Method for automatically controlling aircraft in event of fire in engine area, and aircraft

Abstract

The invention relates to a method for automatically controlling an aircraft in the event of a fire in an engine area and an aircraft. A method for controlling an aircraft comprising at least two engines, each engine being arranged in its own engine compartment, each engine being connected to a fuel supply circuit provided with its own fuel supply shut-off means for shutting off the fuel supply, the aircraft includes at least one fire detector in each nacelle, the aircraft including at least one first fire extinguisher and at least one second fire extinguisher. The automatic assistance phase comprises, in the event that a fire is detected in the engine compartment, performing automatically and with the avionics system under predetermined respective conditions: activation of a fuel supply shut-off device of the engine present in the compartment in question, then triggering of the first fire extinguisher, and then triggering of the second fire extinguisher.

Description

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS

[0002] This application claims the benefit of FR 2402011, filed on February 29, 2024, the disclosure of which is incorporated herein by reference in its entirety. Technical Field

[0003] The present invention relates to a method for automatically controlling an aircraft in the event of a fire in an engine area and an aircraft using the method.

[0004] An aircraft may include one or more engines.

[0005] For example, a conventional helicopter may include several engines that together move the main rotor via a powertrain. Each engine is also located in an engine nacelle. Fire detectors are located in each engine nacelle to detect the possible presence of a fire. Such an aircraft may also include two fire extinguishers. Each fire extinguisher can deliver an extinguishing agent, such as halon, to each engine nacelle. The aircraft also includes a fuel shutoff valve for each engine, which is used to cut off the fuel supply to the associated engine.

[0006] In the event of a fire, pilots must interpret the alarms generated by fire detectors, identify the engine affected by the alarm, close the fuel shutoff valve to prevent fuel from being supplied to the fire, activate the fire extinguisher, and verify that the alarm has ceased. This process is complex because pilots must interpret the situation based on the generated alarms. This process places a heavy workload during particularly demanding times. The stress experienced by pilots can lead to accidents due to misinterpretation of the situation. In extreme cases, pilots may even ignore the alarms triggered by the fire detectors or attempt an emergency landing, forgetting to extinguish the fire.

[0007] On some aircraft, an assisted engine shutdown is available. On some aircraft, a single button can be used to trigger both fire extinguishers. Background Art

[0008] The following technical documents are known: documents CN109533348A, US2019 / 126082A1, FR3130751A1 and "chapter 17: fire protection systems" (August 28, 2016 (2016-08-28), XP002791327, retrieved from the Internet URL: http: / / www.sweethaven02.com / aviation / mainthandbook / ama_ch17.pdf [retrieved on May 15, 2019]). Summary of the Invention

[0009] The object of the present invention is therefore to propose a method for reducing the pilot's workload and thereby reducing the risk of human error in the event of a fire being detected in an aircraft's nacelle.

[0010] The present invention therefore relates to a method for controlling an aircraft comprising at least two engines, each engine being arranged in its own nacelle, each engine being connected to a fuel supply circuit provided with its own fuel supply shut-off device for shutting off the fuel supply, the aircraft comprising at least one fire detector in each nacelle, the aircraft comprising at least one first fire extinguisher and at least one second fire extinguisher.

[0011] The control method includes:

[0012] Detecting a fire in a fire compartment in the engine compartment using at least one of the fire detectors; and

[0013] After detecting a fire in the fire compartment, the method comprises an automatic assistance phase controlled by the avionics system, the automatic assistance phase comprising continuously, automatically and under predetermined respective conditions using the avionics system: activating the fuel supply cut-off device of the engine present in the fire compartment so as to stop supplying fuel to the engine, then triggering the first fire extinguisher and then the second fire extinguisher.

[0014] Each nacelle may be bounded by at least one firewall to prevent a detected fire from spreading to another area of ​​the aircraft.

[0015] For example, the engine is connected to a mechanical system. The mechanical system may include rotors, propellers, or indeed rotors for controlling the yaw motion of the aircraft. For example, the aircraft is a rotorcraft, in particular a helicopter.

[0016] Therefore, if a fire is detected, the avionics system is configured to control the fuel supply shutoff device when a first predetermined condition is met. This measure prevents the extinguishing agent emitted by the fire extinguisher from being drawn into the engine within the fire compartment, thereby optimizing the chances of extinguishing the fire. The avionics system is then configured to trigger the first fire extinguisher when a second predetermined condition is met, and then the second fire extinguisher when a third predetermined condition is met.

[0017] The avionics system thus helps significantly reduce pilot workload because, in the event of a fire being detected, it automatically takes various measures to extinguish the detected fire. This allows the pilot to focus on other tasks, such as searching for a landing area. The avionics system also ensures that, in the event of a fire being detected in the fire compartment, the aircraft's fire extinguishing system is activated, rather than a manual procedure subject to human error.

