• 专利附录
  • 专利说明
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    • 专利摘要:
    A method for selectively sensing smoke detection of an aircraft (12a) comprising: installing one or more selectable smoke detector assemblies (70); electrically or wirelessly coupling the selectable sensitivity smoke detector assembly (70) installed in an aircraft to one or more sensitivity select commands installed in an aircraft (12a); and selecting an alarm setpoint sensitivity level from two or more alarm set point sensitivity levels for each of the selectable sensitivity smoke detector assembly (s) ( 70), based on sensitivity level determining factors of one or more of a type of mission, cargo, compartment area specific area on the aircraft (12a), as well as an assignment status. on the aircraft (12a).
    公开号:FR3027147A1
    申请号:FR1559652
    申请日:2015-10-09
    公开日:2016-04-15
    发明作者:Oliver C Meier
    申请人:Boeing Co；
    IPC主号:
    专利说明:

    [0001] The present invention generally relates to systems and methods for smoke detection, and more particularly to systems and methods with selective smoke detection sensitivity for air vehicles, such as aircraft. commercial passengers and cargo aircraft.
    [0002] Known methods and systems exist for the detection of smoke on air vehicles, such as commercial passenger aircraft and cargo aircraft. With such known smoke detection methods and systems, when smoke in an area of an aircraft becomes sufficiently dense, it will typically trigger the smoke detection system and cause an alarm in the cockpit signaling the presence of smoke. a fire. The sensitivity of smoke detection systems is a key factor in the time required to detect smoke / fire. The faster the detection of smoke or fire, the faster the ignition of fire extinguishing systems by the crew and the deflection of the air vehicle to an airport.
    [0003] However, known smoke detection methods and systems can typically have only one alarm set point. This alarm set point can be based on laboratory and flight tests and can be set to be as high (the least sensitive) as possible to create a false alarm resistant system. This false-alarm system assumes that certain types of freight (eg fresh flowers, fish) can accidentally trigger a false alarm, if moisture vapor, dust, or other sources of false alarms, are presented. In some cases, operators may prefer to have a more sensitive system and accept in compensation the detector with "lower sensitivity", if freight not causing false alarms nuisance is not transported. For example, when transporting batteries, such as lithium batteries, as freight, the likelihood of a false alarm may be reduced, whereas early detection may be strongly desired. In many cases, inert freight, such as packages, machinery, batteries, and the like, may be transported but may pose a reduced risk of false alarm. In these cases, the smoke detection methods and systems may be unnecessarily "desensitized" for false alarm immunity. In addition, with known smoke detection methods and systems, it may be difficult, without purely and simply installing new smoke detectors, for the crew to change or vary the sensitivity of the smoke detector to increase the smoke detector sensitivity in the aircraft. Therefore, an improved method and system for providing selective smoke detection sensitivity, which provide advantages over known methods and systems, is necessary in the art.
    [0004] Illustrative implementations of the present invention provide an improved method and system for enabling selective smoke detection sensitivity. As described in the detailed description below, improved embodiments of the method and system for enabling selective smoke detection sensitivity can provide significant advantages over existing systems and methods. In one embodiment, a method for providing a selective smoke detection sensitivity on board an aircraft is provided. The method includes a step of installing one or more smoke detector assemblies with selectable sensitivity on board the aircraft.
    [0005] The method further comprises a step of electrically or wirelessly coupling the selectable sensitivity smoke detector assembly (s) installed on the aircraft to one or more sensitivity select commands installed on the aircraft. The method further comprises a step of selecting an alarm set point sensitivity level from two or more alarm set point sensitivity levels for each of the one or more sensing smoke detector assemblies. selectable, based on sensitivity level determination factors including one or more of a mission type of the aircraft, a type of cargo on the aircraft, a specific sector type of compartment area on the aircraft, and a state of assignment on the aircraft.
    [0006] In another embodiment, a method for providing a selective smoke detection sensitivity on board an aircraft is provided. The method includes a step of installing one or more smoke detector assemblies with selectable sensitivity on board the aircraft. The method further comprises a step of using the selectable sensitivity smoke detector assembly (s) on board the aircraft to autonomously vary in real time its alarm setpoint sensitivity level or level, selected from two or more alarm setpoint sensitivity levels based on sensitivity level determining factors comprising one or more of an aircraft system state and an aircraft configuration state. In another embodiment, a system for providing a selective smoke detection sensitivity on board an aircraft is provided. The system includes one or more selectable smoke detector assemblies 10 installed on board the aircraft. Each sensitively selectable smoke detector assembly includes a selectable sensitivity smoke detector device; one or more sensors coupled electrically or wirelessly to the selectable sensitivity smoke detector device; and a control apparatus coupled to the selectable sensitivity smoke detector device. Each selectable sensitivity smoke detector further includes system logic coupled to the selectable sensitivity smoke detector device or control device. The system logic is configured to autonomously vary two or more alarm setpoint sensitivity levels in real time, based on sensitivity level determining factors including one or more of a system state of the system. aircraft and an aircraft configuration state. Each selectable sensitivity smoke detector further comprises one or more system inputs measured by the sensor (s) and inputted to each selectable sensitivity smoke detector device, or input to the control apparatus, for logic processing. system. Each selectable sensitivity smoke detector further includes a generated system output when the alarm set point sensitivity level is triggered. The features, functions, and advantages that have been described can be achieved independently in various embodiments of the description or can be combined in yet other embodiments of which further details can be seen with reference to the description and to the following drawings. The present invention will be better understood by reference to the following detailed description taken in conjunction with the accompanying illustrative drawings illustrating preferred embodiments, but which are not necessarily drawn to scale, in which: FIG. perspective view of an air vehicle which can incorporate one or more embodiments of a system and method according to the invention, FIG. 2 is a flowchart of an aircraft manufacturing and maintenance process, FIG. 3 is a schematic illustration of an aircraft, FIG. 4A is a schematic diagram showing an embodiment of a system for selective smoke detection sensitivity, FIG. 4B is a schematic diagram showing another mode of realization of a system allowing a selective sensing of smoke detection, FIG. 5A is a schematic diagram of a cock In an aircraft which incorporates a sensitivity selection control panel of a system according to the invention, FIG. 5B is an enlarged scale diagram of the sensitivity selection control panel of FIG. 5C is an enlarged diagram of an alarm signal of the cockpit of FIG. 5A, FIG. 6 is a flow chart showing an embodiment of a method according to the invention, the FIG. 7 is a flowchart showing another embodiment of a method according to the invention, FIG. 8A is an illustration in the form of a functional box diagram showing an embodiment of a system according to the invention, and Fig. 8B is an illustration in the form of a functional box diagram showing the sensitivity level determining factors used to determine the cone point sensitivity level. alarm sign of a system according to the invention. Each figure shown in this specification represents a variation of one aspect of the embodiments presented, and only differences will be described in detail.
