EP2923737A1 - 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
EP2923737A1
EP2923737A1 EP15161127.4A EP15161127A EP2923737A1 EP 2923737 A1 EP2923737 A1 EP 2923737A1 EP 15161127 A EP15161127 A EP 15161127A EP 2923737 A1 EP2923737 A1 EP 2923737A1
Authority
EP
European Patent Office
Prior art keywords
fire
display
time
input element
fire extinguishing
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.)
Granted
Application number
EP15161127.4A
Other languages
German (de)
English (en)
Other versions
EP2923737B1 (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
Original Assignee
Airbus Defence and Space 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 Defence and Space GmbH filed Critical Airbus Defence and Space GmbH
Publication of EP2923737A1 publication Critical patent/EP2923737A1/fr
Application granted granted Critical
Publication of EP2923737B1 publication Critical patent/EP2923737B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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 includes a fire detector for detecting fire, a first container containing a pressurized fire extinguishing medium having a switchable first outlet valve to the outlet of the fire extinguishing medium from the first container, a second container containing a pressurized fire extinguishing medium having a switchable second outlet valve to the outlet of the Fire extinguishing medium from the second container, wherein the first exhaust valve and the second exhaust valve are respectively closed in the states and openly switchable.
  • the fire-extinguishing system comprises a line system connecting the first and the second outlet valve with at least one outlet opening, wherein the at least one outlet opening for dispensing the fire-extinguishing medium is arranged and configured in a predetermined area of the aircraft.
  • the invention further relates to an integrated display and input element for a similar fire extinguishing system, a method for operating such a fire extinguishing system, as well as an aircraft with such a fire extinguishing system.
  • Generic fire extinguishing systems are known. They are used in particular for the firefighting of engine fires and fires in cargo compartments ("cargocompartment") of aircraft.
  • Such an engine fire extinguishing system typically includes at least three controls in the cockpit of the aircraft: a first control to stop fueling and possibly cap other service lines to and from the engine; a second control to manually trigger a fire extinguishing agent in the engine a first container, and a third operating element for 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 located in the engine and acoustically and optically signaled by an output unit in the cockpit.
  • the fire extinguishing system includes a fire detector for detecting fire, a first container containing a pressurized fire extinguishing medium having a switchable first outlet valve to the outlet of the fire extinguishing medium from the first container, and a second container containing a pressurized fire extinguishing medium having a switchable second outlet valve to the outlet of the fire extinguishing medium from the second container.
  • the first exhaust valve and the second exhaust valve are in each case in the states "closed” and "open” switchable.
  • the fire-extinguishing system comprises a line system connecting the first and the second outlet valve with at least one outlet opening, wherein the at least one outlet opening for dispensing the fire-extinguishing medium is arranged and configured in a predetermined area of the aircraft.
  • a fire-extinguishing medium are all known today and aviation fire extinguishing agent into consideration.
  • the line system advantageously comprises a plurality of 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 an integrated display and input element is present, which indicates a fire alarm and the current state of each of the first and second exhaust valves, and with which a control device is activated by a manual input, wherein the control unit with the fire detector, the display and input element, and the first and the second exhaust valve is connected.
  • the control unit is designed and set up such that its activation by manual input is only possible after the display of a fire alarm triggered by the fire detector by the display and input element.
  • the fire extinguishing medium of the first container is discharged via the line system and the outlet opening in the region of the aircraft in which the fire detector has detected the fire.
  • a switching of the exhaust valves from the state “open” to the state “closed” is advantageously carried out by 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 or 30 s or 35 s.
  • the integrated display and input element reduces the space required for installation space in the cockpit compared to the known fire extinguishing system with the associated display and controls considerably. Furthermore, only one input element is present with which an automated fire extinguishing process is initiated by a single operation.
  • the advantage of the proposed system lies in particular, that when triggered by the fire detector and displayed by the display and input element fire alarm only an input for initialization of an automatically running control of the fire extinguishing system required, the current state of the fire extinguishing system is always displayed up-to-date. The time required to operate the fire extinguishing system is therefore considerably reduced, operating errors are avoided and the space required for integration of the control and display elements in the cockpit is considerably reduced. This is accompanied by a reduction in the mass or weight of the fire extinguishing system advantageous.
  • the display and input element for displaying a fire alarm comprises at least one light source, for example a light bulb, an LED or a light guide, which decouples light from a light source for displaying the fire alarm in the display and input element.
  • the display of the fire alarm is preferably done with red light.
  • the display and input element is designed as a pushbutton, the pushbutton comprising: a button surface area which is illuminated to display a fire alarm (preferably red), a first optical display unit arranged in the illuminated button surface for indicating the current state of the first outlet valve, a second optical display unit arranged in the illuminated pushbutton surface for indicating the current state of the second outlet valve, and a protective device for preventing an undesired or unintentional actuation of the pushbutton.