[0018] Furthermore, the method overcomes the pilot's concerns, who would like to be able to control the fire extinguishing system to prevent the fire extinguisher from being triggered unnecessarily. However, since the aircraft is a multi-engine aircraft, even if one engine is unnecessarily shut down due to a false fire detection, the aircraft still always includes at least one operating engine to ensure that the flight is completed safely.

[0019] Furthermore, each fire detector may in particular comprise a thermocouple, a thermistor or a gas fire detector.

[0020] For example, a thermocouple fire detector may include two different metal blades that deform and move away from each other in response to an increase in temperature, breaking the circuit when a detection threshold is reached. The two blades may include one rapidly deforming blade and one slowly deforming blade.

[0021] Thermistor fire detectors may include a temperature sensor based on changes in resistance according to temperature.

[0022] A gas fire detector may comprise a tube, for example made of stainless steel, filled with a gas-absorbing material. The temperature rise caused by a fire, in particular, causes the gas in the sealed tube to be expelled, resulting in a rapid and detectable increase in pressure in the tube.

[0023] Such a fire detector is highly reliable. Arranging such a fire detector in a multi-engine aircraft having an avionics system to which the method of the invention is applied makes it possible to obtain a robust and reliable fire protection method.

[0024] The method may also include one or more of the following features.

[0025] According to a first alternative, the aircraft can include at least one flight control member that affects the movement of the aircraft in the air, and after detecting a fire in the fire compartment, the automatic assistance phase consists in adjusting the position of the at least one flight control member using the avionics system so as to place the aircraft in a predetermined flight configuration, the activation of the fuel supply shut-off device being triggered simultaneously with or after said adjustment.

[0026] The avionics system is configured to then automatically place the aircraft into a specific flight configuration, for example compatible with the use of a single engine. Thus, the avionics system plays an active role in ensuring flight safety.

[0027] In this case, the first conditions warranting activation of the fuel supply shutoff device may include detection of a fire and satisfaction of predetermined flight conditions.

[0028] The predetermined flight configuration may be defined by at least one of the following parameters: the forward speed of the aircraft, an operating parameter of an engine other than the engine present in the fire compartment, and the altitude or height of the aircraft. The operating parameter may be the drive power or engine torque produced by a component of the engine not related to the detected fire or by a component of the engine set in motion.

[0029] Adjusting the position of the at least one flight control member using the avionics system may include causing the value of at least one of the following parameters to follow a predetermined corresponding set point value: the forward speed of the aircraft, the value of an operating parameter of an engine different from the engine present in the fire compartment, the altitude or height above the ground of the aircraft.

[0030] According to a second alternative, activation of the fuel supply shut-off device is triggered after detection of a fire.

[0031] In this case, the fuel supply to the engine in the fire compartment is cut off without any condition other than the detection of a fire by a fire detector, or after a predetermined waiting period in which the pilot has the option of canceling the automatic assistance phase by operating the human-machine shutdown interface. In this case, the first condition for activating the fuel supply cutoff may include only the detection of a fire, and may also include the expiration of a predetermined waiting period. This predetermined waiting period may, for example, allow the pilot to cancel the automatic assistance phase.

[0032] According to a possibility compatible with the aforementioned possibility, the automatic assistance phase may comprise measuring, by means of the avionics system, the speed of a movable member of the engine arranged in the fire compartment, and triggering, after activating the fuel supply shut-off device, the first fire extinguisher controlled by the avionics system when the speed of the movable member becomes less than or equal to a predetermined speed threshold.

[0033] For example, the engine is a turboshaft engine. Thus, the avionics system may include a sensing device for measuring the rotational speed of a rotating assembly of a gas generator of the turboshaft engine.

[0034] This feature helps maximize the chances of extinguishing a fire by reducing the risk of extinguishing agent from the extinguisher being drawn into the engine.

[0035] In this case, the second condition authorizing triggering of the first fire extinguisher involves two factors: detecting when the fuel supply shutoff device is activated, and detecting when the speed of the movable member of the engine present in the fire compartment becomes less than or equal to a predetermined speed threshold.

[0036] Alternatively, the second condition authorizing triggering of the first fire extinguisher may include only detecting activation of the fuel supply shutoff, and possibly detecting expiration of a predetermined time period from that activation.

[0037] According to a possibility compatible with the aforementioned possibility, the activation of the second fire extinguisher may be controlled by the avionics system if the fire detector still detects a fire at the end of a predetermined monitoring period after the activation of the first fire extinguisher.

[0038] For example, such a period is in the range of 5 seconds.The avionics system is configured to take into account that if a fire is still detected in the fire compartment at the end of this monitoring period, a second fire extinguisher should be triggered to extinguish the fire.

[0039] Then, a third condition for authorizing the triggering of the second fire extinguisher may be the detection of a fire in the fire compartment at the end of the monitoring period after the triggering of the first fire extinguisher.