    [0007] Embodiments of the invention will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all, of the described embodiments are shown. Indeed, several different embodiments may be proposed and should not be construed as being limited to the embodiments set forth below. Rather, these embodiments are proposed so that the present description is thorough and fully expresses the scope of the invention to those skilled in the art. Referring now to the figures, FIG. 1 is an illustration of a perspective view of an overhead vehicle 12, such as an aircraft 12a, which may incorporate one or more embodiments of an aircraft. system 10 (see FIGS. 4A to 4B, 8), a method 200 (see FIG. 6), or a method 300 (see FIG. 7) according to the invention to allow a selective detection of smoke detection on board the aerial vehicle 12, such as in the form of the aircraft 12a.
    [0008] As shown in FIG. 1, the aerial vehicle 12, as in the form of the aircraft 12a, comprises a fuselage 14, a nose 16, wings 18, engines 20, a stabilizer 22 comprising horizontal stabilizers 24 and a vertical stabilizer 26, and a cockpit 28. As further shown in FIG. 1, the aircraft 12a includes an embodiment of the system 10 with the selectable sensitivity smoke detector assemblies 70 and the flight selection control panels. sensitivity 72 coupled via a coupling member 73, such as wired or wireless coupling elements. Although the air vehicle 12, as in the form of the aircraft 12a, shown in FIG. 1, is generally representative of an aircraft for commercial passenger transport comprising one or more embodiments of the system 10, the teachings of the embodiments described may be applied to other passenger aircraft, cargo aircraft, military aircraft, rotorcraft, and other types of aircraft or aerial vehicles, as well as aerospace vehicles, satellites , space launch vehicles, rockets, and other aerospace vehicles, as well as vehicles such as trains, trucks, automobiles, watercraft, ships and submarines, and warehouses or other suitable structures for incorporating one or more embodiments of the system according to the invention. FIG. 2 is a flowchart of an aircraft manufacturing and maintenance process 30. FIG. 3 is a schematic illustration of an aircraft 50. Referring to FIGS. 2 and 3, embodiments of the invention are described in FIG. The invention may be described in the context of the aircraft manufacturing and maintenance process 30, as shown in FIG. 2, and the aircraft 50, as shown in FIG. pre-production, an illustrative aircraft manufacturing and servicing process may include the specification and design 32 of the aircraft 50 and the material supply 34. During manufacture, component manufacturing steps and subsystems 36 and systems integration 38 of the aircraft 50 take place. After that, the aircraft 50 can go through the certification and the delivery 40 to be put into service 42. While it is in service 42, at a customer's location, the aircraft 50 can be programmed for maintenance and service. routine maintenance 44 (which may also include modification, reconfiguration, refurbishment and other appropriate services). Each of the steps of the illustrative aircraft manufacturing and servicing process may be performed or executed by a system integrator, a third party and / or an operator (eg, a customer). Within the scope of this disclosure, a system integrator may include, without limitation, any number of aircraft manufacturers and major system subcontractors. A third party may include, without limitation, any number of vendors, subcontractors and suppliers. An operator may include, without limitation, an airline, a rental company, a military entity, a service organization and other appropriate operators. As shown in FIG. 3, the aircraft 50 produced by the illustrative aircraft manufacturing and maintenance process 30 may comprise a cell 52 with a plurality of systems 54 and an interior 56. For example, the A plurality of systems 54 may include a propulsion system 58 and / or an electrical system 60 and / or a hydraulic system 62 and / or an environmental system 64. Any number of other systems may be included. Although an aerospace example is shown, the principles of the invention can be applied to other industries, such as the automotive industry, the truck industry, the aquatic vehicle industry, such as ships and submarines, the warehouse industry, and other appropriate industries. The methods and systems described herein may be used during one or more of the steps of the illustrative aircraft manufacturing and maintenance process 30. For example, components or sub-assemblies corresponding to the manufacture of components and sub-assemblies assemblies 36 may be manufactured or produced in a manner similar to components or subassemblies produced while aircraft 50 is in service 42. Also, one or more embodiments of apparatus, embodiments of the method, or an association of these, can be used during the manufacture of components and sub-assemblies 36 and the integration of systems 38, for example, substantially by accelerating the assembly or reducing the cost of the aircraft 50. similar, one or more of apparatus embodiments, process embodiments, or a combination thereof, may be used while the aircraft 50 is in a state of being Service 42, for example and without limit, for maintenance and service 44. In one embodiment of the invention, as shown in FIGS. 4A and 4B and FIG. 8A, a system 10 is proposed, such as in the form of the system 10a (see FIG. 4A) or as in the form of the system 10b (see FIG. 4B), to allow a selective detection of smoke detection in the overhead vehicle 12, such as in the form of the aircraft 12a. Fig. 4A is a schematic diagram showing an embodiment of the system 10, such as in the form of the system 10a, to enable selective smoke detection sensitivity. Fig. 4B is a schematic diagram showing another embodiment of the system 10, such as in the form of the system 10b, to enable selective smoke detection sensitivity. Fig. 8A is a block diagram showing one embodiment of the system 10 according to the invention. As shown in FIGS. 4A to 4B and FIG. 8A, the aerial vehicle 12, as in the form of the aircraft 12a, houses the system 10 (see FIG. 8A) to enable a selective detection of smoke detection. on board the aircraft 12a.
    [0009] FIG. 4A shows, in one embodiment, the system 10, such as in the form of the system 10a, installed in the aircraft 12a, such as an aircraft intended for the commercial transportation of passengers. As shown in FIG. 4A, the aircraft 12a, such as an aircraft intended for commercial passenger transport, comprises aircraft sectors 74, which can be categorized into one or more specific areas of the aircraft. Compartment 128. As further shown in FIG. 4A, the aircraft sectors 74, which can be categorized into one or more compartment area 128 specific sectors, preferably comprise the cockpit 28, a cabin area. Passenger 76a, an electrical cargo hold 78, a front cargo hold 80, a wing box 82, a rear cargo hold 84 and a bulk cargo hold 86. The cabin / passenger area 76a (see Fig. 4A) may include one or more closet / storage compartments 88 (see FIG. 4A), one or more washrooms 90 (see FIG. 4A), one or more crew rest compartments 92 (see FIG. 4A), and one or more several offices 94. T As shown in FIG. 4A, the cockpit 28 and the cabin / passenger area 74 are aircraft sectors 74 located on an upper deck 66 of the aircraft 12a. The upper deck 66 is an occupied area of the aircraft 12a which, in general, is occupied by passengers and crew members. As shown in FIG. 4A, the electric cargo hold 78, the forward cargo hold 80, the sail box 82, the rear cargo hold 84, and the bulk cargo hold 86 are aircraft sectors 74. located on a lower deck 68 of the aircraft 12a. The lower deck 68 is an unoccupied area of the aircraft 12a. For example, freight 126 (see FIG. 4A) is shown stored in the rear cargo hold 84 (see FIG. 4A). However, cargo 126 (see Figure 4A) may also be stored in other cargo areas of aircraft 12a (see Figure 4A). FIG. 4B represents, in another embodiment, the system 10, such as in the form of the system 10b, installed in the aircraft 12a, such as a freight aircraft.