  • the protective device is advantageously designed as a cap, which is optionally secured with a further mechanical security (safety wire, locking element, etc.).
  • the first and second optical display units each have a two-color LED or two single-color LEDs.
  • the state of the respective exhaust valve may be displayed, for example, such that the state “exhaust valve closed” in green color and the state “exhaust valve open” in red color is displayed.
  • the state of the exhaust valves is displayed only if the control unit has been previously activated. As a result, the so-called “Dark Cockpit Philosophy" can be implemented.
  • the light source for indicating a fire alarm with a frequency between 1 Hz and 5 Hz, in particular with 2 Hz or 3 Hz, is advantageously switched on and off.
  • An 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 unit is embodied and set up such that, depending on the switching state of the first and second exhaust valves, a congruence check is performed between the current (switching) states of the exhaust valves and the currently determined filling pressures, and unless an expected congruence is determined Warning display is issued by the display and input element. In this congruence test, it is determined, depending on the detected state of the exhaust valve, whether the condition "exhaust valve closed" also has an associated or corresponding filling pressure, i.
  • a congruent filling pressure in particular a filling pressure corresponding to a container filled with fire-extinguishing medium.
  • a congruent filling pressure is present, in particular corresponding to a container from which the fire-extinguishing medium has been released. If the state of the respective outlet valve does not coincide with the detected filling pressure of the respective container, a warning display of the display and input element is activated.
  • the warning display may, for example, be an LED, preferably a yellow LED.
  • the fire detector is preferably arranged in the aircraft so that a fire in an engine or an auxiliary power unit (APU) or a loading space of the aircraft can be detected by it.
  • the control unit is preferably embodied and set up such that it is automatically triggered by the control unit after it has been activated: stopping a fuel supply to the respective engine, and / or switching off one or more electric generators of the respective engine, and / or stopping a bleed air supply from the respective engine in a passenger cabin or in a cargo area. Stopping the fuel supply to the affected engine can stop the fire become.
  • the further measures mentioned may prevent or limit the impact of the fire on the aircraft and possibly on the passengers and crew.
  • the display and input element is designed such that status: "control unit activated" is displayed optically. This can be done with a corresponding LED, for example. In green color.
  • the assigned display and input element has a corresponding light source, for example an LED.
  • control unit is designed and set up such that once the control unit has been activated, it can be withdrawn by a further input into the display and input element, for example by a renewed actuation of the pushbutton. So the cockpit crew can stop the automatic execution of the deletion process again.
  • this reentry requires a given input pattern, for example, a particular sequence of keystrokes per time, or a keystroke that lasts for a predetermined time, eg, 3 seconds or 5 seconds. Thus, it can be prevented that the execution of the deletion process is unintentionally withdrawn.
  • 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 comprises: a button surface area illuminatable for displaying a fire alarm, a first optical display unit arranged in the illuminated button surface for displaying the current state of the first outlet valve, a second optical display unit arranged in the illuminable button surface for indicating the current state of the second outlet valve, and a protection device for preventing accidental operation of the button.
  • the invention further relates to an aircraft with a fire extinguishing system, as described above, in which the at least one exhaust valve in an engine, an auxiliary turbine (APU), a passenger compartment or a cargo compartment of the aircraft is arranged, and wherein the integrated display and input element in Cockpit of the aircraft is arranged.
  • the at least one exhaust valve in an engine, an auxiliary turbine (APU), a passenger compartment or a cargo compartment of the aircraft is arranged, and wherein the integrated display and input element in Cockpit of the aircraft is arranged.
  • at least one respective fire detector and a respective associated display and input element are present in the aircraft for each engine and the APU.
  • the invention relates to a method of operating a fire extinguishing system for an aircraft, the fire extinguishing system comprising a fire detector for detecting fire, a pressurized fire extinguishing medium containing a first container with a switchable first outlet valve to the outlet of the fire extinguishing medium from the first container, and a pressurized fire extinguishing medium comprising second container having a switchable second outlet valve to the outlet of the fire extinguishing medium from the second container.
  • the first exhaust valve and the second exhaust valve are each in the states “closed” and "open” switchable.
  • the fire extinguishing system comprises a first and the second outlet valve with at least one outlet opening connecting line system, wherein the at least one outlet opening for discharging the fire extinguishing medium is arranged and formed in a predetermined region of the aircraft, and an integrated display and input element, one through the Fire detector triggered fire alarm and indicates the current state of each of the first and second exhaust valves, and with which a controller is activated by a manual input, wherein the controller with the fire detector, the display and input element, and the first and the second exhaust valve is connected ,