[0040] According to a possibility compatible with the above-mentioned possibility, the automatic assistance phase may comprise the following steps:

[0041] When no fire detector detects a fire at the end of a first predetermined period of time after triggering the first fire extinguisher, the method comprises issuing a first alarm, the first alarm at least signaling the end of the automatic assistance phase or a command to land as soon as possible;

[0042] When a fire detector detects a fire in the fire compartment at the end of the first predetermined period of time after the triggering of the first fire extinguisher, the method includes triggering the second fire extinguisher under the command of the avionics system;

[0043] When no fire detector detects a fire at the end of a second predetermined time period after triggering the second fire extinguisher, the method includes sounding the first alarm; and

[0044] When the fire detector detects a fire in the fire compartment at the end of the second predetermined time period after triggering the second fire extinguisher, the method comprises sounding a second alarm, which signals an immediate order to land.

[0045] Depending on the severity of the situation, the avionics system can issue a command to land immediately or as soon as possible, a command aimed at the pilot.

[0046] Therefore, if both fire extinguishers fail to extinguish the fire, an order for immediate landing is issued.

[0047] According to a possibility compatible with the previous one, after the detection of a fire, the automatic assistance phase consists in generating, controlled by the avionics system and using an alarm, a fire alarm indicating the nacelle involved.

[0048] The pilot is thus notified that a fire has been detected and can act accordingly.

[0049] According to a possibility compatible with the aforementioned possibility, after the detection of a fire, the automatic assistance phase comprises the generation of an information alarm, controlled by the avionics system and using an alarm, after activation of the automatic assistance phase.

[0050] The pilot is thus informed that the automated assistance phase is in progress. This step allows the pilot to focus on other tasks.

[0051] According to a possibility compatible with the aforementioned possibility, after activation of the fuel supply shut-off device, the automatic assistance phase comprises, controlled by the avionics system and using an alarm, the generation of a status alarm after said activation of the fuel supply shut-off device.

[0052] The pilot is thus informed of the progress of the automatic assistance phase, in particular of the shut-off of the fuel supply to the engine. This shut-off can be detected by the avionics system by means of a signal emitted by a position sensing device measuring the position of the flap of the fuel shut-off valve, or, for example, by a flow meter measuring the flow rate of fuel delivered to the engine.

[0053] The term "signal" refers hereinafter to, for example, an analog, digital, electrical or optical signal.

[0054] According to a possibility compatible with the aforementioned possibility, after triggering the first fire extinguisher, the automatic assistance phase consists in generating, controlled by the avionics system and using an alarm, a first extinguishing alarm after such triggering of the first fire extinguisher.

[0055] When a fire extinguisher sprays extinguishing agent into the engine compartment, the pressure in the container containing the agent drops. For example, each fire extinguisher may include a pressure sensor that sends a signal when the pressure in the extinguisher's container reaches a low threshold. The avionics system then infers that the fire extinguisher has functioned correctly and sends a signal to an alarm.

[0056] The pilot is thus informed that the automatic assistance phase is ongoing and has caused the first fire extinguisher to be triggered.

[0057] According to a possibility compatible with the preceding one, after triggering the second fire extinguisher, the automatic assistance phase may comprise generating, controlled by the avionics system and using an alarm, a second extinguishing alarm carrying this triggering of the second fire extinguisher.

[0058] The pilot is thus informed that the automatic assistance phase is ongoing and has caused the second fire extinguisher to be triggered.

[0059] According to a possibility compatible with the preceding one, the method comprises stopping the automatic assistance phase after operating the human-machine closing interface.

[0060] The pilot can activate the human-machine shutdown interface at any time if he or she deems it necessary in light of the various information received.

[0061] According to a possibility compatible with the aforementioned, the avionics system activates the auto-assistance phase only during flight. For example, the avionics system applies the auto-assistance phase when the aircraft's altitude or height above the ground is greater than a threshold. For this purpose, the aircraft may include conventional altitude or height sensing devices.

[0062] The invention also relates to a computer program comprising instructions causing an avionics system to implement the above method when said program is executed by said avionics system.

[0063] The invention also relates to an aircraft comprising at least two engines, each engine being arranged in its own engine nacelle, each engine being connected to a fuel supply circuit provided with its own fuel supply shut-off device for shutting off the fuel supply, the aircraft comprising at least one fire detector in each engine nacelle, the aircraft comprising at least one first fire extinguisher and at least one second fire extinguisher.

[0064] The aircraft includes an avionics system in communication with each fire detector, each fuel supply shutoff device, and the at least one first fire extinguisher and the at least one second fire extinguisher to implement the above method.

[0065] The aircraft may include at least one of the following features: each fuel supply shutoff device is a fuel shutoff valve, each of the at least one first fire extinguisher and the at least one second fire extinguisher includes a fire extinguishing agent and a pipe for delivering the fire extinguishing agent to each of the engine nacelles.

