an automatic setting of the Travel path of the rotary actuator 1 reaches the stop. This can be dispensed with an end position sensor.
  • the DC motor 2 is de-energized and the rotatable hook 7 by means of the restoring force of the two springs 8a, 8b in its initial position reset, so that the door inner lever 15 is released and is to operate to open the door.
  • the DC motor 2 runs as a brake by short circuiting the motor windings via a braking resistor and thus prevents a hard stop.
  • the geometry of the contact surfaces between the rotary hook 7 and the recess 16 is designed by a Abgleittangent T inclined at an angle ⁇ to a line N such that in the currentless case, even at Sluggishness of the locking mechanism 18, by hand force on the handle roller 12 via a contact point K between the hook 7 and the recess 16 of the fitting 9 an opening moment on the rotary hook 7 is generated. If there is a current, this opening moment is overcompensated by the holding torque of the rotary actuator 1.
  • the locking device according to the invention is thus constructed such that even in case of failure of one of the components of the locking device (eg failure of the DC motor, mechanical breakage of a component), the return device 8a, 8b unlock the locking device independently, so that in an emergency always the possibility of opening the outer door guaranteed by hand.
  • the rotary actuator 1 can thus be achieved with high reliability in case of failure of a single element of the locking device a secure state (unlocked position).
  • this electromechanical locking device also has the highest reliability when held in the locked position and has a low weight and low manufacturing and assembly costs. Due to the compact design, it is also easily possible to retrofit aircraft already in use with the locking device according to the invention.

Landscapes

  • Lock And Its Accessories (AREA)
  • Power-Operated Mechanisms For Wings (AREA)

Claims (14)

  1. Dispositif de verrouillage d'une porte extérieure d'un avion, pour le blocage d'une cinématique de porte (12, 15), comprenant :
    - un mécanisme de verrouillage (18 ; 5, 6, 7, 8a, 8b, 9), qui peut être amené dans une position de verrouillage et dans une position de déverrouillage ;
    - un actuateur de rotation (1), commandé, avec un arbre de sortie (17) pour l'actionnement du mécanisme de verrouillage (18) ;
    - une unité de commande (10), à laquelle peut être transmis un premier signal de commande prédéfini, et qui actionne l'actuateur de rotation (1) en présence du premier signal de commande, de sorte que ce dernier amène le mécanisme de verrouillage (18) dans la position de verrouillage et le maintient dans cette position par l'intermédiaire d'un couple de retenue ;
    - un dispositif de rappel automatique (8a, 8b), qui amène de façon autonome le mécanisme de verrouillage (18) dans la position de déverrouillage en l'absence du premier signal de commande et en l'absence résultante du couple de retenue de l'actuateur de rotation (1), et
    - un mécanisme de butée (11a, 11b, 4) avec
    - une première butée (11a), qui définit la position de verrouillage, et une seconde butée (11b), qui définit la position de déverrouillage, et
    - un levier de butée (4), qui est raccordé à l'arbre de sortie (17) et peut tourner avec ce dernier entre une première position sur la première butée (11a) et une seconde position sur la seconde butée (11b), et soulage dans la position de verrouillage le mécanisme de verrouillage (18) du couple de retenue de l'actuateur de rotation (1).
  2. Dispositif de verrouillage suivant la revendication 1, caractérisé en ce que l'actuateur de rotation (1) comprend un moteur à courant continu (2) sans balais.
  3. Dispositif de verrouillage suivant l'une des revendications précédentes, caractérisé en ce que le premier signal de commande prédéfini est un signal « flight » de l'avion.
  4. Dispositif de verrouillage suivant l'une des revendications précédentes, caractérisé en ce qu'il comprend en outre un engrenage (3), en particulier un planétaire, qui réduit la vitesse de rotation motrice du moteur à courant continu (2).
  5. Dispositif de verrouillage suivant l'une des revendications précédentes, caractérisé en ce que le dispositif de rappel automatique (8a, 8b) est réalisé sous forme d'élément à ressort.
  6. Dispositif de verrouillage suivant la revendication 5, caractérisé en ce que le dispositif de rappel automatique comprend au moins deux éléments à ressort (8a, 8b), qui sont chacun capables individuellement d'amener le mécanisme de verrouillage (18) de la position de verrouillage dans la position de déverrouillage.
  7. Dispositif de verrouillage suivant l'une des revendications 5 et 6, caractérisé en ce que l'élément à ressort est tendu, lorsque le mécanisme de verrouillage (18) se situe dans la position de verrouillage.
  8. Dispositif de verrouillage suivant l'une des revendications précédentes, caractérisé en ce qu'il comprend un dispositif de freinage de la vitesse de déplacement du mécanisme de verrouillage (18) lors du déverrouillage du dispositif de verrouillage.
  9. Dispositif de verrouillage suivant la revendication 8, caractérisé en ce que l'actuateur (1) est réalisé sous forme du dispositif de freinage et freine le mécanisme de verrouillage (18) dans un état de commutation sans courant, lorsque le mécanisme de verrouillage (18) est ramené de la position de verrouillage dans la position de déverrouillage, si bien que ce dernier est ramené de façon amortie.
  10. Dispositif de verrouillage suivant l'une des revendications précédentes, caractérisé en ce que l'unité de commande (10) est réalisée sous forme du dispositif de freinage et l'actuateur (1) peut être commandé par l'unité de commande (10) de telle sorte que la vitesse du levier de butée (4) est réduite lors de son approche de la première butée (11a).
  11. Dispositif de verrouillage suivant l'une des revendications précédentes, caractérisé en ce que le mécanisme de verrouillage (18) comprend un crochet (7) et un élément de ferrure (9) avec un évidement (16), le crochet (7) s'engageant à l'état de verrouillage dans l'évidement (16) et bloquant la cinématique de porte (12, 15).
  12. Dispositif de verrouillage suivant la revendication 11, caractérisé en ce que le crochet (7) est un crochet rotatif autour d'un axe de rotation (A) de crochet.
  13. Dispositif de verrouillage suivant l'une des revendications précédentes, caractérisé en ce qu'un second signal de commande prédéfini peut être transmis à l'unité de commande (10), et l'unité de commande (10) actionne l'actuateur de rotation (1) en présence du second signal de commande de telle sorte que ce dernier (1) amène activement le mécanisme de verrouillage (18) en direction de la position de déverrouillage.
  14. Agencement de porte d'avion, comprenant une porte extérieure d'un avion avec un dispositif de verrouillage suivant l'une ou plusieurs des revendications 1 à 13.
EP03010526A 2002-05-29 2003-05-10 Mécanisme de blocage d'une porte Expired - Lifetime EP1366985B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10223902 2002-05-29
DE10223902A DE10223902B4 (de) 2002-05-29 2002-05-29 Sperrvorrichtung einer Außentür eines Flugzeugs zum Sperren einer Türkinematik

