EP2923737B1 - Fire extinguishing system for an aircraft - Google Patents

Description

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. Furthermore, 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.

From the EP 2 399 649 A2 a fire extinguishing system for an aircraft is known. 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. Furthermore, 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.

From the U.S. 4,482,018 A 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 invention results from the features of the independent claims. Advantageous further developments and refinements are the subject matter of the dependent claims. Further features, possible applications and advantages of the invention emerge from the following description, as well as the explanation of exemplary embodiments of the invention, which are shown in the figures.

One aspect of the object according to the device is achieved with 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, 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. Furthermore, 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. After activation, the control unit automatically switches the first outlet valve to the "open" state _{at a time t 1} = t ₀ + Δt ₁ , provided the fire detector still detects fire _{at time t 1 , where t 0 is} the time of activation of the control unit and Δt _{1 is} a predetermined period of time. As a result, 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. Furthermore, the control unit then automatically switches the second outlet valve to the "open" state _{at a time t 2} = t ₁ + Δt ₂ , provided that the fire detector still detects fire _{at time t 2 , with Δt 2 being} a predetermined period of time. As a result, 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 Δt 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 Δt 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.

In a particularly advantageous embodiment, 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.).

In one embodiment, 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.

In order to draw the attention of the cockpit crew specifically to the display of a fire alarm triggered by the fire detector, 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. In this embodiment, 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. In this congruence check, depending on the detected state of the outlet valve, it is determined whether 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. In other words, it is determined whether 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. For this purpose, 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. Furthermore, 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.

After the control device has been activated at a time t ₀ by manual input into the display and input element, the control device automatically switches the first outlet valve to the "open" state _{at a time t 1} = t ₀ + Δt _{1, if} the fire detector still detects fire at time t _{1 , where Δt 1 is} a predetermined period of time. Subsequently, at a time t ₂ = t ₁ + Δt ₂ , the control device automatically switches the second outlet valve to the "open" state, provided that the fire detector still detects fire _{at time t 2 , with Δt 2 being} a predetermined period of time.

Further advantages, features and details emerge from the following description in which - possibly with reference to the drawing - at least one exemplary embodiment is described in detail. Identical, similar and / or functionally identical parts are provided with the same reference symbols.

Fig. 1

schematisierte Darstellung einer Ausführungsform des vorgeschlagenen Feuerlöschsystems,

Fig. 2

eine Ausführungsform des Anzeige- und Eingabeelements

Fig. 3a-f

eine Abfolge der Anzeigen des Anzeige- und Eingabeelements gemäß Fig. 2 nach einer Aktivierung des Steuergeräts, und

Fig. 4

Darstellung eines Ablaufplans nach Aktivierung des Steuergeräts.

Show it:

Fig. 1

schematic representation of an embodiment of the proposed fire extinguishing system,

Fig. 2

an embodiment of the display and input element

Figures 3a-f

a sequence of displays of the display and input element according to Fig. 2 after activation of the control unit, and

Fig. 4

Representation of a flow chart after activation of the control unit.

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. The engine can also have an auxiliary turbine (Auxiliray Power Unit = APU) be. Corresponding fire detectors are known to the person skilled in the art. Furthermore, 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. Furthermore, 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.

Furthermore, there is 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. Furthermore, after its activation, the control device 104 automatically switches the first outlet valve 107 to the open state _{at a time t 1} = t ₀ + Δt ₁ , provided that the fire detector 111 still detects fire _{at time t 1 , where t 0 is} the time of activation of the control _{device 104 and Δt 1 is} a predetermined period of time, and the control device 104 then automatically switches the second outlet valve 108 to the open state _{at a time t 2} = t ₁ + Δt ₂ , provided that the fire detector 111 still detects fire _{at time t 2,} where Δt _{2 is} a predetermined period of time. 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. In 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 reference symbols of the Fig. 2 apply in the following also to the Figures 3a-f .

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. In 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. In 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.

If a fire is detected by the fire detector 111, the button surface 201 is illuminated in red ( Figure 3c ). The button surface 201 is illuminated by flashing at a frequency of 2 Hz. After the crew has recognized the fire warning, 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.

After a time t ₁ = Δt ₁ + t ₀ after the activation of the control _{device at time t 0} , 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. In the present case, Δt 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. In one embodiment, 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.

