EP3439961A1 - Dispositif d'affichage installable ultérieurement destiné à afficher un état d'activation d'un toboggan de secours dans un avion - Google Patents

Dispositif d'affichage installable ultérieurement destiné à afficher un état d'activation d'un toboggan de secours dans un avion

Info

Publication number
EP3439961A1
EP3439961A1 EP16716016.7A EP16716016A EP3439961A1 EP 3439961 A1 EP3439961 A1 EP 3439961A1 EP 16716016 A EP16716016 A EP 16716016A EP 3439961 A1 EP3439961 A1 EP 3439961A1
Authority
EP
European Patent Office
Prior art keywords
display device
aircraft
sensor
door
person
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.)
Withdrawn
Application number
EP16716016.7A
Other languages
German (de)
English (en)
Inventor
Kai Bredemeier
Carsten Heuer
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 Operations GmbH
Original Assignee
Airbus Operations 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 Airbus Operations GmbH filed Critical Airbus Operations GmbH
Publication of EP3439961A1 publication Critical patent/EP3439961A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/0005—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D25/00—Emergency apparatus or devices, not otherwise provided for
    • B64D25/08—Ejecting or escaping means
    • B64D25/14—Inflatable escape chutes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/02—Arrangements or adaptations of signal or lighting devices
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S15/00—Systems using the reflection or reradiation of acoustic waves, e.g. sonar systems
    • G01S15/02—Systems using the reflection or reradiation of acoustic waves, e.g. sonar systems using reflection of acoustic waves
    • G01S15/06—Systems determining the position data of a target
    • G01S15/08—Systems for measuring distance only
    • G—PHYSICS
    • G08—SIGNALLING
    • G08B—SIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
    • G08B7/00—Signalling systems according to more than one of groups G08B3/00 - G08B6/00; Personal calling systems according to more than one of groups G08B3/00 - G08B6/00
    • G08B7/06—Signalling systems according to more than one of groups G08B3/00 - G08B6/00; Personal calling systems according to more than one of groups G08B3/00 - G08B6/00 using electric transmission, e.g. involving audible and visible signalling through the use of sound and light sources
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D2045/007—Indicators or signs in the cabin, e.g. exit signs or seat numbering