    [0010] As shown in FIG. 4B, the aircraft 12a, such as a cargo aircraft, includes aircraft sectors 74, which can be categorized into one or more specific areas of the compartment area 128. this is further illustrated in FIG. 4B, the aircraft sectors 74, which may be categorized into one or more compartment compartment specific sectors 128, preferably comprise the cockpit 28, a main deck cargo hold 76b, the electrical cargo hold 78, the forward cargo hold 80, the sail box 82, the rear cargo hold 84, and the bulk cargo hold 86. As shown in FIG. 4B, the cockpit 28 and the main cargo compartment 76b are aircraft sectors 74 located on the upper deck 66 of the aircraft 12a, and the electric cargo hold 78, the forward cargo hold 80, the wing box 82, the rear cargo hold 84, and the cargo hold f Bulk 86 are aircraft sectors 74 located on the lower deck 68 of the aircraft 12a. Freight 126 (see Figure 4B) is shown stored in the rear cargo hold 84 (see Figure 4B). However, cargo 126 (see FIG. 4B) may also be stored in other cargo areas of aircraft 12a (see FIG. 4B). As shown in FIGS. 4A-4B and 8A, the system 10 includes one or more selectable sensitivity smoke detector assemblies 70 installed on the aircraft 12a. In the embodiment of the system 10, such as in the form of the system 10a, shown in FIG. 4A, the system 10 preferably comprises one or more selectable sensitivity smoke detector assemblies 70 located in the closet / storage compartment 88, the toilet 90, the crew rest compartment 92, and the pantry 94 of the cabin / passenger sector 76a. Further, in the embodiment of the system 10, such as in the form of the system 10a, shown in FIG. 4A, the system 10 preferably comprises one or more selectable sensitivity smoke detector assemblies 70 located in the electrical equipment hold 78, the forward cargo hold 80, the wing box 82, the rear cargo hold 84 and the bulk cargo hold 86. In the system embodiment 10, such as in the form of the system 10b, shown in FIG. In Figure 4B, the system 10 preferably comprises one or more selectable sensitivity smoke detector assemblies 70 located in the main deck cargo hold 76b. Further, in the embodiment of the system 10, such as in the form of the system 10b, shown in FIG. 4A, the system 10 preferably comprises one or more selectable sensitivity smoke detector assemblies 70 located in the equipment hold. 78, the forward cargo hold 80, the wing box 82, the rear cargo hold 84, and the bulk cargo hold 86.
    [0011] As further shown in FIGS. 4A-4B, each of the selectable sensitivity smoke detector assembly (s) 70 is preferably electrically or wirelessly coupled to one or more sensitivity select control panels 72 installed onboard the receiver. the aircraft 12a. In the system embodiment 10, as in the form of the system 10a, shown in FIG. 4A, the system 10 comprises two sensitivity selection control panels 72, including a first sensitivity selection control panel 72a. located in the cockpit 28 and a second sensitivity select control panel 72b located in the cabin / passenger area 76a. In the embodiment of the system 10, such as in the form of the system 10b, shown in FIG. 4B, the system 10 comprises a sensitivity selection control panel 72, including the first sensitivity selection control panel 72a, located in the cockpit 28.
    [0012] As shown in FIGS. 4A to 4B and FIG. 8A, each of the selectable sensitivity smoke detector assembly (s) 70 installed on board the aircraft 12a includes a selectable sensitivity smoke detecting device 71. Selectable sensitivity smoke detector device 71 may include such devices as a selectable ion-type smoke detector device, a selectable photoelectric type smoke detector, a photoelectric selectable smoke detector type (channelized or ambient), or other suitable sensitivity sensing smoke detector 71. An ionically sensitive selectable smoke detector device 20 is adapted to detect the presence of ionized particles created by the combustion process as they are convectively transported through, for example, toilets 90 (see FIG. 4A) or Crew rest compartments 92 (see Figure 4A) in case of fire. It may be mounted in the ceiling or upper side walls of the aircraft sectors 74 (see FIG. 4A) where the selectable sensitivity smoke detector device 71 is located. A photoelectric type selectable smoke detector is designed to detect the presence of smoke particles in the air by reflected light reflection. It also takes into account particles in the air convectively transported in a detection chamber in which light from a pilot lamp is transmitted through a detection chamber. If smoke is present, it will reflect light on a photocell and trigger an alarm. Alternatively, photoelectric sensors based on an improved smoke sensor using two or more discrete wavelengths to determine the presence of smoke and to distinguish between aerosols corresponding to smoke and not corresponding to smoke. smoke can be used. These are also mounted in the ceiling or the upper side walls of the aircraft sectors 74 (see FIG. 4A) where the selectable sensitivity smoke detector 71 is located. The photoelectric-channelizable selectable smoke detector device is similar to the photoelectric type selectable smoke detector device but may be mounted behind the walls of the aircraft sectors 74 (see FIG. 4A) where the sensor device Smoke with 10 selectable sensitivity 71 is located. It differs from the photoelectric type selectable smoke detector device in that fans draw air samples from the aircraft sector 74 into a series of air sampling ports in the walls and ceiling. , and then through a tubular aluminum collector to the detectors.
    [0013] In addition, each selectable sensitivity smoke detector assembly 70 (see FIGS. 4A-4B and FIG. 8A) comprises one or more sensors 132 (see FIG. 8A) electrically or wirelessly coupled to the selectable sensitivity smoke detector device 71 (FIG. see FIGS. 4A-4B and FIG. 8A), and a control apparatus 134 (see FIG. 8A) coupled to the selectable sensitivity smoke detector 71 (see FIGS. 4A-4B and FIG. 8A). The control apparatus 134 (see Fig. 8A) preferably comprises a computer processing device (including hardware and software) 134a (see Fig. 8A). Each selectable sensitivity smoke detector assembly 70 (see FIGS. 4A-4B and FIG. 8A) further comprises system logic 136 (see FIG. 8A) coupled to the selectable sensitivity smoke detector device 71 (see FIGS. 4A-4B and FIG. Figure 8A), or the control apparatus 134 (see Figure 8A). System logic 136 (see FIG. 8A) is preferably configured to autonomously vary in real time two or more alarm setpoint sensitivity levels 100 (see FIGS. 5B, 8A). The system logic 136 (see FIG. 8A) preferably comprises one or more of an algorithm 136a (see FIG. 8A), a software program 136b (see FIG. 8A), a firmware 136c, or "firmware" (see FIG. 8A), or other appropriate system logic 136.
