EP2923737B1 - Système de lutte contre l'incendie pour un aéronef - Google Patents

Système de lutte contre l'incendie pour un aéronef Download PDF

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Publication number
EP2923737B1
EP2923737B1 EP15161127.4A EP15161127A EP2923737B1 EP 2923737 B1 EP2923737 B1 EP 2923737B1 EP 15161127 A EP15161127 A EP 15161127A EP 2923737 B1 EP2923737 B1 EP 2923737B1
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EP
European Patent Office
Prior art keywords
fire
fire extinguishing
outlet valve
control device
indicating
Prior art date
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Active
Application number
EP15161127.4A
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German (de)
English (en)
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EP2923737A1 (fr
Inventor
Daniel Dreyer
Matthias Oberhauser
Philipp Schmidt
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 Defence and Space GmbH
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Airbus Defence and Space GmbH
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Publication date
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Publication of EP2923737A1 publication Critical patent/EP2923737A1/fr
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Publication of EP2923737B1 publication Critical patent/EP2923737B1/fr
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Classifications

    • A—HUMAN NECESSITIES
    • A62—LIFE-SAVING; FIRE-FIGHTING
    • A62C—FIRE-FIGHTING
    • A62C3/00—Fire prevention, containment or extinguishing specially adapted for particular objects or places
    • A62C3/07—Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles
    • A62C3/08—Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
    • A—HUMAN NECESSITIES
    • A62—LIFE-SAVING; FIRE-FIGHTING
    • A62C—FIRE-FIGHTING
    • A62C37/00—Control of fire-fighting equipment
    • A62C37/36—Control of fire-fighting equipment an actuating signal being generated by a sensor separate from an outlet device
    • A62C37/44—Control of fire-fighting equipment an actuating signal being generated by a sensor separate from an outlet device only the sensor being in the danger zone
    • A—HUMAN NECESSITIES
    • A62—LIFE-SAVING; FIRE-FIGHTING
    • A62C—FIRE-FIGHTING
    • A62C35/00—Permanently-installed equipment
    • A62C35/02—Permanently-installed equipment with containers for delivering the extinguishing substance
    • A62C35/11—Permanently-installed equipment with containers for delivering the extinguishing substance controlled by a signal from the danger zone
    • A62C35/13—Permanently-installed equipment with containers for delivering the extinguishing substance controlled by a signal from the danger zone with a finite supply of extinguishing material

Definitions

  • the invention relates to a fire extinguishing system for an aircraft.
  • the fire extinguishing system comprises a fire detector for detecting fire, a first container containing a pressurized fire extinguishing medium with a switchable first outlet valve for discharging the fire extinguishing medium from the first container, a second container containing a pressurized fire extinguishing medium with a switchable second outlet valve for the outlet of the Fire extinguishing medium from the second container, wherein the first outlet valve and the second outlet valve can each be switched into the closed and open states.
  • the fire extinguishing system comprises a line system connecting the first and second outlet valves with at least one outlet opening, the at least one outlet opening being arranged and designed for discharging the fire extinguishing medium into a predetermined area of the aircraft.
  • the invention further relates to an integrated display and input element for such a fire extinguishing system, a method for operating such a fire extinguishing system, and an aircraft with such a fire extinguishing system.
  • Fire extinguishing systems of the generic type are known (see, for example, " Fundamentals of aircraft technology in theory and practice ", Vol. II, Chapter 16, 1992 edition, Verlag TÜV Rheinland GmbH ). They are used in particular to fight fires from engine fires and from fires in cargo holds (English “cargo compartment”) of aircraft.
  • Such a system for extinguishing a fire in the engine typically comprises at least three operating elements in the cockpit of the aircraft: a first operating element for stopping a fuel supply and, if necessary, for capping other supply lines to and from the engine, a second operating element for the manually triggered release of a fire extinguishing agent in the engine a first container, and a third control element for the manually triggered release of a fire extinguishing agent in the engine from a second container.
  • the presence of a fire is detected by a fire detector arranged in the engine and signaled acoustically and optically by an output unit in the cockpit.
  • Such a typical fire extinguishing system therefore requires multiple handling and checking of the fire signaling or operating several control elements over a period of at least 30 - 60 s.In an emergency situation with fires, however, time is valuable and should not be wasted on monitoring and operating the fire extinguishing system . Furthermore, it must be stated that incorrect operation of fire extinguishing systems can occur in emergency situations despite intensive pilot training.