Definitions

  • Retrofittable display device for displaying an activation status of a
  • the invention relates to a display device for displaying a
  • Activation status of an escape slide in an aircraft a method for indicating an activation status of an escape slide and an aircraft with at least one escape slide and a display device for indicating an activation status of the at least one emergency slide.
  • aircraft doors are couplable with an escape slide deployment device such that when the aircraft door is opened, an escape slide disposed thereon is deployed.
  • an emergency slide release lever Prior to departure, an emergency slide release lever is placed in an armed mode with the doors closed.After normal landing, the emergency slide release lever is placed in a "disarmed” mode so that coupling with the emergency slide release device is released and the aircraft doors are normally open.
  • the position of the emergency slide release lever s is optically clearly recognizable.
  • a warning light can be installed in or on the aircraft door, which has a optical indication of the state of the emergency slide activation enabled.
  • the escape slide activation lever may be left in the armed state and an emergency slide accidentally released when an aircraft door is opened, causing damage in the vicinity of the aircraft This is independent of the door structure and the aircraft manufacturer
  • There are solutions to prevent the accidental release of emergency slides for example by means of detecting an approach of a person to an aircraft door and an optical and / or audible warning when a person approaches the door or touches the handle when the escape slide deployment device is coupled to the aircraft Such a solution may require modification of the aircraft door.
  • a display device for indicating an activation status of an escape slide in an aircraft, which is an optical display device for outputting an optical signal, an acoustic signaling device for
  • a sensor for detecting the approach of a person to the display device and an electronic unit, which is coupled to the optical display device, the acoustic signal device and the sensor and is adapted to approach a person at least a predetermined threshold distance at least to operate one of the optical and the acoustic signaling device.
  • the visual display device, the acoustic signal device, the sensor and the electronic unit further form a coherent, compact unit which can be integrated into a door panel of the aircraft.
  • the optical display device is used to generate a visually perceptible signal that indicates to a person that when opening a door of the aircraft, an emergency slide is triggered. Any of these can be used to generate this signal
  • Display devices find use, in particular selectively generate a light signal, for example by a lighting device based on a light bulb, an LED or a plurality thereof.
  • the lighting device may be configured to emit a continuous light or a flashing light, wherein the visual perceptibility of a flashing light may exceed that of a continuous light.
  • the acoustic signal device may analogously have a sound generating unit with which an acoustically perceptible signal can be generated.
  • the sound generating means may for this purpose comprise an electromagnetically or piezoelectrically operable loudspeaker or buzzer and, if required, a means for selectively outputting a burst for reproducing a recorded or synthetic sound.
  • the sensor is also able to detect an approach of a person to the sensor and thus to the display device housing it, so that knowledge can be obtained on whether and / or at what distance a person is in front of the sensor. Based on information determined by the sensor, the electronic unit coupled thereto is capable of selectively detecting the optical signal
  • Display device and the acoustic signaling device to operate.
  • the electronic unit based on the distance of a person from the sensor or the display device can make a visual and / or audible warning, by which the person is advised that when opening the door with a release of the emergency slide is to be expected .
  • the display device By the execution of the display device as a compact unit, which is integrable in a door panel of the aircraft, such as a window funnel of a door window, thus can be readily arranged there, a conventional warning lamp for emergency slip activation by the
  • the display device is preferably to be designed such that it is designed at least in a necessary area for attachment as a conventional warning light, so that the door trim and a corresponding cutout or a fastener arranged thereon need not be modified.
  • the display device according to the invention thus has a very high potential for a retrofit solution (retrofit), because it would only have to be replaced by a conventional warning light by the display device according to the invention.
  • the display device preferably has a housing with a fastening region and a visible side.
  • the attachment portion is adapted to engage mechanically with the door panel or fastener on the aircraft door.
  • the optical display device and the sensor extend at least partially toward the visible side. The arrangement of the optical display device in a range close to the visible side allows undisturbed perception of the optical signal that is emitted by the optical signal
  • the sensor is also preferred in one arranged close to the visual area to allow undisturbed monitoring of a located in front of the display device and thus in front of the door panel in the interior of the aircraft detection or monitoring area.
  • This monitoring area is defined as a space in front of the aircraft door or as a surface area of a floor in front of the door panel by selecting and fine-tuning of the sensor and extends into the interior of the aircraft, that is a remote from the door panel area.
  • the sensor and the optical display device can be arranged side by side or one above the other on the visible side.
  • the senor is an ultrasonic sensor. This can periodically emit an acoustic signal in the ultrasonic range, which is reflected by objects located in the detection or monitoring area and reflected back to the sensor. From the time difference between emitted and incoming signal, the distance of the object from the sensor can be determined.
  • ultrasonic sensors have a comparatively low weight, yet allow a precise measurement and an adjustable sensor behavior.
  • the electronic unit has at least one activation signal input and is configured to be based on a via the
  • Activation signal input receivable activation signal to activate or interrupt the operation of the optical display device and the acoustic signaling device.
  • the electronics unit can thus make the operation of the optical display device and the acoustic signal device dependent on the landing state of the aircraft and / or the position of an emergency slide activation lever located on the relevant door. This has the advantage that appropriate monitoring is carried out only when landed aircraft and in a certain position emergency slide activation lever when there is a risk that without deactivation of