    [0014] Each selectable sensitivity smoke detector assembly 70 (see Figs. 4A to 4B and Fig. 8A) further comprises one or more system inputs 138 (see Fig. 8A) measured by the sensor (s) 132 (see Fig. 8A) and inputs into the selectable sensitivity smoke detector 71 (see Figs. 4A to 4B and Fig. 8A), or inputs to the control apparatus 134 (see Fig. 8A), for processing by the system logic 136 (see Fig. 8A). Each selectable sensitivity smoke detector assembly 70 (see FIGS. 4A-4B and FIG. 8A) further comprises a system output 140 (see FIG. 8A) generated when the alarm setpoint sensitivity level 100 (see FIG. 8A) 10 is triggered. The system output 140 (see FIG. 8A) preferably comprises an alarm signal 114 (see FIGS. 5B, 8A) generated when the alarm setpoint sensitivity level 100 (see FIG. 8A) is triggered. Each selectable sensitivity smoke detector 70 (see FIGS. 4A-4B and FIG. 8A) may further comprise a protection assembly 150 (see FIG. 8A) coupled to the selectable sensitivity smoke detector assembly (s) 70 (see FIG. at 4B and FIG. 8A). The protection assembly 150 (see FIG. 8A) preferably comprises one or more of a software-based protection set 150a (see FIG. 8A), such as a digital input identifier, for example, a word of digital pass or digital code; a physical-based protection set 150b (see Fig. 8A) such as lock or keyed hardware or other appropriate physical-based protection; a location-based protection set 150c (see Fig. 8A), such as location-based limited usage protections; or another suitable protection assembly 150 (see FIG. 8A).
    [0015] As shown in FIGS. 4A-4B, each sensitivity select control panel 72 includes a sensitivity select control 96 (see also FIG. 5B). In one embodiment, the sensitivity select control 96 (see Figs. 4A-4B, 5B) includes a master sensitivity selection control 96a (see Fig. 8A) for selecting and setting a set point sensitivity level of alarm 100 (see FIGS. 5B, 8A) for all or one of the selectable sensitivity smoke detector assemblies 70 (see FIGS. 4A-4B, 8A) simultaneously. In another embodiment, the sensitivity select control 96 (see Figs. 4A to 4B, 5B) comprises a selective sensitivity control 96b (see Fig. 8A) for selecting and adjusting the sensitivity level of the alarm setpoint 100 (see FIGS. 5B, 8A) for one or more, simultaneously, of the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A to 4B, 8A). The sensitivity select control 96 (see Figs. 4A to 4B, 5B) may be selected and activated via a smoke sensitivity select switch 98 (see Fig. 5B) located on or near each of the at least one selectable smoke detector assembly 70 (see FIGS. 4A-4B). FIG. 5A is a schematic diagram of the cockpit 28 of the aircraft 12a 10 (see FIG. 1) incorporating the sensitivity selection control panel 72 (see also FIGS. 4A to 4B) of the system 10. FIG. 5A represents the panel sensitivity selection control 72 installed at a first location of the cockpit 110 on an aircraft control display 111. The sensitivity selection control panel 72 (see FIG. 5A) can be positioned near other control commands. aircraft 113 (see FIG. 5A). FIG. 5A further shows an alarm signal 114 installed at a second location in the cockpit 112. FIG. 5A further shows a crew indication and engine warning system 122 installed at a third cockpit location 120 The Engine Indicator and Crew Alerting System (EICAS) 122 (see Figure 5A) is preferably coupled to one or more data processing units 124. The EICAS typically includes instrumentation of various engine parameters, including, for example, engine speed, temperature values, fuel flow and amount, oil pressure, and other engine parameters. Aircraft systems that can be monitored by the EICAS can include, for example, hydraulic, pneumatic, electrical, de-icing, environmental and steering systems. The Crew Alerting System (Crew Alert System) can be used instead of an annunciator panel. Rather than signaling a system failure by lighting a light behind a translucent button, failures are represented as a list of messages in a small window near other EICAS indications. Fig. 5B is an enlarged scale diagram of the sensitivity select control panel 72 of Fig. 5A showing the sensitivity select control 96. Fig. 5B further shows the smoke sensitivity select control switch 98 and the alarm setpoint sensitivity levels 100. As shown in FIG. 5B, the sensitivity select control panel 72 may further include an ARM control 101 for a cargo fire indicator 105, a front control 102 with a front indicator armed control 102a and a forward indicator front control 102b, and a rear control 104 with a rear indicator armed control 104a and a forward indicator front control 104b. The sensitivity select control panel 72 (see Fig. 5B) further comprises a test switch assembly 106 (see Fig. 5B) including a fire / overheat test indicator 106a (see Fig. 5B) and a test switch. 106b (see FIG. 5B). Test switch assembly 106 (see FIG. 5B) participates in the electrical sensor and sensing integrity of sensor (s) 132 (see FIG. 8A) and system 10 (FIG. 8A) being controlled by a member. crew navigating in the cockpit 28 (see Figure 5B). Alternatively, the test switch assembly 106 may be located on or near each of the selectable sensitivity smoke detector assemblies 70 (see FIGS. 4A-4B and FIG. 8A) to enable a user, such as flight crew or a cargo loading team member, to check the electrical sensor and sensor sensing integrity 132 (see Figure 8A) and system 10 (see Figures 8A) at any time. The sensitivity selection control panel 72 (see Fig. 5B) further comprises a discharge control 108 (see Fig. 5B) with a discharge-free discharge control indicator 108a (see Fig. 5B) and a control indicator of discharge-discharge 108b (see FIG. 5B). Fig. 5C is an enlarged scale diagram of the alarm signal 114 of the cockpit 28 of Fig. 5A. The alarm signal 114 (see Fig. 5C) preferably includes a warning flag 116 and a warning flag 118. Fig. 8A further shows a system entry 138 of sensitivity level determination factors 130 One or more of the sensitivity level determining factors 130 (see FIG. 8A) can be used to select and set the alarm setpoint sensitivity levels 100 (see FIG. 8A) for the sensing smoke detector device. selectable 71 3027147 (see FIG. 8A). The system 10 (see FIG. 8A) allows a user, such as a flight crew member or a cargo loading team member, to select one or more alarm setpoint sensitivity levels 100 (FIG. see FIG. 8A) ranging from a certified baseline setpoint to more sensitive set points. As used herein, a "certified baseline setpoint" means a current certified baseline level set by the Federal Aviation Administration (FAA), which currently means that all The selectable sensitivity smoke detector 70 and the system 10 will sound an alarm within one (1) minute of the start of a fire, including in the presence of smoke particles or other small particles suspended in the fire. air or other substances. The sensor (s) 132 of the selectable sensitivity smoke detector assembly 70 (see Fig. 8A) can detect one of the sensitivity level determination factors 130 (see Fig. 8B), perform one or more signal measurements, and send the signal measurements to system logic 136 as a system input 138 (see FIG. 8A). The system logic 136 may be in the controller 134 (see FIG. 8A) or in the selectable sensitivity smoke detector 71 (see FIG. 8A) and the system logic 136 will take the