[0066] Each fire detector may possibly comprise a thermocouple, a thermistor, or a gas fire detector. BRIEF DESCRIPTION OF THE DRAWINGS

[0067] The invention and its advantages emerge in more detail against the backdrop of the following description of embodiments given by way of example and with reference to the accompanying drawings, in which:

[0068] Figure 1 is a schematic diagram of an aircraft according to the present invention; and

[0069] Figure 2 is a logic diagram illustrating the method of the present invention. DETAILED DESCRIPTION

[0070] Elements that appear in more than one figure are given the same reference numeral in each of them.

[0071] Figure 1 An aircraft 1 is shown that is capable of implementing the method of the invention described below.

[0072] The aircraft 1 includes at least two engines 16 and 17. Reference numeral 15 is used to denote any engine, if desired. The engines 15 may be connected to a mechanical system 2. For example, the mechanical system 2 includes a drivetrain 5 that moves a rotary system 7. According to the example shown, the drivetrain 5 includes a gearbox 6 connected to each engine 15 and the rotary system 7 by conventional components, which are not shown here to avoid cluttering the drawing. The rotary system 7 may include at least one blade 8, which may be carried by a hub 9. This rotary system 7 may form a propeller, a rotary wing, or a yaw motion control rotor, to give various examples.

[0073] Regardless of this aspect, each engine 15 can be an engine supplied with fuel. Each engine 16, 17 is thus connected to a fuel supply circuit 31, 36. Each fuel supply circuit 31, 36 includes at least one fuel tank 33, 330, which may be shared with another fuel circuit, at least one conduit 32, 37 connecting the fuel tank to the associated engine, and at least one fuel supply shutoff device 34, 38 specific to the associated engine 15. Thus, the first engine 16 is supplied with fuel by a first fuel supply circuit 31, which includes a first conduit 32 equipped with at least one first fuel supply shutoff device 34 and extending from the fuel tank 33 to the first engine 16. Similarly, the second engine 17 is supplied with fuel by a second fuel supply circuit 36, which includes a second conduit 37 equipped with at least one second fuel supply shutoff device 38 and extending from the fuel tank 330 to the second engine 17.

[0074] Each fuel supply shutoff device 34, 38 may comprise a fuel shutoff valve and / or a pump. Thus, activating the fuel supply shutoff device comprises closing the fuel shutoff valve or stopping the pump, depending on the variant.

[0075] Furthermore, each engine 16, 17 comprises a movable member 151, 152. In the context of a turboshaft engine, this movable member 151, 152 may be a rotating assembly of a gas generator and may comprise at least one compression stage constrained to rotate with at least one turbine.

[0076] In addition, each engine 16, 17 is arranged in its own engine compartment 21, 22. If necessary, reference numeral 20 represents any engine compartment. Each engine compartment 21, 22 can be delimited by at least one firewall to contain a possible fire in the engine compartment 21, 22.

[0077] In addition, at least one fire detector 26-29 is housed in each nacelle 21, 22. Reference numeral 25 may represent any fire detector, if desired. For example, a given nacelle 21, 22 may include fire detectors 26-27, 28-29 set at different trigger temperatures depending on their location. Each fire detector 26-29 may include a thermocouple, a thermistor, or a gas fire detector.

[0078] Furthermore, aircraft 1 includes at least one first fire extinguisher 40 and at least one second fire extinguisher 45. Each fire extinguisher 40, 45 includes a container containing a fire extinguishing agent, such as halon. Furthermore, each fire extinguisher 40, 45 may include a respective conduit for each nacelle 21, 22, namely, in the illustrated example, a first conduit 41, 46 leading to the first nacelle 21 and a second conduit 43, 48 leading to the second nacelle 22. Each fire extinguisher 40, 45 includes a trigger 42, 44, 47, 49 (e.g., a pyrotechnic cartridge) for each conduit 41, 43, 46, 48 of the fire extinguisher 40, 45, for delivering the fire extinguishing agent to one or the other of the conduits 41, 43, 46, 48.

[0079] Alternatively, for example, each nacelle may have its own fire extinguisher.

[0080] Furthermore, each fire extinguisher 40 , 45 may include a pressure sensor 400 , 500 that sends a specific signal when the pressure within its container reaches a low threshold indicating that fire extinguishing agent should be injected into the engine compartment.

[0081] Furthermore, the aircraft 1 comprises an avionics system 60 in communication with each fire detector 26 to 29 , each fuel supply shut-off device 34 , 38 and each fire extinguisher 40 , 45 , in order to implement the method of the invention.

[0082] For example, the avionics system 60 may include a respective speed sensing device 18 , 19 for each engine 16 , 17 that measures the speed of the movable member 151 , 152 of that engine 16 , 17 , i.e., a first speed sensing device 18 for the first engine 16 and a second speed sensing device 19 for the second engine 17 .