  • Landing state of the aircraft can be generated by a separate device in aircraft on the ground and transmitted to the activation signal input.
  • An activation signal which depends on the position of the
  • Emergency slide activating lever may be generated by a further sensor which is arranged in or on the emergency slide activation lever, monitors the position of the emergency slide activation lever and transmits a corresponding signal to the at least one activation signal input.
  • An activation signal which depends on the landing state of the aircraft, can be generated and transmitted by a central, already existing system of the aircraft. It makes sense to connect the display device according to the invention for this purpose via a corresponding bus or a network with this central device, for example via an AFDX, CAN or the like.
  • the prerequisite for this is that a corresponding data line is present in the door or is subsequently integrated into it.
  • a wireless connection device or a data transmission system realized on the basis of the power line entering the door could also be used for this purpose.
  • the display device further comprises an inertial measuring unit coupled to the electronic unit with at least one inertial sensor for continuous or periodic detection of at least one directional acceleration, wherein the electronic unit is adapted to determine from the detected at least one directional acceleration whether the aircraft is at Floor is located.
  • An inertial sensor could be both a Acceleration along one of three spatial axes as well as one
  • Detect spin around one of three space axes By using at least one inertial sensor, the movement of the aircraft can be tracked to conclude whether the aircraft is on the ground or in flight.
  • Various different methods can be used for this purpose. For example, by continuously tracking the movements of the aircraft, a flight profile can be detected, which consists of a climb phase, a cruise with one or more cruising altitudes, a sinking phase and a subsequent roll phase in which the aircraft is strongly decelerated and acceleration in the vertical direction is negligible. It would also be possible to detect only a characteristic landing following a descent phase and / or a significant deceleration in the longitudinal direction of the aircraft.
  • the different methods may require different arrangements with a different number of inertial sensors, in determining a landing impact could be sufficient for example a single inertial sensor, the
  • the display device according to the invention makes sense, the display device according to the invention as always To design the same component that can be integrated into many different aircraft doors.
  • the inertial measuring unit integrated in the display device can therefore be aligned in two different ways to the direction of flight.
  • Installation side of the display device must therefore be known to the direction of flight to be able to reliably identify the state of the aircraft with the signals supplied by the inertial measurement unit.
  • appropriate firmware in the electronics unit can also offer, with the help of bridgeable pins, i.e. a pin programming, at the
  • the electronic unit is configured to operate the optical display device when approaching a person below a first threshold distance and the acoustic signal device when approaching a person below a second threshold distance, wherein the first threshold distance is greater than the second threshold distance.
  • the first threshold distance is greater than the second threshold distance.
  • Limit distance for example, is below one or one and a half arm lengths, preferably a maximum of 0.5 m, an additional acoustic signal can be issued, which explicitly indicates the person that when pressing the handle, the emergency chute is triggered.
  • the housing of the display device according to the invention may be at least partially transparent in a section housing the optical display device. Therefore, the package shape does not need to be different from that of a conventional warning lamp and the components integrated therein are external
  • the invention further relates to a method for displaying an activation status of an escape slide in an aircraft, which comprises the steps of detecting a distance of a person from a display device in a door panel of an aircraft, comparing the distance with at least a threshold distance, operating at least one optical display device and having an acoustic signaling device as soon as the at least one limit distance is exceeded.
  • the optical display device is operated when approaching a person below a first threshold distance and the acoustic signaling device is operated when approaching a person below a second threshold distance, wherein the first threshold distance is greater than the second threshold distance.
  • the electronics unit may further inhibit the operation of the at least one optical display device and the acoustic signal device as soon as no activation signal is received at at least one activation signal input.
  • this may be a land condition dependent signal and / or a signal dependent on the position of a landslide activation lever.
  • At least one directed sensor can be continuously or intermittently connected to at least one inertial sensor via an inertial measuring unit coupled to the electronic unit, which is arranged in the display device
  • the inertial measuring unit preferably has a three-axis or six-axis sensor.
  • the invention further relates to an aircraft with at least one door and an attached door panel inside the aircraft and a
  • Fig. 1 shows a display device in a three-dimensional view.
  • Fig. 2 shows a possible installation position of the display device.
  • Fig. 3 shows the display device in a four-page view.
  • Fig. 4 shows the display device in a partially decomposed view.
  • Fig. 5 shows possible sound lobes of an ultrasonic sensor.
  • Fig. 6 shows a person in front of an aircraft door and a triggered display.
  • Fig. 7 shows the display device in a schematic, block-based
  • FIG. 1 shows a display device 2 according to the invention, which has a housing 4 with a fastening region 6 and a visible side 8.
  • Display device 2 is an optical display device 10 which has, as an example, a plurality of lighting devices 18, an acoustic signal device 12 hidden in FIG. 1, and a sensor 14 for detecting the distance of an object from the display device 2.
  • exemplary are the optical
  • the attachment portion 6 may further comprise elastic retaining clips 15, which upon insertion of the
  • Attachment 6 enter into a corresponding opening of a door panel with this a positive and / or non-positive connection.
  • Limit distance 32, 34 can be achieved, which may reach an object at most, so that the optical display device 10 and the acoustic signal device 12 are operated.