  • the control unit is designed and set up such that its activation by manual input is only possible after a fire alarm has been displayed by the display and input element.
  • the method comprises 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 includes 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 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 extinguishing medium with a switchable second outlet valve 108 to the outlet of the Fire extinguishing medium from the second container 102, wherein the first exhaust valve 107 and the second exhaust valve 108 are respectively in the states "closed” and "open” switchable.
  • sensors 105 and 106 are arranged, 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 the second 108 outlet valve to at least one outlet opening 110, the at least one outlet opening 109 being arranged and configured for dispensing 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 state of each of the first 107 and the second exhaust valve 108 and with a controller 104 is activated by a manual input, wherein the controller 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 exhaust valve is connected.
  • the controller 104 is configured to have its Activation by manual input is only possible after the display of a fire alarm triggered by the fire detector 111 fire alarm by the display and input element 103.
  • the controller 104 controls the displays output from 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 sees the display and input element 103 in the installed state in the cockpit.
  • the display and input member includes a manual input key 201, a button of the button 201 illuminated to display a fire alarm, a first optical display unit with displays 204a-c for displaying the current state of the first exhaust valve 107, a second optical display unit with displays 205a -c for indicating the current state of the second exhaust valve 108, and a protection device 202 for preventing an unwanted actuation of the button 201.
  • Protective device is designed as a cap 202, which is hinged to hinges 203 and from an actuation of the display and input element 103 preventing first Position (as in Fig. 2 shown) in a second, which allows an operation of the display and input element 103.
  • the illustrated display and input element 103 in each case has individual light-emitting diode LEDs (204a-c, 205a-c, 207) which can be controlled by the control device 104.
  • the green LED 204a indicates the state: first valve 107 "closed”.
  • the green LED 205a indicates the state: second valve 108 "closed”.
  • the red LED 204b indicates the state: first valve 107 "open”.
  • the red LED 205b indicates the state: second valve 108 "closed”.
  • the amber LED 204c indicates a warning indicating that there is no congruence between the filling pressure of the fire extinguishing medium in the first tank 101 and the state of the first valve 101.
  • the amber LED 205c indicates a warning indicating that there is no match between filling pressure of the fire extinguishing medium in the second container 101 and the state of the second valve 102 is present.
  • the LED 207 can light up either green or red. If it is green, it indicates that the controller 104 has been activated. If it is red, it indicates that the activation of the controller 104 has been canceled and thus the automatic sequence of steps initiated thereby is stopped.
  • the illuminable surface has in particular the caption "FIRE Push", which can only be recognized when a fire alarm is triggered and 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 illumination of the surface 201 are off, which corresponds to the so-called “black panel philosophy". It should be noted that the LEDs or the illumination of the surface 201 are active when the LEDs shown as circles are filled in black, or if the words "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 controller.
  • Fig. 3a All LEDs and the button surface 201 are illuminated. This condition is generated as part of a so-called "Annunciator Panel Test", which serves to verify that all bulbs of displays in the cockpit work.
  • Fig. 3b the display state of the display and input element 103 is shown when no fire is detected and no system test is performed. Here all bulbs of the display and input element 103 are off.
  • the button surface 201 illuminates red ( Fig. 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 in Fig. 3c shown.
  • the control unit 104 is activated.
  • the in Fig. 3d shown display state.
  • the LEDs 204a and 205a are lit in green. Which means that the first 107 and the second 108 valve are closed in the state. Because in Fig. 3d the LEDs 204c and 205c are off, this means that the fire extinguishing agent is present in containers 107 and 108 with sufficient filling pressure.
  • the LED 207 lights green, indicating that the controller 104 is activated and thus the automatic sequence of automatic steps is activated.
  • the flashing of the button surface 201 changes to a continuous lighting.
  • pressing the button 201 also cuts off the supply of fuel to the engine 112, the power supply between the engine 112 and the aircraft, and the bleed-air line for cabin pressurization.
  • This display state thus indicates that the first container 107 does not contain any fire-extinguishing agent, while the second container 108 has, as before, fire-extinguishing means with a sufficient filling pressure.
  • the LED 204a may also flash green in the period in which the fire extinguishing agent of the first container 107 exits and only when no extinguishant is present in the first container, and the red lit LED 204b may be turned on.
  • the fire detector 111 does not detect fire in the engine 112
  • the automatic operation is stopped by the controller 104 and the illumination of the button surface 201 is turned off.
  • the second container does not contain any more fire extinguishing agent then the in Fig. 3f shown display state. It should be noted that as long as the fire detector 111 detects fire, the button surface 201 is continuously illuminated. As a result, the display state of Fig.3f that despite the application of fire extinguishing agent from the first and second tank, the fire could not be extinguished.
  • Fig. 4 shows a representation of a flowchart after activation of the control unit, as already explained above.
  • the flowchart includes the self-explanatory steps 401-405.