  • the fire extinguishing system comprises at least one extinguishing agent reservoir with an activatable closure means which, in an activated state, enables the extinguishing agent to flow out of the extinguishing agent reservoir, and a supply line connected to the closure means and at least one outlet opening, with which the extinguishing agent can be fed from the extinguishing agent reservoir to the outlet opening to spread it there for fire fighting.
  • the fire extinguishing system further comprises a control unit which is connected to the closure means and a manually operated input means and can be activated by the closure means.
  • the fire extinguishing system comprises one or more sensor systems by means of which a current aircraft state can be determined, the control unit being designed and set up in such a way that the closure means is activated depending on the current flight state present at the time the input is actuated.
  • a fire extinguishing system for an aircraft is known.
  • the fire extinguishing system comprises several containers with a fire extinguishing agent that can be directed to one of several fire fighting zones via valves.
  • the release of the fire extinguishing agent from a container is initiated by manually pressing a pressure switch.
  • the fire extinguishing agent is released from a further filled container by repeatedly pressing the pressure switch.
  • the object is therefore to further develop a generic fire extinguishing system for an aircraft in such a way that operating errors of the fire extinguishing system are avoided and the time required to operate the fire extinguishing system is reduced.
  • the fire extinguishing system comprises a fire detector for detecting fire, a first container containing a pressurized fire extinguishing medium with a switchable first outlet valve for discharging the fire extinguishing medium from the first container, and a second container containing a pressurized fire extinguishing medium with a switchable second outlet valve for the outlet the fire extinguishing medium from the second container.
  • the first outlet valve and the second outlet valve can each be switched into the "closed” and "open” states.
  • the fire extinguishing system comprises a line system connecting the first and second outlet valves with at least one outlet opening, the at least one outlet opening being arranged and designed for discharging the fire extinguishing medium into a predetermined area of the aircraft.
  • All fire extinguishing agents that are known today and can be used in aviation can be used as fire extinguishing media.
  • the line system advantageously comprises several outlet openings which are arranged in corresponding flammable areas of the aircraft (engine, APU (auxiliary turbine), cargo area, etc.).
  • the proposed fire extinguishing system is characterized in that there is an integrated display and input element that displays a fire alarm and the current status of the first and second outlet valves, and with which a control device is activated by manual input, the control device with the fire detector, the display and input element, and the first and the second exhaust valve is connected.
  • the control device is designed and set up in such a way that it can be activated by manual input only after a fire alarm triggered by the fire detector has been displayed by the display and input element.
  • t 0 the time of activation of the control unit
  • ⁇ t 1 is a predetermined period of time.
  • the fire extinguishing medium of the first container is discharged via the line system and the outlet opening into the area of the aircraft in which the fire detector has detected the fire.
  • the fire extinguishing medium of the first container is discharged via the line system and the outlet opening into the area of the aircraft in which the fire detector has detected the fire.
  • Switching the outlet valves from the “open” state to the “closed” state is advantageously carried out by means of a maintenance measure and requires a reconfiguration of the fire extinguishing system.
  • the time period ⁇ t 1 is advantageously selected in the range between 5 to 30 s and is in particular 10 s or 15 s or 20 s or 25 s.
  • the time period ⁇ t 2 is advantageously selected in the range between 10 to 40 s and is in particular 20 s or 25 s s or 30 s or 35 s.
  • the integrated display and input element significantly reduces the space required for installation in the cockpit compared to the known fire extinguishing system with the associated display and operating elements. Furthermore, there is only one input element with which an automated fire extinguishing process is initiated by a one-time operation.
  • the advantage of the proposed system is that, in the case of a fire alarm triggered by the fire detector and displayed by the display and input element, only one input is required to initialize an automated control of the fire extinguishing system, the current state of the fire extinguishing system always being displayed. The time required to operate the fire extinguishing system is therefore considerably reduced, operating errors are avoided and the space required for integrating the operating and display elements in the cockpit is considerably reduced. This is accompanied advantageously by a reduction in the mass or weight of the fire extinguishing system.