system input 138 (see FIG. 8A) from the one or more sensors 132 (see FIG. 8A) and will review a series of decisions or logic to decide whether or not to trigger an alarm signal 114 (see FIG. 5B). The alarm signal 114 (see FIG. 5B) is the system output 140 if the alarm is triggered. The decision or logic used to determine whether or not to trigger the alarm signal 114 (see FIG. 5B) is preferably based on the use of one or more sensitivity level determination factors 130 to determine the alarm set point sensitivity levels 100 (see FIG. 8A) of the system 10 (see FIG. 8A). Fig. 8B is a functional box diagram showing the sensitivity level determination factors 130 used to determine the alarm set point sensitivity levels 100 (see Fig. 8A) of the system 10 (see Fig. 8A). according to the invention. As shown in FIG. 8B, the sensitivity level determination factors 130 include one or more factors selected from a mission type 130a of the aircraft 12a (see FIG. 1), a type of cargo 130b in the aircraft 12a (see FIG. 1), a specific sector zone type 130c in the aircraft 12a (see FIG. 1), an assignment state 130d in the aircraft 12a (see FIG. 1), a density level 130e smoke in an aircraft sector 74 (see Figure 8A), a moisture content 130f in the aircraft sector 74 (see Figure 8A), a 130g temperature of the aircraft sector 74 (see Figure 8A), a type of gas present 130h in the aircraft sector 74 (see FIG. 8A), a present gas concentration 130i in the aircraft sector 74 (see FIG. 8A), an aircraft engine operating state 130j, a aerodynamic speed 130k of the aircraft 12a (see FIG. 1), an altitude 1301 of the aircraft 12a (see FIG. FIG. 1), an open or closed aircraft door state 130m, an aircraft system state 130n, an environmental control system control 130o on the aircraft 12a (see FIG. 1), a system configuration 130p environmental control in the aircraft 12a (see Figure 1), an aircraft 130q air conditioning system on or off status, a condition of on or off of the air conditioning system. cargo area air 130r, an aircraft configuration state 130s, or other suitable sensitivity level determining factor 130. As used herein, "environmental control system setting" means a setting of the air vehicle environmental control system 12 (see FIG. 1), such as the aircraft 12a (see FIG. 1), where the adjustment preferably comprises the amount of airflow that the air conditioning system produces or moves, for example e, in cubic feet per minute (cfm: lcfm = 0.47 liter / second = 0.47 10-3m3s-1); the amount of airflow flowing in the cabin / passenger area 76a (see FIG. 4A) or the main deck cargo hold 76b (see FIG. 4B) relative to the electric cargo hold 78 (FIG. see FIGS. 4A to 4B), at the forward cargo hold 80 (see FIGS. 4A to 4B), at the wing caisson 82 (see FIGS. 4A to 4B), at the rear cargo hold 84 (see FIGS. 4A to 4B), and bulk cargo hold 86 (see FIGS. 4A-4B); a temperature of the airflow that the air conditioning system produces or displaces; the fact that recirculating air fans are on or off; and / or the fact that other types of fans are on or off for aircraft systems, such as equipment cooling or other suitable aircraft systems.
    [0016] In another embodiment, a method 200 (see FIG. 6) for enabling a selective smoke detection sensitivity on board the aircraft 12a (see FIG. 1) is provided. Fig. 6 is a flowchart showing an embodiment of the method 200 according to the invention. As shown in FIG. 6, method 200 includes step 202 of installing one or more selectable sensitivity smoke detector assemblies 70 (see FIGS. 4A-4B) aboard the aircraft 12a (see FIGS. 4A to 4B). As shown in FIG. 6, the method 200 further comprises a step 204 of electrical or wireless coupling of the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A to 4B) installed on the aircraft 12a. (see FIG. 1) to one or more sensitivity selection commands 96 (see FIGS. 4A to 4B) installed on the aircraft 12a (see FIGS. 4A to 4B). The electrical or wireless coupling step 204 of the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A-4B) may include the electrical or wireless coupling of the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. Figs. 4A-4B) to one or more sensitivity selection controls 96 (see Fig. 5B) including a smoke sensitivity selection control switch 98 (see Fig. 5B) located on or near each of the one or more sets. smoke detector with selectable sensitivity 70 (see FIGS. 4A-4B). Step 204 of the electrical or wireless coupling of the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A-4B) may include electrical or wireless coupling of the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A-4B) to one or more sensitivity select commands 96 (see FIG. 5B) including a smoke sensitivity selection control switch 98 (see FIG. 5B) located in one or more aircraft sectors 74 (see FIG. FIGS. 4A to 4B) in the aircraft 12a (see FIGS. 4A to 4B). The aircraft sector or sectors 74 (see FIGS. 4A to 4B) preferably comprise the cockpit 28 (see FIGS. 4A to 4B), the cabin / passenger sector 76a (see FIG. 4A), the deck cargo hold. main 76b (see FIG. 4B), the electric cargo hold 78 (see FIGS. 4A to 4B), the forward cargo hold 80 (see FIGS. 4A to 4B), the wing caisson 82 (see FIGS. 4A to 4B), the rear cargo hold 84 (see FIGS. 4A to 4B), the bulk cargo hold 86 (see 3027147 18 FIGS. 4A to 4B), the closet / storage compartment 88 (see FIG. 4A), the lavatory 90 (see FIG. 4A ), the crew rest compartment 92 (see Figure 4A) and the galley 94 (see Figure 4A). As shown in FIG. 6, the method 200 further comprises a step 206 of selecting the alarm set point sensitivity level 100 (see FIG. 5B) from two or more point sensitivity levels. alarm setpoint 100 (see FIG. 5B) for each of the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A to 4B). The two or more levels of alarm setpoint sensitivity 100 (see FIG. 5B) are preferably based on one or more of a mission of the aircraft 12a (see FIGS. 1, 4A-4B), the freight 126 (see FIGS. 4A to 4B) on the aircraft 12a (see FIGS. 1, 4A to 4B) and an assignment state 130d (see FIG. 8B) of the aircraft 12a (see FIGS. 1, 4A to 4B) . The step 206 for selecting the alarm setpoint sensitivity level 100 (see FIGS. 5B, 8A) further comprises, in one embodiment, the use of a master sensitivity selection control 96a (FIG. see FIG. 8A) to select and set the alarm setpoint sensitivity level 100 (see FIG. 8A) for all or one of the selectable sensitivity smoke detector assemblies 70 (see FIG. 8A) simultaneously. The step 206 of selecting the alarm setpoint sensitivity level 100 (see FIGS. 5B, 8A) further comprises, in another embodiment, the use of a selective sensitivity selection control 96b. (See Fig. 8A) to select and set the alarm setpoint sensitivity level 100 (see Fig. 8A) for one or more simultaneously of the selectable sensitivity smoke detector assembly (s) 70 (see Fig. 8A). . The step 206 of selecting the alarm setpoint sensitivity level 100 (see FIG. 5B) may include the selection of the alarm setpoint sensitivity level 100 (see FIG. 5B) remotely or in a remote manner. each of the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A-4B). The step 206 of selecting the alarm set point sensitivity level 100 (see FIG. 5B) may include the selection of the alarm set point sensitivity level 100 (see FIG. 5B) according to a setting 130o environmental control system (see Figure 8B).