  • the electronics unit 16 may include an enable signal input to which an enable signal may be sent. This is used to initiate the operation of the optical display device 10 and the acoustic signal device 12 only when the aircraft is on the ground and at any time the associated aircraft door can be opened.
  • the optical display device 10 is in the embodiment shown only separated by a transparent cover 13 from the visible side 8 or disposed in a cutout therein, so that an unrestricted visibility of the optical display device 10, i. the lighting means 18, which are suitable for generating a sufficiently bright light, pulsed or continuous.
  • the optical display device 10 has, by way of example, a lettering "20" ("Slide Armed"), which is embodied as the only nontranslucent surface of the optical display device 10.
  • the lettering 20 can also be realized as the only light passage surface of the optical display device.
  • the sensor 14 is an example of an ultrasonic sensor, which periodically
  • sensors such as optical, camera-based, or radar-based sensors.
  • the display device 2 is designed as a very compact unit that can be used instead of a conventional warning light in a door trim or the like.
  • the optical display device 10 and / or the acoustic signal device 12 then operate when the aircraft is on the ground and an opening of the aircraft door is imminent. This can be realized in a particularly simple manner by receiving an activation signal at the activation signal input, for which, however, a data line to a central unit on board the aircraft is necessary.
  • a here hidden inertial measuring device (inertial platform or IMU) 22 is integrated, which is adapted to detect the spatial movements of the aircraft and to transmit it to the electronic unit 16.
  • the landing of an aircraft can be detected by succinct events, such as a landing impact after a continuous descent, with the detected altitude of the aircraft after landing impact practically no longer changes. If this event has occurred, the electronic unit 16 can carry out the monitoring and thereby controlled visual or acoustic warnings.
  • Fig. 2 shows by way of example an aircraft door 24 with a door panel 26 facing the interior of the fuselage. If the aircraft is on a runway or in a parked position, the door 24 will be from the inside of the car
  • the display device 2 is integrated on or in the door panel 26, such as in a window funnel of a door window, wherein the visible side 8 of the display device 2 is turned into the interior of the aircraft.
  • the sensor 14 monitors a space 28 on the inside of the aircraft and defines a detection area 30 there.
  • the electronics unit 16 may define a first limit distance 32 and a second limit distance 34, the electronics unit 16 operating the optical display device 10 as soon as a person falls below the first limit distance 32 and the acoustic signal device 12 is operated as soon as a person reaches the second limit distance 34 below.
  • the first Grenzabstand 32 it is advisable to provide a distance of at most 1.1 m and preferably 0.9 m.
  • the second limit distance 34 a distance of at most 0.5 m and preferably 0.35 m is recommended. If a person is located between the two lines delineating the border distances 32 and 34, they are only made visually, for example by a flashing light, aware of the still activated escape slide.
  • the two boundary distances 32 and 34 may also be the same, so that a visual and acoustic signaling takes place simultaneously.
  • Fig. 3 shows a four-sided view of the display device 2, in which a bottom 36 is shown with an electrical connection 38 which is to be connected to a power supply of the door 24 and further coupled to a sensor, not shown, which the emergency slide activation lever 31 monitored. Both can be realized via an activation signal, which depends on the position of the emergency slide activation lever 31, as well as on a dependent of the position of the emergency slide activation lever 31 power supply.
  • a narrow end 40 of the viewing area 8 mainly comprises the sensor 14, which, in the case of installation shown in FIG. 2, is directed directly into the interior of the aircraft fuselage.
  • the lighting devices 18 can be seen, which are distributed along the side wall 42 in the interior of the cover 13.
  • the mounting portion 6 is narrower than the viewing area 8 designed so that in an openingInstitutschnappter display device 2 facing the mounting portion 6 edge 44 can rest on an edge of the respective opening and the retaining clips 15 flush contact of the edge 44 with the edge of the the opening in question.
  • the lettering 20 is disposed on an upper side 46 and takes there in
  • FIG. 4 further shows the display device 2 in a partially disassembled arrangement, wherein an inertial measuring unit 48 integrated in the electronic unit 16 can be seen here, which can detect the movement of the display device 2 and thus of the aircraft.
  • an inertial measuring unit 48 integrated in the electronic unit 16 can be seen here, which can detect the movement of the display device 2 and thus of the aircraft.
  • a diagram in Fig. 5 further shows two preferred sound beams 50 and 52 of the ultrasonic sensor 14, wherein the sound beam 50 to a plate-oriented ultrasonic sensor and the sound beam 52 to an ultrasonic sensor with a tube having a diameter of, for example, 27 mm.
  • the sound beam should be as narrow as possible, so that a width of well below one meter and preferably from 0.3 to 0.7 m is reached.
  • the detection area 28 is thus quite narrow and can hide laterally further away people.
  • the use of an aligned plate allows a sound lobe 50 slightly wider than the solution with tube.
  • a person 54 is shown, which approaches the door 24 and in this case has already exceeded the first limit distance 32 and reaches the second limit distance.
  • a visual warning and an audible warning are emitted so that the person 54 is clearly warned against being in one Activating position emergency slide activation shebel 31 to open the door 24.
  • FIG. 7 shows an exemplary embodiment of the display device 2 in a schematic block-based representation.
  • the ultrasonic sensor 14 and the inertial measurement unit 48 are connected to the electronics unit 16, which also has two activation signal inputs 56 and 58.
  • the inertial measurement unit 48 may generate via an appropriate logic circuit 60 an activation signal representing a successful landing, in which case the activation signal is sent to the activation signal input 56. Another one
  • Activation signal may be sent to the second activation signal input which represents an activation position of an emergency slide activation lever.
  • the aircraft is on the ground and the escape slide activation lever is in an activation position, monitoring of the detection area 30 is initiated. If it is determined in the electronics unit 16 that an object is within at least one threshold distance 32, 34, an optical signaling 62 and / or an acoustic signaling 64 is triggered.
  • Ultrasonic sensor 14 are connected downstream in order to achieve a desired signal quality.
  • a power supply unit 70 is further connected to the terminal 8.
  • a pin programming unit 72 with the