  • the display and input element for displaying a fire alarm advantageously comprises at least one light source, for example a light bulb, an LED or a light guide Decouples light from a light source to display the fire alarm in the display and input element.
  • the fire alarm is preferably displayed with a red light.
  • the display and input element is designed as a button, the button having: a button surface area that can be illuminated to display a fire alarm (preferably red), a first optical display unit arranged in the illuminated button surface to display the current status of the first outlet valve, a second optical display unit arranged in the illuminated button surface to display the current status of the second outlet valve, and a protective device to prevent unintentional or unintentional actuation of the button.
  • the protective device is advantageously designed as a cap which, if necessary, is secured with a further mechanical safety device (safety wire, locking element, etc.).
  • the first and the second optical display unit each have a two-color LED or two single-color LEDs.
  • the state of the respective outlet valve can thus be displayed, for example, in such a way that the state “outlet valve closed” is displayed in green and the state “outlet valve open” is displayed in red.
  • the status of the outlet valves is advantageously only displayed if the control device has been activated beforehand. This enables the so-called “Dark Cockpit Philosophy" to be implemented.
  • the lighting means for displaying a fire alarm is advantageously switched on and off with a frequency between 1 Hz and 5 Hz, in particular with 2 Hz or 3 Hz.
  • One embodiment of the fire extinguishing system is characterized in that the first and the second container each have a sensor for determining a current filling pressure of the fire extinguishing medium.
  • the control device is designed and set up in such a way that, depending on the switching state of the first and the second outlet valve, a congruence check is carried out between the current (switching) states of the outlet valves and the currently determined filling pressures, and if an expected congruence is not determined, a Warning indication by the display and Input element is output.
  • the "outlet valve closed” state also has an associated or corresponding filling pressure, ie a filling pressure that is congruent to it, in particular a filling pressure that corresponds to a container filled with fire extinguishing medium.
  • the "outlet valve open” state also has an assigned or corresponding filling pressure, ie a filling pressure that is congruent to it, in particular that corresponds to a container from which the fire extinguishing medium has been released. If the state of the respective outlet valve does not match the recorded filling pressure of the respective container, a warning display of the display and input element is activated.
  • the warning display can, for example, be an LED, preferably an LED that lights up yellow.
  • the fire detector is preferably arranged in the aircraft in such a way that it can detect a fire in an engine or an auxiliary power unit (APU) or in a cargo hold of the aircraft.
  • the control device is preferably designed and set up in such a way that after it has been activated by the control device, the following is automatically initiated: stopping a fuel supply to the respective engine, and / or switching off one or more electrical generators of the respective engine, and / or stopping a bleed air supply from the respective engine to a passenger cabin or cargo area.
  • the fire can be stopped by stopping the fuel supply to the affected engine.
  • the further measures listed can prevent or limit the effect of the fire on the aircraft and, if applicable, the passengers and crew.
  • the display and input element is advantageously designed in such a way that the status: "Control device activated" is visually displayed. This can be done with a corresponding LED, for example in green.
  • the assigned display and input element has a corresponding light source, for example an LED.
  • the control device is advantageously designed and set up in such a way that once the control device has been activated, it can be withdrawn by a further input in the display and input element, for example by pressing the button again. In this way, the cockpit crew can stop the automatic deletion process again.
  • This renewed input advantageously requires a predefined input pattern, for example one specific sequence of key actuations per time or a key actuation that lasts a predetermined time, for example 3 s or 5 s.
  • the invention further relates to a display and input element for a fire extinguishing system, as stated above, which is designed as a button.
  • the button has: a button surface area that can be illuminated to display a fire alarm, a first optical display unit arranged in the illuminated button surface to display the current status of the first outlet valve, a second optical display unit arranged in the illuminated button surface to display the current status of the second outlet valve, and a protective device to prevent unintentional actuation of the button.
  • the invention finally relates to a method for operating a fire extinguishing system for an aircraft, the fire extinguishing system comprising a fire detector for detecting fire, a first container containing a pressurized fire extinguishing medium with a switchable first outlet valve for discharging the fire extinguishing medium from the first container, and a comprises pressurized fire extinguishing medium containing second container with a switchable second outlet valve for discharging the fire extinguishing medium from the second container.
  • the first outlet valve and the second outlet valve can each be switched into the "closed” and "open” states.