    [0017] As shown in FIG. 6, the method 200 further comprises an optional step 208 of maintaining the selected alarm set point sensitivity level 100 (see FIG. 5B), until a user changes. the selected alarm setpoint sensitivity level 100 (see FIG. 5B) at a different alarm setpoint sensitivity level 100 (see FIG. 5B). As shown in FIG. 6, the method 200 further comprises an optional step 210 of autonomously varying the selected alarm set point sensitivity level 100 (see FIG. 5B) in real time using one or more sensors 132 (FIG. see FIG. 8A), a control apparatus 134 (see FIG. 8A) and a system logic 136 (see FIG. 8A) of the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A to 4B, 8A). The method 200 (see FIG. 6) may further comprise an optional step 212 of generating an alarm signal 114 (see FIG. 5C) in response to the one or more selectable sensitivity smoke detector assemblies 70 (see FIGS. 4B) measuring and detecting a level of smoke density 130e (see FIG. 8B) which satisfies a predetermined threshold 142 (see FIG. 8A) of the alarm setpoint sensitivity level 100 (see FIG. 5B). In another embodiment, a method 300 (see FIG. 7) for enabling a selective smoke detection sensitivity on board the aircraft 12a (see FIG. 1) is provided. Fig. 7 is in the form of a flow chart showing an embodiment of the method 300. As shown in Fig. 7, the method 300 includes step 302 of installing one or more smoke detector assemblies to selectable sensitivity 70 (see FIGS. 4A to 4B) on board the aircraft 12a (see FIG. 1). As shown in FIG. 7, the method 300 further comprises a step 304 of using the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A-4B) on board the aircraft 12a (see FIG. ) to autonomously vary in real time its alarm set point sensitivity level or 100 (see FIG. 5B), selected from two or more levels of alarm set point sensitivity 100 (see FIG. 5B), as a function of sensitivity level determination factors 130 (see FIGS. 8A and 8B) comprising one or more factors selected from an aircraft system state 130n (see FIG. 8B) and a configuration state of FIG. 130s aircraft (see FIG. 8B).
    [0018] The step 304 of using the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A-4B) comprises the autonomous variation of the selected alarm set point sensitivity level 100 (see FIG. 5B) in FIG. real time using one or more sensors 132 (see FIG. 8A), the control apparatus 134 (see FIG. 8A) and the system logic 136 (see FIG. 8A) of the selectable sensitivity smoke detector assembly (s) 70 (see FIG. Figures 4A to 4B). Step 304 of using the selectable sensitivity smoke detector assembly (s) 70 (see FIGS. 4A-4B) further comprises the autonomous variation of the selected alarm setpoint sensitivity level 100 (see FIG. 5B). in real time, according to the sensitivity level determination factors 130 (see FIG. 8B) comprising one or more factors in the following list: a mission type 130a (see FIG. 8B) of the aircraft 12a (see FIG. ), a type of freight 130b (see FIG. 8B) in the aircraft 12a (see FIG. 1), a specific sector zone type 130c (see FIG. 8B) in the aircraft 12a (see FIG. Assigned state 130d (see FIG. 8B) of the aircraft 12a (see FIG. 1), a smoke density level 130e (see FIG. 8B) in an aircraft sector 74 (see FIGS. 4A to 4B, 8A). , a moisture content 130f (see FIG. 8B) in the aircraft sector 74 (see FIGS. 4A to 4B, 8A), a 130g (see FIG. 8B) of the aircraft sector 74 (see FIGS. 4A to 4B, 8A), a type of gas present 130h (see FIG. 8B) in the aircraft sector 74 (see FIGS. 4A to 4B, 8A). ), a present gas concentration 130i (see FIG. 8B) in the aircraft sector 74 (see FIGS. 4A to 4B, 8A), an aircraft engine operating state 130j (see FIG. 8B), an aerodynamic speed 130k (see FIG. 8B) of the aircraft 12a (see FIG. 1), an altitude 1301 (see FIG. 8B) of the aircraft 12a (see FIG. 1), an open door state or closed aircraft door 130m (FIG. see FIG. 8B), an environmental control system setting 103o (see FIG. 8B) on the aircraft 12a (see FIG. 1), an environmental control system configuration 130p (see FIG. 8B) on the aircraft 12a (see FIG. 1), an on / off state of aircraft air-conditioning system 130q (see FIG. 8B).