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Radar, Positioning & Navigation (AREA)
  • General Physics & Mathematics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Acoustics & Sound (AREA)
  • Mechanical Engineering (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Emergency Alarm Devices (AREA)
  • Measurement Of Velocity Or Position Using Acoustic Or Ultrasonic Waves (AREA)
  • Audible And Visible Signals (AREA)

Abstract

La présente invention concerne un dispositif d'affichage (2) destiné à afficher un état d'activation d'un toboggan de secours dans un avion. Ledit dispositif d'affichage comprend : un dispositif d'affichage optique (10) destiné à délivrer un signal optique ; un dispositif de signal acoustique (12) destiné à délivrer un signal acoustique ; un capteur (14) destiné à détecter qu'une personne (54) s'approche du dispositif d'affichage (2) ; et une unité électronique (16) qui est couplée au dispositif d'affichage optique (10), au dispositif de signal acoustique (12) et au capteur (14) et qui est conçue pour activer le dispositif d'affichage optique (10) et/ou le dispositif de signal acoustique (12) lorsqu'une personne (54) s'approche à moins d'une distance limite (32, 34) prédéfinie. Le dispositif d'affichage optique (10), le dispositif de signal acoustique (12), le capteur et l'unité électronique (16) forment en outre une unité modulaire assemblée et compacte qui peut être intégrée dans le revêtement (26) d'une porte d'avion (24).
EP16716016.7A 2016-04-05 2016-04-05 Dispositif d'affichage installable ultérieurement destiné à afficher un état d'activation d'un toboggan de secours dans un avion Withdrawn EP3439961A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2016/057444 WO2017174119A1 (fr) 2016-04-05 2016-04-05 Dispositif d'affichage installable ultérieurement destiné à afficher un état d'activation d'un toboggan de secours dans un avion