  • the fire extinguishing system comprises a line system connecting the first and the second outlet valve with at least one outlet opening, the at least one outlet opening being arranged and designed for discharging the fire extinguishing medium into a predetermined area of the aircraft, as well as an integrated display and input element, which is connected through the Fire detector triggered fire alarm and the current state of each of the first and second outlet valve, and with which a control device is activated by a manual input, wherein the control device is connected to the fire detector, the display and input element, and the first and the second outlet valve.
  • the control device is designed and set up in such a way that it can be activated by manual input only after a fire alarm has been displayed by the display and input element.
  • the method comprises of the following steps.
  • Fig. 1 shows a schematic representation of an embodiment of the proposed fire extinguishing system fire extinguishing system for an aircraft.
  • the fire extinguishing system comprises a fire detector 111 for detecting fire in an engine 112 of the aircraft.
  • auxiliary turbine APU
  • Corresponding fire detectors are known to the person skilled in the art.
  • the fire extinguishing system comprises a first container 101 containing a pressurized fire extinguishing medium with a switchable first outlet valve 107 for discharging the fire extinguishing medium from the first container 101, and a second container 102 containing a pressurized fire extinguishing medium with a switchable second outlet valve 108 for discharging the Fire extinguishing medium from the second container 102, wherein the first outlet valve 107 and the second outlet valve 108 can each be switched into the "closed” and "open” states.
  • Sensors 105 and 106 are arranged in the first and second containers, respectively, with which a filling pressure of the respective fire extinguishing medium is detected.
  • the fire extinguishing system comprises a line system 109 connecting the first 107 and second 108 outlet valves with at least one outlet opening 110, the at least one outlet opening 109 being arranged and designed for discharging the fire extinguishing medium into a predetermined area of the aircraft.
  • an integrated display and input element 103 which displays a fire alarm and the current status of the first 107 and second 108 outlet valves and with which a control device 104 can be activated by manual input, the control device 104 with the fire detector 111, the display and input element 103, the sensors 105 and 106, and the first 107 and the second 108 outlet valve is connected.
  • the control device 104 is set up so that its activation by manual input is only possible after a fire alarm triggered by the fire detector 111 has been displayed by the display and input element 103.
  • the control device 104 controls the displays output by the display and input element 103.
  • Fig. 2 shows an embodiment of the display and input element 103 in plan view, ie in the view in which a pilot has the display and input element 103 installed Condition in the cockpit.
  • the display and input element comprises a button 201 for manual input, a surface of the button 201 that can be illuminated to display a fire alarm, a first optical display unit with displays 204a-c for displaying the current status of the first outlet valve 107, a second optical display unit with displays 205a -c to display the current state of the second outlet valve 108, and a protective device 202 to prevent unintentional actuation of the button 201.
  • the protective device is designed as a cap 202, which is hinged to hinges 203 and consists of a first actuation of the display and input element 103 Position (as in Fig. 2 shown) can be folded into a second, which enables operation of the display and input element 103.
  • the depicted display and input element 103 each has individual light-emitting diodes LEDs (204a-c, 205a-c, 207) that can be controlled by the control unit 104.
  • the green LED 204a shows the state: first valve 107 "closed”.
  • the green LED 205a shows the state: second valve 108 "closed”.
  • the red glowing LED 204b shows the state: first valve 107 "open”.
  • the red glowing LED 205b shows the status: second valve 108 "closed”.
  • the yellow glowing LED 204c indicates a warning that indicates that there is no congruence between the filling pressure of the fire extinguishing medium in the first container 101 and the state of the first valve 101.
  • the yellow glowing LED 205c indicates a warning, which indicates that there is no congruence between the filling pressure of the fire extinguishing medium in the second container 101 and the state of the second valve 102.
  • the LED 207 can light up either green or red. If it lights up green, it indicates that the control unit 104 has been activated. If it lights up red, it indicates that the activation of the control device 104 has been withdrawn and thus the automatic sequence of method steps initiated thereby has been stopped.
  • the surface that can be illuminated has, in particular, the inscription "FIRE Push", which can only be recognized when a fire alarm is triggered and is displayed accordingly.