    [0019] As shown in FIG. 7, the method 300 further comprises an optional step 306 of increasing or reducing the alarm setpoint sensitivity level 100 (see FIG. 5B), depending on the determination factor of sensitivity level 130 (see FIGS. 8A and 8B) of a state of on or off of the cargo area air conditioning system 130r (see FIG. 8B). As shown in FIG. 7, the method 300 further comprises an optional step 308 of generating an alarm signal 114 (see FIG. 5C) in response to the one or more selectable sensitivity smoke detector assemblies 70 (see FIGS. 4A-4B) measuring and detecting a smoke density level 130e (see FIG. 8B) in an aircraft sector 74 (see FIG. 8A) which satisfies a predetermined threshold 142 (see FIG. 8A) of the point of sensitivity level. alarm setpoint 100 (see FIG. 5B). The described embodiments of the system 10 (see FIGS. 4A to 4B), the method 200 (see FIG. 6), and the method 300 (see FIG. 7) allow flight crews or loading crews to select the sensitivity to which the selectable sensitivity smoke detector assemblies 70 (see Figures 4A to 4B) are to be set. The least sensitive setting will be set to a current certified baseline setpoint. In addition, the system 10 (see FIGS. 4A to 4B), the method 200 (see FIG. 6), and the method 300 (see FIG. 7) enable flight crews and loading crews to select more sensitive settings in function of a risk of a false alarm compared to the risk of a fire situation. This may enable the flight crews and loading crews to select a higher sensitivity for the alarm set point sensitivity level 100 (see FIG. 5B) for the selectable sensitivity smoke detector assemblies 70 (see FIG. 4A). at 4B), if the aircraft 12a (see Figures 4A-4B) carries batteries, such as lithium batteries, or other cargo causing a high threat / reduced false alarm. In addition, described embodiments of system 10 (see FIGS. 4A to 4B), method 200 (see FIG. 6), and method 300 (FIG. 7) allow two or more point sensitivity levels. alarm setpoint 100 (see FIG. 5B) to be set in one embodiment by the flight crews or loading crews which act to manually select the alarm set point sensitivity level 100 (see FIG. 8A). and when the selectable sensitivity smoke detector assembly 70 (see Figs. 4A to 4B, 8A) reaches the set alarm setpoint sensitivity level 100 (see Fig. 8A), the alarm signal 114 is triggered. Alternatively, in another embodiment, the system 10 (see FIGS. 4A-4B), the method 200 (see FIG. 6), and the method 300 3027147 22 (see FIG. 7) allow two or more levels of alarm setpoint sensitivity 100 (see FIG. 5B) to be set by the use of the selectable sensitivity smoke detector assembly (s) 70 (see FIG. 8A) themselves to autonomously vary in real time their Alarm set point sensitivity level 100 (see Fig. 8A), selected from two or more alarm set point sensitivity levels 100 (see Fig. 8A), depending on various timing factors. determining sensitivity level 130 (see FIG. 8B). In addition, the described embodiments of the system 10 (see FIGS. 4A to 4B), the method 200 (see FIG. 6), and the method 300 (see FIG. 7) allow the application of a multiple-setting smoke detector. level of sensitivity on aircraft, including aircraft for the commercial transport of passengers and aircraft for the transport of freight, allow protection against false alarms due to vapors created by fresh fruits or fresh flowers as freight, allow one or more selectable sensitivity smoke detector assemblies 70 (see FIGS. 4A-4B, 8A) located in a plurality of specific sectors of compartment area 128 (see FIGS. 4A-4B), and make it possible to change the sensitivity settings , such as the alarm setpoint sensitivity levels 100 (see FIG. 5B), from one or more aircraft sectors 74 (see FIGS. 4A to 4B), including the freight, and the cockpit 28 (see Figures 4A to 4B) or the cockpit. In addition, described embodiments of the system 10 (see FIGS. 4A to 4B), the method 200 (see FIG. 6), and the method 300 (see FIG. 7) are designed to provide an early warning of smoke or fire. which, in turn, will provide more time to safely put the crew and / or passengers on the ground. In addition, the description includes embodiments according to the following clauses: Clause 1. A method for enabling a selective sensing of smoke detection on board an aircraft, the method comprising the steps of: installing one or more several smoke detector assemblies with selectable sensitivity on board the aircraft; electrically or wirelessly coupling the selectable sensitivity smoke detector assembly (s) installed on the aircraft to one or more 23 sensitivity select commands installed on board the aircraft; and selecting an alarm set point sensitivity level from two or more alarm setpoint sensitivity levels for each of the selectable sensitivity smoke detector assembly (s) based on 5 sensitivity level determination comprising one or more of a mission type of the aircraft, a type of cargo on the aircraft, a specific sector type of compartment area on the aircraft and an assignment status on the aircraft. aircraft. Clause 2. The method of clause 1, further comprising a step of maintaining the selected alarm set point sensitivity level until a user changes the alarm set point sensitivity level. selected at a different alarm setpoint sensitivity level. Clause 3. The method of clause 1, further comprising a step of autonomously varying the selected alarm setpoint sensitivity level in real time using one or more sensors, a control apparatus, and system logic the one or more smoke detector assemblies with selectable sensitivity. Clause 4. The method of clause 1, further comprising a step of generating an alarm signal in response to the selectable sensitivity smoke detector assembly (s) 20 measuring and detecting a level of smoke density in a dif- aircraft that satisfies a predetermined threshold of the alarm set point sensitivity level. Clause 5. The method of clause 1, wherein the step of electrically or wirelessly coupling the selectable sensitivity smoke detector assembly (s) comprises the electrical or wireless coupling of the at least one selectable smoke detector assembly (s). one or more sensitivity selection commands comprising a smoke sensitivity selection control switch located on or near each of the one or more selectable smoke detector assemblies.
    [0020] Clause 6. The method of clause 1, wherein the step of electrically or wirelessly coupling the selectable sensitivity smoke detector assembly (s) includes the electrical or wireless coupling of the at least one selectable sensitivity smoke detector assembly (s). one or more sensitivity select controls comprising a smoke sensitivity select control switch located in one or more aircraft sectors including a cockpit, a cabin / passenger sector, a main deck cargo bay, an electric cargo hold, a forward cargo bay, a wing box, a rear cargo bay, a bulk cargo hold, a closet, a storage compartment, a toilet, a crew sleeping compartment and an office. Clause 7. The method of clause 1, wherein the step of selecting the alarm setpoint sensitivity level includes selecting the alarm setpoint sensitivity level remotely or near each 10 or smoke detector assemblies with selectable sensitivity. Clause 8. The method of clause 1, wherein the step of selecting the alarm setpoint sensitivity level includes using a master sensitivity selection control to select and adjust the sensitivity level of the alarm. alarm setpoint for all or one of the selectable sensitivity smoke detector assemblies simultaneously, or includes the use of a selective sensitivity select control to select and adjust the setpoint sensitivity level of alarm for one or more, simultaneously, of the smoke detector assembly (s) with selectable sensitivity. Clause 9. The method of clause 1, wherein the step of selecting the alarm set point sensitivity level comprises selecting the alarm set point sensitivity level based on the set point of the alarm set point sensitivity factor. sensitivity level of an environmental control system setting. Clause 10. A method for enabling a selective smoke detection sensibility on board an aircraft, the method comprising the steps of: installing one or more selectable sensitivity smoke detector assemblies aboard the aircraft; and using the selectable sensitivity smoke detector assembly (s) on board the aircraft to autonomously vary in real time its alarm setpoint sensitivity level or level, selected from two or more, alarm setpoint sensitivity levels, according to sensitivity level determining factors comprising one or more of an aircraft system state and an aircraft configuration state. Clause 11. The method of clause 10, further comprising a step of increasing or reducing the alarm set point sensitivity level, based on the sensitivity level determination factor of a state of alarm. running or stopping of cargo area air conditioning system. Clause 12. The method of clause 10, further comprising a step of generating an alarm signal in response to the selectable sensitivity smoke detector assembly (s) measuring and detecting a level of smoke density in a region of interest. aircraft that satisfies a predetermined threshold of the alarm set point sensitivity level. Clause 13. The method of clause 10, wherein the step of using the one or more selectable sensitivity smoke detector assemblies comprises the autonomous variation of the selected alarm set point sensitivity level in real time using one or more sensors, a control apparatus, and system logic of the one or more selectable smoke detector assemblies. Clause 14. The method of clause 10, wherein the step of using the one or more selectable sensitivity smoke detector assemblies comprises the autonomous variation of the selected alarm set point sensitivity level in real time, in a function of the sensitivity level determining factors comprising one or more of a mission type of the aircraft, a type of cargo in the aircraft, a specific sector type of compartment area in the aircraft, a condition aircraft, a level of smoke density in an aircraft sector, a moisture content in the aircraft sector, a temperature of the aircraft sector, a type of gas present in the aircraft sector, aircraft, a concentration of gas present in the aircraft sector, an aircraft engine operating state, an aircraft aerodynamic speed, an aircraft altitude, an open door state or a closed door state. 