Publications (1)

Publication Number Publication Date
EP3439961A1 true EP3439961A1 (fr) 2019-02-13

Family

ID=55750378

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16716016.7A Withdrawn EP3439961A1 (fr) 2016-04-05 2016-04-05 Dispositif d'affichage installable ultérieurement destiné à afficher un état d'activation d'un toboggan de secours dans un avion

Country Status (5)

Country Link
US (1) US10822115B2 (fr)
EP (1) EP3439961A1 (fr)
CN (1) CN109071029B (fr)
CA (1) CA3017774C (fr)
WO (1) WO2017174119A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11955022B2 (en) 2021-08-11 2024-04-09 Rosemount Aerospace Inc. Aircraft door camera system for landing gear monitoring

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US4797657A (en) * 1987-05-27 1989-01-10 Instant Security Systems, Inc. Portable self-contained intrusion detector for passenger aircraft
EP0321994B1 (fr) * 1987-12-21 1993-01-13 The Boeing Company Verrouillage de porte d'avion
FR2644611A1 (fr) * 1989-03-15 1990-09-21 Codema France Organe de commande exterieure pour tous dispositifs de protection, de surveillance et d'alarme caracterises par un systeme de dissuasion audiovisuel actif incorpore
DE19909953A1 (de) * 1999-03-06 2000-09-07 Geze Glas Design Gmbh Sicherungs- und Überwachungseinrichtung
US6676082B2 (en) * 2001-10-26 2004-01-13 The Boeing Company Self-adapting escape slide
GB2416616A (en) * 2004-02-27 2006-02-01 Christopher Yardley Aircraft door handle alarm
DE102004048217B4 (de) * 2004-09-30 2007-04-19 Eurocopter Deutschland Gmbh Luftfahrzeug mit Kabinen-Differenzdruck-Warnsystem
DE602008004092D1 (de) * 2008-04-07 2011-02-03 Airbus Operations Gmbh System und Methode zur Vorbeugung einer unbeabsichtigten Notrutschenentfaltung für ein Flugzeug
DE102011086454A1 (de) * 2011-11-16 2013-05-16 Airbus Operations Gmbh Überwachungsvorrichtung sowie Verfahren zum Überwachen eines Bewegungsprofils eines Anwenders im Bereich eines Betätigungselementes eines Luft- oder Raumfahrzeuges
EP2719625A1 (fr) * 2012-10-11 2014-04-16 Airbus Operations GmbH Signalisation visuelle d'un aéronef
EP2878530B1 (fr) * 2013-11-27 2019-02-27 Airbus Operations GmbH Circuit d'avertissement et dispositif d'avertissement pour aéronef
EP2974963B1 (fr) * 2014-07-18 2018-11-14 Airbus Operations GmbH Appareil pour faire fonctionner une porte d'un aéronef, aéronef comprenant un tel appareil et procédé pour faire fonctionner ladite porte
EP3133018B1 (fr) * 2015-08-19 2018-12-19 Airbus Operations GmbH Dispositif d'affichage et systeme de porte et avion equipe d'un tel dispositif d'affichage

Also Published As

Publication number Publication date
CN109071029B (zh) 2022-08-09
CN109071029A (zh) 2018-12-21
US20190039748A1 (en) 2019-02-07
CA3017774C (fr) 2022-06-21
CA3017774A1 (fr) 2017-10-12
US10822115B2 (en) 2020-11-03
WO2017174119A1 (fr) 2017-10-12

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