  • Fig. 1 it is assumed that no such fire alarm is triggered by the fire detector 111, so that all LEDs and the lighting of the area 201 are off, which corresponds to the so-called "black panel philosophy". It should be noted in this regard that the LEDs or the lighting of the surface 201 are active when the LEDs shown as circles are filled in black or when the writing “FIRE PUSH” can be seen.
  • the Fig. 3a -f show a sequence of the display states of the display and input element 103 according to FIG Fig. 2 after activation of the control unit.
  • Fig. 3a all LEDs and the button surface 201 are illuminated. This state is generated in the context of a so-called "Annunciator Panel Test", which is used to verify that all the lamps on displays in the cockpit are working.
  • Figure 3b the display state of the display and input element 103 is shown when no fire is detected and no system test is carried out. Here all the lighting means of the display and input element 103 are off.
  • the button surface 201 is illuminated in red ( Figure 3c ).
  • the button surface 201 is illuminated by flashing at a frequency of 2 Hz.
  • the protective cap 202 is folded into a position in which the button 201 can be operated. This state of the protective cap 202 is also shown in FIG Figure 3c shown.
  • the control device 104 is activated by pressing the button 201 once. Immediately after activation, the in Fig. 3d Display state shown. The LEDs 204a and 205a light up green. Which means that the first 107 and the second 108 valve are in the closed state. There in Fig. 3d If the LEDs 204c and 205c do not light up, this means that the fire extinguishing agent is present in the containers 107 and 108 with sufficient filling pressure. Furthermore, the LED 207 lights up green, which indicates that the control device 104 is activated and thus the automatic sequence of automatic steps is activated. After the activation of the control device 104, the flashing of the button surface 201 changes to a continuous light. In one embodiment, pressing the button 201 also cuts off the fuel supply to the engine 112, the power supply between the engine 112 and the aircraft, and the bleed-air line for cabin printing.
  • the first valve 107 is automatically opened when the fire detector 111 still detects fire, so that its fire extinguishing agent can be sent via the lines 109 and the outlet opening 110 enters the engine 112 in order to extinguish the fire there.
  • ⁇ t 1 10 s. Since the state of the first valve 107 changes from "closed” to "open", the display state of the display and input element 103 also changes in that the green LED 204a goes out and the red LED 204b lights up (see Fig. 3e ).
  • This display state thus indicates that the first container 107 does not contain any fire extinguishing agent, while the second container 108 has unchanged fire extinguishing agent with a sufficient filling pressure.
  • the LED 204a can also flash green in the time segment in which the fire extinguishing agent leaves the first container 107, and only when there is no longer any fire extinguishing agent in the first container, can be switched off and the red illuminated LED 204b can be switched on.
  • Fig. 4 shows a representation of a flow chart after activation of the control device, as has already been explained above.
  • the flow chart comprises the self-explanatory steps 401 to 405.

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  • Health & Medical Sciences (AREA)
  • Public Health (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Fire-Extinguishing By Fire Departments, And Fire-Extinguishing Equipment And Control Thereof (AREA)

Claims (14)

  1. Système d'extinction d'incendie destiné à un aéronef, ledit système comprenant
    - un détecteur d'incendie (111) destiné à détecter un incendie,
    - un premier récipient (101) contenant un milieu d'extinction d'incendie sous pression et pourvu d'une première vanne de sortie commutable (107) destinée à évacuer le milieu d'extinction d'incendie du premier récipient (101),
    - un deuxième récipient (102) contenant un milieu d'extinction sous pression et pourvu d'une deuxième vanne de sortie commutable (108) destinée à évacuer le milieu d'extinction d'incendie du deuxième récipient (102), la première vanne de sortie (107) et la deuxième vanne de sortie (108) étant chacune commutables dans les états fermé et ouvert,
    - un système de conduites (109) reliant les première (107) et deuxième (108) vannes de sortie à au moins une ouverture de sortie (110), l'au moins une ouverture de sortie (109) étant disposée et conçue pour évacuer le milieu d'extinction d'incendie dans un zone spécifiée de l'aéronef, caractérisé en ce qu'un élément d'indication et d'entrée intégré (103) est prévu qui produit une alarme incendie et l'état actuel des première (107) et deuxième (108) vannes de sortie, et qui permet d'activer un organe de commande (104) par une entrée manuelle, l'organe de commande (104) étant relié au détecteur d'incendie (111), à l'élément d'indication et d'entrée (103) et aux première (107) et deuxième (108) vannes de sortie,
    l'organe de commande (104) étant conçu et réalisé de telle sorte que :
    - son activation par entrée manuelle ne soit possible qu'après qu'une alarme incendie déclenchée par le détecteur d'incendie (111) a été produite par l'élément d'indication et d'entrée (103),
    - l'organe de commande (104) commute automatiquement, après son activation, la première vanne de sortie (107) à l'état ouvert à un instant t1 = t0 + Δt1, à condition que le détecteur d'incendie (111) détecte toujours un incendie à l'instant t1, t0 étant l'instant d'activation de l'organe de commande (104) et Δt1 étant une durée spécifiée, et
    - l'organe de commande (104) commute ensuite automatiquement la deuxième vanne de sortie (108) à l'état ouvert à un instant t2 = t1 + Δt2, à condition que le détecteur d'incendie (111) détecte toujours un incendie à l'instant t2, Δt2 étant une durée spécifiée.