'ac an aircraft environmental control system control, an aircraft environmental control system configuration, and an aircraft air conditioning system on or off state. Clause 15. A system for enabling a selective smoke detection sensitivity on board an aircraft, the system comprising: one or more selectable smoke detector assemblies installed on board the aircraft, each smoke detector assembly on selectable sensitivity comprising: a selectable sensitivity smoke detector device; one or more sensors coupled electrically or wirelessly to the selectable sensitivity smoke detector device; a control apparatus coupled to the selectable sensitivity sensing smoke detector device; a system logic coupled to the selectable sensitivity smoke detector device or control device, the system logic configured to autonomously vary in real time two or more alarm setpoint sensitivity levels, based on sensitivity level determining factors comprising one or more of an aircraft system state and an aircraft configuration state; one or more system inputs measured by the one or more sensors and inputs in each selectable sensitivity smoke detector device, or inputs to the control apparatus, for processing by the system logic; and a generated system output when the alarm setpoint sensitivity level is triggered. Clause 16. The clause system 15, further comprising a protection assembly coupled to the selectable sensitivity smoke detector assembly (s), the protection assembly comprising a software-based protection assembly and / or a protection assembly physically based and / or location-based protection package. Clause 17. The clause system 15, wherein the control apparatus comprises a computer processor device. Clause 18. The system of clause 15, wherein the system logic comprises one or more of an algorithm, a software program, and a firmware (in English: firmware). Clause 19. The system of clause 15, wherein the sensitivity level determination factors further include one or more of a mission type of the aircraft, a type of cargo in the aircraft, a specific sector type 30 of compartment area on the aircraft, a state of assignment on the aircraft, a level of smoke density in an aircraft sector, a moisture content in the aircraft sector, a temperature of the aircraft sector, aircraft, a type of gas present in the aircraft sector, a concentration of gas present in the aircraft sector, an aircraft engine operating state, an aircraft aerodynamic speed, an aircraft altitude, aircraft, an open or closed aircraft door state, an environmental control system setting on the aircraft, an environment control system configuration on the aircraft, a running state or shutdown of packaging system aircraft air, and a running or stopping state of the cargo area air conditioning system. Clause 20. The clause system 15, wherein the system output comprises an alarm signal generated when the alarm setpoint sensitivity level is triggered.
    [0021] Numerous modifications and other embodiments of the description will come to the mind of those skilled in the art, to which the present description belongs, having the advantage of the teachings presented in the foregoing descriptions and the accompanying drawings. The embodiments described herein are intended to be illustrative and are not intended to be limiting or exhaustive.
    [0022] Although specific terms are used herein, they are used in a generic and descriptive sense only and not for limiting purposes.
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. A method for enabling a selective smoke detection sensitivity on board an aircraft (12a), characterized in that it comprises the steps of: - installing (202) one or more smoke detector assemblies with selectable sensitivity ( 70) on board the aircraft (12a); - electrical or wireless coupling (204) of the selectable sensitivity smoke detector assembly (70) installed on board the aircraft (12a) to one or more sensitivity select commands (96) installed on board the aircraft; aircraft (12a); and selecting (206) an alarm setpoint sensitivity level (100) from two or more alarm setpoint sensitivity levels for each of the selectable sensitivity smoke detector assembly (s). (70), based on sensitivity level determining factors including one or more of a mission type (130a) of the aircraft (12a), a type of cargo (130b) aboard the aircraft (12a). ), a specific area type of compartment area (130c) on the aircraft (12a), and an assignment state (130d) on the aircraft (12a).
    [0002]
    The method of claim 1, further comprising a step of maintaining (208) the selected alarm setpoint sensitivity level (100) until a user changes the level of the alarm level. alarm setpoint sensitivity (100) selected at a different alarm setpoint sensitivity level (100).
    [0003]
    3. Method according to claim 1, characterized in that it further comprises an autonomous variation step (208) of the alarm set point sensitivity level (100) selected in real time using one or more sensors ( 132), a control apparatus (134), and system logic (136) of the selectable sensitivity smoke detector assembly (70).
    [0004]
    The method of claim 1, further comprising a step of generating (212) an alarm signal in response to the at least one selectable smoke detector assembly (70) measuring and detecting a level of smoke density in an aircraft sector (12a) that reaches a predetermined threshold of the alarm set point sensitivity level (100).
    [0005]
    The method of claim 1, characterized in that the step of electrically or wirelessly coupling (204) the at least one selectable smoke detector assembly (70) comprises electrically or wirelessly coupling the detector assembly (s). selectable sensitivity smoke (70) to one or more sensitivity select commands (96) comprising a smoke sensitivity select control switch (98) located on or near each of the one or more smoke detector assemblies with selectable sensitivity (70).
    [0006]
    The method of claim 1, characterized in that the step of electrically or wirelessly coupling (204) the at least one selectable smoke detector assembly (70) comprises electrically or wirelessly coupling the detector assembly (s). selectable smoke detector (70) with one or more sensitivity selection commands (96) comprising a smoke sensitivity selection control switch located in one or more aircraft sectors (12a) including a cockpit (28) a cabin / passenger area (76a), a main deck freight bay (76b), an electric cargo bay (78), a forward cargo bay (80), a wing box (82), a rear cargo hold (84), a bulk cargo hold (86), a closet, a storage compartment, a toilet (90), a crew rest compartment (92), and a galley (94) .
    [0007]
    The method of claim 1, characterized in that the step of selecting (206) the alarm set point sensitivity level (100) comprises selecting the alarm set point sensitivity level ( 100) away from or near each of the one or more selectable smoke detector assemblies (70).
    [0008]
    The method of claim 1, characterized in that the step of selecting (206) the alarm set point sensitivity level (100) comprises using a master sensitivity selection control (96a). to select and set the alarm setpoint sensitivity level (100) for the entire 3027147 or selectable sensitivity smoke detector assemblies (70) simultaneously, or includes the use of a selection control selective sensitivity (96b) for selecting and setting the alarm set point sensitivity level (100) for one or more simultaneously of the selectable sensitivity smoke detector assembly (70).
    [0009]
    The method of claim 1, characterized in that the step of selecting (206) the alarm set point sensitivity level (100) includes selecting the alarm set point sensitivity level (100). ) according to the sensitivity level determining factor 10 of an environment control system setting (130o).
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    申请号 | 申请日 | 专利标题
    US14512447|2014-10-12|
    US14/512,447|US9472079B2|2014-10-12|2014-10-12|Method and system to enable selective smoke detection sensitivity|
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