[0083] The avionics system 60 may include a controller in communication with the speed sensing devices 18, 19. The controller may execute a computer program comprising instructions that, when executed by the avionics system 60, cause the avionics system 60 to implement the method of the present invention.

[0084] According to the example shown, the controller may include one engine computer for each engine 15 , namely a first engine computer 160 controlling the first engine 16 and a second engine computer 170 controlling the second engine 17 .

[0085] The controller may include an autoflight control computer 65 that may be in communication with the engine computers 160 , 170 .

[0086] As examples, each described computer may include at least one processor and at least one memory, at least one integrated circuit, at least one programmable system, or at least one logic circuit, without limiting the scope of the term "computer." The term "processor" may equally refer to a central processing unit or CPU, a graphics processing unit or GPU, a digital signal processor or DSP, a microcontroller, etc.

[0087] According to another aspect, the avionics system 60 may be configured to automatically control the aircraft 1 under certain conditions by controlling the position of one or more flight control members. The controller may, for example, run a program for this purpose.

[0088] According to the example shown, such a flight control member may be in the form of a blade 8, the pitch angle of which can be controlled using one or more servo-controllers 88. Another flight control member may be in the form of a fuel metering valve that supplies fuel to the engine 15, a blade of another rotor, a vertical stabilizer flap, or a tail flap, etc. Regardless of the nature of the flight control member, the position of the flight control member may be controlled using actuators of the avionics system 60.

[0089] For example, each blade 8 may be hinged to a pitch stick 90, which is hinged to a set of swashplates 89, the position of which can be controlled by a servo controller 88. Each servo controller 88 may be controlled by a control channel 86 including at least one actuator 87. The controller and possibly the automatic flight control computer 65 may control the actuators 87.

[0090] Furthermore, the avionics system 60 may include a human-machine control interface 95 for requesting the application of the method of the present invention, and / or a human-machine shutdown interface 96. These interfaces transmit signals to the controller, or in particular to the automatic flight control computer 65. Each human-machine interface may include at least one button, a touch screen, a mouse, a keyboard, a voice system, etc.

[0091] In addition, aircraft 1 may include an alarm 70 capable of generating various alarms upon command from a controller and, for example, an automatic flight control computer 65. Each alarm may be in the form of a visual alarm (e.g., by displaying one or more characters on a screen) and / or an audible and / or tactile alarm. If a visual alarm is present, alarm 70 may include one or more screens. The controller or automatic flight control computer 65 may send one or more signals to the alarm to request the issuance of the desired alarm.

[0092] Additionally, the aircraft 1 may include an altitude or height sensing device 97 (eg, a radio altimeter) that measures height above the ground or altitude, or a conventional forward speed sensing device 970 that measures aircraft speed and, for example, airspeed.

[0093] The aircraft 1 may include position sensing means 340, 380 in each fuel supply shut-off device 34, 38 for assessing whether a component of the fuel supply shut-off device is in the closed position, or flow sensing means 341, 381 in each fuel supply circuit 31, 36 for determining whether the fuel supply to the engine 15 is open or closed.

[0094] These sensing devices 97 , 970 , 341 , 381 send signals to a controller, or in particular to the automatic flight control computer 65 .

[0095] Figure 2 A method of controlling such an aircraft 1 in the event of a fire in the nacelle is shown.

[0096] The method may include the step of activating the method by operating the human-machine control interface 95 .

[0097] In case of a fire, the method comprises, during a step STP1 , detecting a fire in an engine compartment referred to as the “fire compartment” by means of at least one of the fire detectors 26 - 29 . For the purpose of explaining the invention, the fire compartment will hereinafter be considered the first engine compartment 21 .

[0098] The fire detector, such as detector 27, then sends a signal to the controller of the avionics system 60 and, for example, to the automatic flight control computer 65. The controller decodes the signal and deduces from it that a fire has occurred in the fire compartment 21.

[0099] After this detection step STP1 of a fire in the fire compartment 21, the PHASASSIST phase is controlled by the avionics system 60. The PHASASSIST phase can only be activated by the avionics system 60 when the aircraft is at an altitude above the ground or at an altitude measured by the sensing means 97 above a threshold.

[0100] During this PHASASSIST phase, the avionics system 60 continuously, automatically and under predetermined conditions controls the activation STP5 of the fuel supply shut-off device 34 of the engine 16 present in the fire compartment 21 , then controls the triggering STP7 of the first fire extinguisher 40 , then controls the triggering STP9 of the second fire extinguisher 45 , and possibly controls the emission of various alarms.