  2. Système d'extinction d'incendie selon la revendication 1,
    dans lequel l'élément d'indication et d'entrée (103) destiné à produire une alarme incendie comprend une source lumineuse.
  3. Système d'extinction d'incendie selon la revendication 1 ou 2,
    dans lequel l'élément d'indication et d'entrée (103) comprend :
    - un bouton (201) destiné à l'entrée manuelle,
    - une surface du bouton (201) qui peut être éclairée pour produire une alarme incendie
    - une première unité d'indication optique (204a-b) destinée à produire l'état actuel de la première vanne de sortie (107),
    - une deuxième unité d'indication optique (205a-b) destinée à produire l'état actuel de la deuxième vanne de sortie (108), et
    - un dispositif de protection (202) destiné à empêcher l'actionnement intempestif du bouton (201).
  4. Système d'extinction d'incendie selon la revendication 3.
    dans lequel le dispositif de protection (202) est réalisé sous la forme d'un capuchon.
  5. Système d'extinction d'incendie selon la revendication 3 ou 4,
    dans lequel la première (204a-b) et la deuxième (205a-b) unité d'indication optique comportent chacune une LED bicolore ou deux LED monocolores.
  6. Système d'extinction d'incendie selon l'une des revendications 2 à 5,
    dans lequel la source lumineuse d'indication d'une alarme incendie est allumée et éteinte à une fréquence comprise entre 1 Hz et 5 Hz, notamment de 2 Hz ou 3 Hz.
  7. Système d'extinction d'incendie selon l'une des revendications 1 à 6,
    dans lequel la durée Δt1 est comprise entre 5 et 30 s et en particulier est de 10 s ou 15 s ou 20 s.
  8. Système d'extinction d'incendie selon l'une des revendications 1 à 7,
    dans lequel la durée Δt2 est comprise entre 10 et 40 s et notamment est de 20 s ou 25 s ou 30 s ou 35 s.
  9. Système d'extinction d'incendie selon l'une des revendications 1 à 8,
    dans lequel le premier (101) et le deuxième récipient (102) comportent chacun un capteur (105, 106) destiné à déterminer une pression de remplissage actuelle du milieu d'extinction d'incendie, et l'organe de commande (104) est conçu et réalisé de manière à effectuer, en fonction de l'état de commutation des première (107) et deuxième (108) vannes de sortie, un essai de concordance entre les états de commutation actuels des vannes de sortie (107, 108) et les pressions de remplissage actuellement déterminées et, si une concordance attendue n'est pas déterminée, une indication d'alarme (204c, 205c) est délivrée par l'élément d'indication et d'entrée (103).
  10. Système d'extinction d'incendie selon l'une des revendications 1 à 9,
    dans lequel le détecteur d'incendie (111) est disposé de manière à pouvoir détecter un incendie dans un propulseur ou un propulseur auxiliaire (112) de l'avion, et l'organe de commande (104) est conçu et réalisé de manière que, après son activation, l'organe de commande (104) ordonne automatiquement :
    - de cesser une alimentation en carburant du propulseur respectif (112), et/ou
    - d'arrêter un ou plusieurs générateurs électriques du propulseur respectif (112), et/ou
    - de cesser une amenée d'air de distribution allant du propulseur respectif (112) à une cabine passagers ou à une soute.