If the fire is extinguished by the above measure, ie the fire detector 111 does not detect a fire in the engine 112, the automatic sequence is stopped by the control device 104 and the lighting of the button surface 201 is switched off. However, if this measure does not extinguish the fire, ie the fire detector 111 continues to detect fire in the engine 112, then the control unit 104 automatically opens the second valve 108 _{at a time t 2} = t ₁ + Δt _2. In the present case, Δt ₁ = 15 s. If the second container then no longer contains any fire extinguishing agent, then the in Fig. 3f Display state shown. It should be noted that as long as the fire detector 111 detects fire, the button surface 201 is continuously illuminated. Accordingly, the display state of FIG Fig.3f indicates that the fire could not be extinguished despite the application of fire extinguishing agent from the first and second containers.

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.

Although the invention has been illustrated and explained in more detail by preferred exemplary embodiments, the invention is not restricted by the disclosed examples and other variations can be derived therefrom by the person skilled in the art without departing from the scope of protection of the invention, which is defined in the claims. It is therefore clear that there is a multitude of possible variations. It is also clear that the exemplary embodiments mentioned are really only examples that are not in any way intended to limit the scope of protection, the possible applications or the configuration of the Invention are to be understood. Rather, the preceding description and the description of the figures enable the person skilled in the art to implement the exemplary embodiments in concrete terms, whereby the person skilled in the art, with knowledge of the disclosed inventive concept, can make various changes, for example with regard to the function or the arrangement of individual elements mentioned in an exemplary embodiment, without the To leave the scope of protection defined by the claims.

Reference number

101

first container

102

second container

103

Display and input element

104

Control unit

105, 106

Sensor for recording the filling pressure

107

first valve

108

second valve

109

Line for the fire extinguishing agent

110

Outlet opening

111

Fire detector

112

Engine or APU

201

Button / button surface

202

protective cap

203

Hinges

204a-c

LEDs to display the status of the first container or the first valve

205a-c

LEDs to display the status of the second container or the second valve

206

Top of the display and input element

207

two-color LED to indicate the activation status of the control unit

401-405

Procedural steps

Claims (14)

1. Fire extinguishing system for an aircraft, with

   - a fire detector (111) for detecting fire,

   - a first container (101), containing pressurized fire extinguishing medium, with a switchable first outlet valve (107) for letting out the fire extinguishing medium from the first container (101),

   - a second container (102), containing pressurized fire extinguishing medium, with a switchable second outlet valve (108) for letting out the fire extinguishing medium from the second container (102), wherein the first outlet valve (107) and the second outlet valve (108) are each switchable into the closed and open states,

   - a system of lines (109) connecting the first outlet valve (107) and the second outlet valve (108) to at least one outlet opening (110), wherein the at least one outlet opening (109) is arranged and designed for delivering the fire extinguishing medium into a predetermined area of the aircraft,
   characterized in that there is an integrated indicating and inputting element (103), which indicates a fire alarm and the current state respectively of the first outlet valve (107) and the second outlet valve (108), and with which a control device (104) can be activated by a manual input, wherein the control device (104) is connected to the fire detector (111), the indicating and inputting element (103), and the first outlet valve (107) and the second outlet valve (108),
   wherein the control device (104) is configured and set up in such a way that:

   - its activation by a manual input is only possible after the indication of a fire alarm triggered by the fire detector (111) by the indicating and inputting element (103),

   - after its activation, the control device (104) automatically switches the first outlet valve (107) into the open state at a time t₁ = t₀ + Δt₁ as long as the fire detector (111) still detects fire at the time t₁, where t₀ is the time of the activation of the control device (104) and Δt₁ is a predetermined time period, and

   - the control device (104) subsequently automatically switches the second outlet valve (108) into the open state at a time t₂ = t₁ + Δt₂, as long as the fire detector (111) still detects fire at the time t₂, where Δt₂ is a predetermined time period.
2. Fire extinguishing system according to Claim 1,
   in which the indicating and inputting element (103) for indicating a fire alarm comprises a lighting means.
3. Fire extinguishing system according to Claim 1 and 2,
   in which the indicating and inputting element (103) comprises:

   - a pushbutton (201) for manual input,

   - a surface of the button (201) that can be illuminated for indicating a fire alarm,

   - a first optical indicating unit (204a-b) for indicating the current state of the first outlet valve (107),

   - a second optical indicating unit (205a-b) for indicating the current state of the second outlet valve (108), and