[0101] The method may include stopping the PHASASSIST phase at any time after the human-machine shutdown interface 96 is operated. The human-machine shutdown interface 96 then sends a signal to the controller to stop the PHASASSIST phase. The fuel supply shutoff devices 34, 38 and the fire extinguishers 40, 45 may then be manually controlled using conventional dedicated controls.

[0102] According to one possibility, after detecting a fire (STP1), the method includes generating (STP2) a fire alarm signaling the affected nacelle. After receiving a fire detection signal from the fire detector, the avionics system 60 controls the alarm 70 to generate a fire alarm signaling the detection of a fire and the affected nacelle. For example, the controller or the automatic flight control computer 65 sends a signal to the alarm 70 requesting the generation of a fire alarm. The fire alarm specifies the nacelle in which the fire has been detected. For example, the message "ENG1 FIRE" is displayed to signal the fire in the first nacelle.

[0103] Alternatively, later or simultaneously, the PHASASSIST phase may include generating an informational alert indicating the initiation of the PHASASSIST phase. For example, upon receiving a fire detection signal from a fire detector, the controller or automatic flight control computer 65 may send a signal to the alarm 70 requesting the generation of an informational alert. For example, the message "ENG1 FIRE AUTO PROT" may be displayed.

[0104] Alternatively, after or simultaneously with the preceding alarm step, after the detection STP1 of a fire, the automatic assistance phase PHASASSIST may comprise adjusting STP4 the position of at least one flight control member so as to position the aircraft 1 in a predetermined flight configuration, the activation STP5 of the fuel supply shut-off means 34 , 38 being triggered simultaneously with or after said adjustment STP4 .

[0105] For example, after receiving a fire detection signal from a fire detector, the controller or automatic flight control computer 65 sends a signal to at least one actuator that acts on the position of a flight control member so that the value of at least one of the following parameters follows a predetermined set point value: the forward speed of the aircraft 1 measured by the conventional forward speed sensing device 970, the value of an operating parameter of an engine different from the engine present in the fire compartment measured by the speed sensing device 19, the altitude or height above the ground of the aircraft 1 measured by the conventional forward speed sensing device 970.

[0106] Regardless of these possibilities, activation STP5 of the fuel supply shutoff device 34 can be triggered after detection STP1 of a fire. The controller or automatic flight control computer 65 sends a signal to the fuel supply shutoff device 34, which, according to the example shown, shuts off the fuel supply to the first engine 16 (e.g., after receiving a fire detection signal from a fire detector).

[0107] Optionally, after activating the STP5 fuel supply shutoff device 34, the PHASASSIST phase includes generating an STP6 status alarm. The status alarm carries a status signal indicating whether the fuel supply has been shut off or not. For example, a sensing device for sensing the position of the fuel shutoff valve or a flow sensing device sends a signal to the controller, informing it that the fuel supply to the engine in the fire compartment has been shut off. The controller or the automatic flight control computer 65 then sends a signal to the alarm 70 requesting the generation of a status alarm. For example, the message "ENG1 OFF" is displayed, signaling that the fuel shutoff valve has been closed.

[0108] For example, if the pilot notices that no status warning has been issued, he can cancel the auto-assistance phase during the stop phase STPOFF and / or can shut off the fuel supply by another means during step STPMAN and thereby resume the auto-assistance phase.

[0109] Regardless of these selections, after shutting off the fuel supply to the engine 16 present in the fire compartment 21, the avionics system 60 and, for example, the controller or automatic flight control computer 65 send a signal to the first fire extinguisher 40 to trigger the STP7 first fire extinguisher 40. The trigger 42 is then actuated to discharge the extinguishing agent of the first fire extinguisher 40 into the fire compartment.

[0110] The PHASASSIST phase may consist in measuring the speed of the movable member 151 of the engine 16 of the STPCOND fire compartment 21 using the avionics system 60 and in particular using the speed sensing device 18 according to the example given. The avionics system 60 then controls the triggering STP7 of the first fire extinguisher 40 only when the speed of the movable member 151 becomes less than or equal to a predetermined speed threshold and a fire is detected.

[0111] According to one possibility, the PHASASSIST phase includes generating, by means of the alarm 70, a first extinguishing alarm of the triggering of the first fire extinguisher 40 carried by the STP 8. For example, the pressure sensing device 400 of the first fire extinguisher 40 sends a signal to the controller, for example to the automatic flight control computer 65, which then sends a signal to the alarm 70 requesting the issuance of the first extinguishing alarm. For example, the message "ENG1 FIRE SHOT 1" is displayed.

[0112] Furthermore, the PHASASSIST phase may include, after the triggering of the first fire extinguisher 40, generating a second alarm using the alarm 70 and under the command of the avionics system 60 if at least one of the fire detectors 26-29 detects a fire, or generating a first alarm if none of the fire detectors 26-29 detects a fire. The second alarm signals an immediate landing command, and the first alarm signals at least the end of the PHASASSIST phase or a command to land as soon as possible. For example, the first alarm may include the message "LAND AS SOON AS POSSIBLE," and the second alarm may include the message "LAND IMMEDIATELY."