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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)
EP15161127.4A 2014-03-27 2015-03-26 Système de lutte contre l'incendie pour un aéronef Active EP2923737B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102014104302.2A DE102014104302A1 (de) 2014-03-27 2014-03-27 Feuerlöschsystem für ein Luftfahrzeug

Publications (2)

Publication Number Publication Date
EP2923737A1 true EP2923737A1 (fr) 2015-09-30
EP2923737B1 EP2923737B1 (fr) 2021-10-13

Family

ID=52780883

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15161127.4A Active EP2923737B1 (fr) 2014-03-27 2015-03-26 Système de lutte contre l'incendie pour un aéronef

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EP (1) EP2923737B1 (fr)
DE (1) DE102014104302A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110015438A (zh) * 2017-11-30 2019-07-16 空中客车运作有限责任公司 飞行器和用于控制货舱空间中的灭火剂浓度的方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4482018A (en) * 1981-11-25 1984-11-13 William A. Enk Fire protection system for aircraft
EP2399649A2 (fr) * 2010-06-25 2011-12-28 Airbus Operations GmbH Système anti-feu pour aéronef et procédé de lutte contre les incendies à bord d'un aéronef

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4351394A (en) * 1979-12-28 1982-09-28 Enk William A Method and system for aircraft fire protection
KR101514177B1 (ko) * 2005-01-12 2015-04-22 이클립스 에어로스페이스, 인크. 화재 진압 시스템

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4482018A (en) * 1981-11-25 1984-11-13 William A. Enk Fire protection system for aircraft
EP2399649A2 (fr) * 2010-06-25 2011-12-28 Airbus Operations GmbH Système anti-feu pour aéronef et procédé de lutte contre les incendies à bord d'un aéronef

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110015438A (zh) * 2017-11-30 2019-07-16 空中客车运作有限责任公司 飞行器和用于控制货舱空间中的灭火剂浓度的方法

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Publication number Publication date
EP2923737B1 (fr) 2021-10-13
DE102014104302A1 (de) 2015-10-01

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