   - a protective device (202) for preventing unwanted actuation of the button (201).
4. Fire extinguishing system according to Claim 3,
   in which the protective device (202) is formed as a cap.
5. Fire extinguishing system according to Claim 3 or 4, in which the first optical indicating unit (204a-b) and the second optical indicating unit (205a-b) each have a two-coloured LED or two single-coloured LEDs.
6. Fire extinguishing system according to one of Claims 2 to 5,
   in which the lighting means for indicating a fire alarm is switched on and off with a frequency of between 1 Hz and 5 Hz, in particular with 2 Hz or 3 Hz.
7. Fire extinguishing system according to one of Claims 1 to 6,
   in which the time period Δt₁ lies in the range between 5 and 30 s and is in particular 10 s or 15 s or 20 S.
8. Fire extinguishing system according to one of Claims 1 to 7,
   in which the time period Δt₂ lies in the range between 10 and 40 s and is in particular 20 s or 25 s or 30 s or 35 s.
9. Fire extinguishing system according to one of Claims 1 to 8,
   in which the first container (101) and the second container (102) each have a sensor (105, 106) for ascertaining the current filling pressure of the fire extinguishing medium, and the control device (104) is configured and set up in such a way that, dependent on the switching state of the first outlet valve (107) and the second outlet valve (108), a congruence check between the current switching states of the outlet valves (107, 108) and the currently ascertained filling pressures is performed, and unless an expected congruence is ascertained, a warning indication (204c, 205c) is output by the indicating and inputting element (103).
10. Fire extinguishing system according to one of Claims 1 to 9,
    in which the fire detector (111) is arranged in such a way that a fire in an engine or auxiliary engine (112) of the aircraft can be detected by it, and the control device (104) is configured and set up in such a way that, after its activation by the control device (104), the following is automatically instigated:

    - stopping of a fuel supply to the respective engine (112), and/or

    - switching off of one or more electrical generators of the respective engine (112), and/or

    - stopping of a bleed air supply from the respective drive (112) into a passenger cabin or into a cargo area.
11. Fire extinguishing system according to one of Claims 1 to 10,
    in which the status: "control device activated" is visually indicated in the indicating and inputting element (103) by means of an indicator (207).
12. Fire extinguishing system according to one of Claims 1 to 11,
    in which the control device (104) is configured and set up in such a way that a performed activation of the control device (104) can be retracted by a further input into the indicating and inputting element (103) .
13. Aircraft with a fire extinguishing system according to one of Claims 1 to 12, in which the at least one outlet opening (110) is arranged in an engine or auxiliary engine (112), a passenger space or a cargo space of the aircraft and the integrated indicating and inputting element (103) is arranged in the cockpit of the aircraft.
14. Method for operating a fire extinguishing system for an aircraft, wherein the fire extinguishing system comprises:

    - a fire detector (111) for detecting fire,

    - a first container (101), containing pressurized fire extinguishing medium, with a switchable first outlet valve (107) for letting out the fire extinguishing medium from the first container (101),

    - a second container (102), containing pressurized fire extinguishing medium, with a switchable second outlet valve (108) for letting out the fire extinguishing medium from the second container (102), wherein the first outlet valve (107) and the second outlet valve (108) are each switchable into the closed and open states,

    - a system of lines (109) connecting the first outlet valve (107) and the second outlet valve (108) to at least one outlet opening (110), wherein the at least one outlet opening (110) is arranged and designed for delivering the fire extinguishing medium into a predetermined area of the aircraft,

    - an integrated indicating and inputting element (103), which indicates a fire alarm triggered by the fire detector (111) and the current state respectively of the first outlet valve (107) and the second outlet valve (108), and with which a control device (104) can be activated by a manual input, wherein the control device (104) is connected to the fire detector (111), the indicating and inputting element (103), and the first outlet valve (107) and the second outlet valve (108),
    wherein the control device (104) is configured and set up in such a way that its activation by a manual input is only possible after the indication of a fire alarm by the indicating and inputting element (103), with the following steps:

    - after an activation of the control device (104) has taken place at a time t₀, an automatic switching of the first outlet valve (107) into the open state is performed by the control device (104) at the time t₁ = t₀ + Δt₁, as long as the fire detector (111) still detects fire at the time t₁, where Δt₁ is a predetermined time period, and

    - subsequently, an automatic switching of the second outlet valve (108) into the open state is performed by the control device (104) at a time t₂ = t₁ + Δt₂, as long as the fire detector (111) still detects fire at the time t₂, where Δt₂ is a predetermined time period.

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