[0113] For example, the automated assistance phase PHASASSIST includes the following steps.

[0114] Therefore, if, at the end of the first predetermined time period after the triggering of the first fire extinguisher 40 (STP7), no fire detectors 26-29 (particularly the fire detectors of the fire compartment 21) send a signal to the controller indicating a fire, the fire is considered extinguished. The method includes issuing a first alarm (STP10). For example, the controller or the automatic flight control computer 65 sends a signal to the alarm 70 to request the issuance of the first alarm. The pilot is then informed that the PHASASSIST phase is complete and that the fire is extinguished, and / or an urgent landing is recommended.

[0115] Conversely, if fire detectors 26-27 detect a fire in fire compartment 21 at the end of a predetermined monitoring period after the activation of first fire extinguisher 40, the method includes activating second fire extinguisher 45 at step STP 9. The monitoring period may be equal to or different from the first predetermined period. For example, the controller or autoflight control computer 65 sends a signal to the second fire extinguisher 45 to this effect. The trigger 47 is then actuated to discharge the extinguishing agent from the second fire extinguisher 45 into the fire compartment.

[0116] The PHASASSIST phase may include generating a second fire extinguisher 45 carried by STP 11, which triggers a second fire extinguisher alarm at STP 9, using an alarm 70. For example, the controller or the automatic flight control computer 65 sends a signal to the alarm 70 to this effect, such as displaying the message "ENG1 FIRE SHOT 2".

[0117] Thus, if at the end of the second predetermined period after the triggering STP9 of the second fire extinguisher 45 no fire detectors 26-29 (in particular the fire detectors of the fire compartment 21) send a signal to the controller signaling a fire, the fire is extinguished. The method comprises raising STP12 a first alarm.

[0118] If the fire detectors 26 - 27 still detect a fire at the end of the first predetermined activation period after the triggering of the first fire extinguisher 40 , the triggering STP9 of the second fire extinguisher 45 is controlled by the avionics system 60 .

[0119] Conversely, if the fire detectors 26-29 detect a fire at the end of the second predetermined period after the triggering of the second fire extinguisher 45 (STP9), the method includes issuing a second alarm (STP13). For example, the controller or automatic flight control computer 65 sends a signal to the alarm 70. The pilot is then informed that the PHASASSIST automatic assistance stage has not extinguished the fire and is advised to land immediately.

[0120] Of course, the present invention has many variations in its implementation. Although several embodiments have been described above, it should be readily understood that it is not possible to exhaustively identify all possible embodiments. Of course, equivalent devices may be substituted for any of the devices described without departing from the scope of the present invention and the claims.

Claims

1. A method for controlling an aircraft (1), the aircraft (1) comprising at least two engines (16, 17), each engine (16, 17) being arranged in its own engine nacelle (21, 22), each engine (16, 17) being connected to a fuel supply circuit (31, 36), the fuel supply circuit (31, 36) being provided with its own fuel supply shut-off device (34, 38) for shutting off the fuel supply, the aircraft (1) comprising at least one fire detector (26-29) in each engine nacelle (21, 22), the aircraft (1) comprising at least one first fire extinguisher (40) and at least one second fire extinguisher (45), The control method includes: Detecting (STP1) a fire in a fire compartment in the engine compartment (21, 22) using at least one of the fire detectors (26-29); as well as After detecting (STP1) a fire in the fire compartment, the method comprises an automatic assistance phase (PHASASSIST) controlled by the avionics system (60), the automatic assistance phase (PHASASSIST) comprising continuously, automatically and under predetermined respective conditions using the avionics system (60): activating (STP5) the fuel supply cut-off devices (34, 38) of the engines (16, 17) present in the fire compartment so as to no longer supply fuel to the engines (16, 17), then triggering (STP7) the first fire extinguisher (40), then triggering (STP9) the second fire extinguisher (45).

2. The method according to claim 1, The aircraft (1) comprises at least one flight control member (8) affecting the movement of the aircraft (1) in the air, and after detecting (STP1) a fire in the fire compartment, the automatic assistance phase (PHASASSIST) comprises adjusting (STP4) the position of the at least one flight control member (8) using the avionics system (60) so as to place the aircraft (1) in a predetermined flight configuration, activating (STP5) the fuel supply shut-off device (34, 38) being triggered simultaneously with or after the adjustment (STP4).

3. The method according to claim 2, The predetermined flight configuration is defined by at least one of the following parameters: the forward speed of the aircraft (1), operating parameters of engines (16, 17) different from the engines (16, 17) present in the fire compartment, the altitude or height above the ground of the aircraft (1).