  11. Système d'extinction d'incendie selon l'une des revendications 1 à 10,
    dans lequel l'état : « organe de commande activé » est indiqué optiquement dans l'élément d'indication et d'entrée (103) à l'aide d'un moyen d'indication (207).
  12. Système d'extinction d'incendie selon l'une des revendications 1 à 11,
    dans lequel l'organe de commande (104) est conçu et réalisé de manière qu'une activation effective de l'organe de commande (104) puisse être supprimée par une autre entrée dans l'élément d'indication et d'entrée (103) .
  13. Aéronef comprenant un système d'extinction d'incendie selon l'une des revendications 1 à 12, dans lequel l'au moins une ouverture de sortie (110) est ménagée dans un propulseur ou propulseur auxiliaire (112), une cabine passagers ou une soute de l'aéronef et l'élément d'indication et d'entrée (103) est disposé dans le cockpit de l'avion.
  14. Procédé de fonctionnement d'un système d'extinction d'incendie destiné à un aéronef, le système d'extinction d'incendie comprenant :
    - un détecteur d'incendie (111) destiné à détecter un incendie,
    - un premier récipient (101) contenant un milieu d'extinction d'incendie sous pression et pourvu d'une première vanne de sortie commutable (107) destinée à évacuer le milieu d'extinction d'incendie du premier récipient (101),
    - un deuxième récipient (102) contenant un milieu d'extinction sous pression et pourvu d'une deuxième vanne de sortie commutable (108) destinée à évacuer le milieu d'extinction d'incendie du deuxième récipient (102), la première vanne de sortie (107) et la deuxième vanne de sortie (108) étant chacune commutables dans les états fermé et ouvert,
    - un système de conduites (109) reliant les première (107) et deuxième (108) vannes de sortie à au moins une ouverture de sortie (110), l'au moins une ouverture de sortie (110) étant disposée et conçue pour évacuer le milieu d'extinction d'incendie dans un zone spécifiée de l'aéronef,
    - un élément d'indication et d'entrée intégré (103) qui produit une alarme incendie déclenchée par le détecteur d'incendie (111) et l'état actuel des première (107) et deuxième (108) vannes de sortie, et qui permet d'activer un organe de commande (104) par une entrée manuelle, l'organe de commande (104) étant relié au détecteur d'incendie (111), à l'élément d'indication et d'entrée (103) et aux première (107) et deuxième (108) vannes de sortie,
    l'organe de commande (104) étant conçu et réalisé de telle sorte que son activation par entrée manuelle ne soit possible qu'après qu'une alarme incendie a été produite par l'élément d'indication et d'entrée (103), le procédé comprenant les étapes suivantes :
    - après une activation effective de l'organe de commande (104) à un instant t0, une commutation automatique de la première vanne de sortie (107) à l'état ouvert est effectuée à un instant t1 = t0 + Δt1 par l'organe de commande (104) à condition que le détecteur d'incendie (111) détecte toujours un incendie à l'instant t1, Δt1 étant une durée spécifiée, et
    - une commutation automatique de la deuxième vanne de sortie (108) à l'état ouvert est ensuite effectuée à un instant t2 = t1 + Δt2 par l'organe de commande (104) à condition que le détecteur d'incendie (111) détecte toujours un incendie à l'instant t2, Δt2 étant une durée spécifiée.
EP15161127.4A 2014-03-27 2015-03-26 Système de lutte contre l'incendie pour un aéronef Active EP2923737B1 (fr)

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DE102017128486A1 (de) * 2017-11-30 2019-06-06 Airbus Operations Gmbh Flugzeug und Verfahren zum Kontrollieren einer Löschmittelkonzentration in einem Frachtraum

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US4351394A (en) * 1979-12-28 1982-09-28 Enk William A Method and system for aircraft fire protection
US4482018A (en) * 1981-11-25 1984-11-13 William A. Enk Fire protection system for aircraft
KR101514177B1 (ko) * 2005-01-12 2015-04-22 이클립스 에어로스페이스, 인크. 화재 진압 시스템
DE102010025054A1 (de) * 2010-06-25 2011-12-29 Airbus Operations Gmbh Feuerlöschsystem für ein Flugzeug und Verfahren zur Feuerbekämpfung in einem Flugzeug

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