Publications (3)

Publication Number Publication Date
EP1366985A2 EP1366985A2 (fr) 2003-12-03
EP1366985A3 EP1366985A3 (fr) 2004-01-28
EP1366985B1 true EP1366985B1 (fr) 2006-06-28

Family

ID=29414248

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03010526A Expired - Lifetime EP1366985B1 (fr) 2002-05-29 2003-05-10 Mécanisme de blocage d'une porte

Country Status (6)

Country Link
US (1) US6951320B2 (fr)
EP (1) EP1366985B1 (fr)
JP (1) JP4430339B2 (fr)
AT (1) ATE331658T1 (fr)
CA (1) CA2429297C (fr)
DE (2) DE10223902B4 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8047583B2 (en) * 2007-10-04 2011-11-01 B/E Aerospace, Inc. Split handle for aircraft door
CN101967913B (zh) * 2010-10-15 2012-12-26 大连量天科技发展有限公司 一种电动锁
CN102230344B (zh) * 2011-06-21 2014-04-23 宁波永发集团有限公司 密码锁永磁体组件锁紧器
CN103603555B (zh) * 2013-08-23 2016-08-10 中国航空工业集团公司西安飞机设计研究所 一种舱门锁
US11454048B2 (en) 2018-11-07 2022-09-27 The Boeing Company Shape memory alloy locking apparatuses
CN111021865B (zh) * 2019-12-09 2021-07-09 中航沈飞民用飞机有限责任公司 一种堵塞式舱门打开位置锁机构

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0121517B1 (fr) * 1982-09-30 1988-03-30 The Boeing Company Mecanisme de verrouillage de porte anti-detournement avec commande de derogation de decompression pneumatique
EP0321994B1 (fr) * 1987-12-21 1993-01-13 The Boeing Company Verrouillage de porte d'avion
US4915326A (en) * 1987-12-21 1990-04-10 The Boeing Company Aircraft exit door locking system
US5636814A (en) * 1990-04-05 1997-06-10 The Boeing Company Automatic clutch for a door latch handle
DE4334522C1 (de) * 1993-10-09 1995-01-12 Kiekert Gmbh Co Kg Kraftfahrzeugtürverschluß, der von Hand oder über eine Zentralverriegelungseinrichtung zu bedienen ist sowie eine Diebstahlsicherungseinrichtung aufweist
CA2193311A1 (fr) * 1995-12-19 1997-06-20 Vernon L. Abild Systeme de verrouillage electrique de la porte de soute du pont principal
US5803404A (en) * 1996-01-23 1998-09-08 Mpc Products, Inc. Door actuation system having a variable damping device

Also Published As

Publication number Publication date
CA2429297A1 (fr) 2003-11-29
DE10223902A1 (de) 2003-12-18
US6951320B2 (en) 2005-10-04
EP1366985A2 (fr) 2003-12-03
CA2429297C (fr) 2012-07-03
JP2003341596A (ja) 2003-12-03
DE10223902B4 (de) 2009-04-30
ATE331658T1 (de) 2006-07-15
US20040004159A1 (en) 2004-01-08
DE50304025D1 (de) 2006-08-10
JP4430339B2 (ja) 2010-03-10
EP1366985A3 (fr) 2004-01-28

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