4. The method according to claim 2, wherein regulating (STP4) the position of the at least one flight control member (8) using the avionics system (60) comprises causing the value of at least one of the following parameters to follow a predetermined corresponding set point value: the forward speed of the aircraft, the value of an operating parameter of an engine (16, 17) different from the engine (16, 17) present in the fire compartment, the altitude or height above the ground of the aircraft.

5. The method according to claim 1, The activation (STP5) of the fuel supply shut-off device (34, 38) is triggered after the fire is detected (STP1).

6. The method according to claim 1, The automatic assistance phase (PHASASSIST) comprises measuring (STPCOND) the speed of the movable member (151, 152) of the engine (16, 17) arranged in the fire compartment by means of the avionics system (60), and triggering (STP7) the first fire extinguisher (40) controlled by the avionics system (60) after activating (STP5) the fuel supply shut-off device (34, 38) when the speed of the movable member (151, 152) becomes less than or equal to a predetermined speed threshold.

7. The method according to claim 1, If the fire detectors (26-29) still detect a fire at the end of a predetermined monitoring period after the first fire extinguisher (40) is triggered (STP7), the second fire extinguisher (45) is triggered (STP9) under the control of the avionics system (60).

8. The method according to claim 1, The automated assistance phase (PHASASSIST) includes the following steps: When no fire detectors (26-29) detect a fire at the end of a first predetermined period of time after triggering (STP7) the first fire extinguisher (40), the method comprises issuing (STP10) a first alarm, the first alarm at least signaling the end of the automatic assistance phase or a command to land as soon as possible; When the fire detectors (26-29) detect a fire in the fire compartment at the end of the first predetermined period after the triggering (STP7) of the first fire extinguisher (40), the method comprises triggering (STP9) the second fire extinguisher (45) under the command of the avionics system (60); When no fire detectors (26-29) detect a fire at the end of a second predetermined period of time after triggering (STP9) the second fire extinguisher (45), the method comprises issuing (STP12) the first alarm; and When the fire detectors (26-29) detect a fire in the fire compartment at the end of the second predetermined period after triggering (STP9) the second fire extinguisher (45), the method comprises issuing (STP13) a second alarm, the second alarm signaling an immediate landing order.

9. The method according to claim 1, After detecting (STP1) a fire, the automatic assistance phase (PHASASSIST) comprises generating (STP2) a fire alarm indicating the involved nacelle, controlled by the avionics system (60) and using an alarm (70).

10. The method according to claim 1, After a fire is detected (STP1), the automatic assistance phase (PHASASSIST) includes generating (STP3) an information alarm after the activation of the automatic assistance phase (PHASASSIST) by controlling the avionics system (60) and using an alarm (70).

11. The method according to claim 1, wherein after activating (STP5) the fuel supply shutoff device (34, 38), the automatic assistance phase (PHASASSIST) includes being controlled by the avionics system (60) and generating (STP6) a status alarm using an alarm (70) after the activation (STP5) of the fuel supply shutoff device (34, 38).

12. The method according to claim 1, After the triggering (STP7) of the first fire extinguisher (40), the automatic assistance phase (PHASASSIST) includes generating (STP8) a first extinguishing alarm after the triggering (STP7) of the first fire extinguisher (40) by means of an alarm (70) controlled by the avionics system (60).

13. The method according to claim 1, After the second fire extinguisher (45) is triggered (STP9), the automatic assistance phase (PHASASSIST) includes generating (STP11) a second extinguishing alarm controlled by the avionics system (60) and using an alarm (70).

14. The method according to claim 1, The method includes stopping the automatic assistance phase (PHASASSIST) after operating the human-machine shutdown interface (96).

15. An aircraft (1) comprising at least two engines (16, 17), each engine (16, 17) being arranged in its own engine nacelle (21, 22), each engine (16, 17) being connected to a fuel supply circuit (31, 36), said fuel supply circuit (31, 36) being provided with its own fuel supply shut-off device (34, 38) for shutting off the fuel supply, said aircraft (1) comprising at least one fire detector (26-29) in each engine nacelle (21, 22), said aircraft (1) comprising at least one first fire extinguisher (40) and at least one second fire extinguisher (45), wherein the aircraft (1) comprises an avionics system (60) communicating with each fire detector (26-29), with each fuel supply shutoff device (34, 38), and with the at least one first fire extinguisher (40) and the at least one second fire extinguisher (45) in order to implement the method according to claim 1.

16. The aircraft according to claim 15, The aircraft (1) includes at least one of the following features: each fuel supply shut-off device (34, 38) is a fuel shut-off valve, each of the at least one first fire extinguisher (40) and the at least one second fire extinguisher (45) includes an extinguishing agent and a pipe (41, 43, 46, 48) for conveying the extinguishing agent to each engine nacelle (21, 22) respectively.

17. The aircraft according to claim 16, Each fire detector (26-29) comprises a thermocouple, a thermistor or a gas fire detector.

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