CN109533348A - A kind of fireproof fire-extinguishing control system for aircraft engine - Google Patents
A kind of fireproof fire-extinguishing control system for aircraft engine Download PDFInfo
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- CN109533348A CN109533348A CN201811340614.9A CN201811340614A CN109533348A CN 109533348 A CN109533348 A CN 109533348A CN 201811340614 A CN201811340614 A CN 201811340614A CN 109533348 A CN109533348 A CN 109533348A
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- 238000000034 method Methods 0.000 claims abstract description 21
- 230000010365 information processing Effects 0.000 claims description 10
- 238000012545 processing Methods 0.000 claims description 10
- 238000012423 maintenance Methods 0.000 claims description 9
- 230000001629 suppression Effects 0.000 claims description 6
- 238000012360 testing method Methods 0.000 claims description 5
- 230000002159 abnormal effect Effects 0.000 claims description 3
- 230000005856 abnormality Effects 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 239000000523 sample Substances 0.000 claims description 3
- 238000010977 unit operation Methods 0.000 claims description 3
- 238000001514 detection method Methods 0.000 abstract description 6
- 230000007812 deficiency Effects 0.000 abstract description 3
- 230000010354 integration Effects 0.000 abstract description 3
- 238000011161 development Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
-
- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C3/00—Fire prevention, containment or extinguishing specially adapted for particular objects or places
- A62C3/07—Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles
- A62C3/08—Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
-
- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C37/00—Control of fire-fighting equipment
- A62C37/36—Control of fire-fighting equipment an actuating signal being generated by a sensor separate from an outlet device
- A62C37/38—Control of fire-fighting equipment an actuating signal being generated by a sensor separate from an outlet device by both sensor and actuator, e.g. valve, being in the danger zone
- A62C37/40—Control of fire-fighting equipment an actuating signal being generated by a sensor separate from an outlet device by both sensor and actuator, e.g. valve, being in the danger zone with electric connection between sensor and actuator
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- Public Health (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Fire Alarms (AREA)
Abstract
The application belongs to aircraft engine fireproof fire-extinguishing technical field, in particular to a kind of fireproof fire-extinguishing control system for aircraft engine.System includes: information acquisition unit, information process unit, fire extinguishing control unit and output unit.Information acquisition unit is for acquiring fire detector information and temperature parameter；Information process unit is used to generate warning information according to the fire detector information and temperature parameter of the information acquisition unit；Fire extinguishing control unit is used to control fire extinguishing system according to the warning information and external command of the information process unit and put out a fire, and generates fire extinguishing information；Output unit is for exporting the warning information and the fire extinguishing information.The application compensates for deficiency existing for traditional fire detection and fire extinguishing system, and fire detection and fire extinguishing are integrated in one, and by fire detector and temperature parameter information comprehensive descision fire alarm, has the characteristics that technologically advanced, false alarm rate is low, integration degree is high.
Description
Technical field
The application belongs to aircraft engine fireproof fire-extinguishing technical field, in particular to a kind of fire prevention for aircraft engine
Extinguishment control system.
Background technique
During the work time because of reasons aircraft engines such as parts loss, fuel leakage, electric wiring short circuit, battle injuries
Be likely to occur fire alarm, if taking measures not in time, not only can badly damaged engine, but also flight safety may be jeopardized.Therefore,
Modern aircraft, no matter military secret, civil aircraft, be provided with engine fire -detecting system and fire extinguishing system.
Fire -detecting system is used to monitor the fire alarm alert in enging cabin and the cabin APU, and passes through the alarms sides such as light, voice
Formula timely and accurately provides fire alarm to flight unit.When fire extinguishing system is caught fire for aircraft engine, by flight unit root
It operates fire extinguishing switch and fire-suppression bottle according to fire alarm index signal ignition point is implemented to put out a fire.
The system that traditional aircraft fire -detecting system is two independences with fire extinguishing system, separates, when fire alarm occurs for aircraft
When, fire alarm, which is exported, after flight unit finds fire alarm alarm to warning system from fire -detecting system restarts fire extinguishing system
It puts out a fire, the speed put out a fire to a certain extent and accuracy depend on the subjective response power of flight unit, misoperation or not
It can all cause an immeasurable loss in time.Meanwhile fire -detecting system is influenced by environment, weather etc. it is possible that false-alarm,
More increase the burden of flight unit.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
There is provided a kind of fireproof fire-extinguishing control systems for aircraft engine for the purpose of the application, to solve existing skill
At least one problem existing for art.
The technical solution of the application is:
A kind of fireproof fire-extinguishing control system for aircraft engine, comprising:
Information acquisition unit, for acquiring fire detector information and temperature parameter；
Information process unit, for being generated according to the fire detector information and temperature parameter of the information acquisition unit
Warning information；
Fire extinguishing control unit, for controlling fire extinguishing system according to the warning information and external command of the information process unit
System is put out a fire, and generates fire extinguishing information；
Output unit, for exporting the warning information and the fire extinguishing information.
Optionally, further includes:
Self-test unit, the self-test unit include startup self-check module, period selftest module and maintenance selftest module；
The startup self-check module is accused after noting abnormalities in time for checking each unit and external cabling
It is alert；
The period selftest module, for being monitored at predetermined intervals to each abnormal unit；
The maintenance selftest module, for being checked and being safeguarded according to ground maintenance instruction.
Optionally, the information acquisition unit includes:
Detector information acquisition module, including fire detector and with the matched acquisition interface of fire detector, it is described
Fire detector is used to detect the fire alarm information in region to be measured, and the acquisition interface is used to acquire the fire alarm letter of engine region
Breath, and the acquisition interface includes the location information where the corresponding fire detector, when generation fire alarm or line fault
When, current fire alarm information and location information are sent to information process unit；
Temperature parameter acquisition module, for acquiring the temperature parameter of engine region.
Optionally, the fire detector is respectively in enging cabin, the cabin APU, engine fan case and combustion chamber machine
Casket at least arranges one.
Optionally, the temperature parameter includes: temperature, oil temperature, engine after engine intake temperature, gas turbine
Cabin temperature.
Optionally, the information process unit includes:
Detector information processing module, for one or more fire alarm informations of pick-up probe information acquisition module and position
Confidence is ceased and is handled, and generates alarm signal
Temperature parameter processing module, by real time temperature compared with predetermined temperature, if predetermined period real time temperature is persistently higher than
Predetermined temperature judges engine fire, generates alarm signal；
When detector information processing module and temperature parameter processing module judge fire alarm occur, information process unit is raw
At warning information.
Optionally, the fire extinguishing control unit includes:
Operational module, the operational module can be realized self-extinguishing mode and be gone out manually by the manipulation of flight unit
The switching of fiery mode.
Optionally, the operational module includes control switch and indicator light, and the control switch includes that fire extinguishing control is opened
It closes, fire-suppression bottle switch, left hair fire extinguishing switch, right hair fire extinguishing switch, APU fire extinguishing switch, each control switch is provided with instruction
Lamp is used to indicate the position of switch knob, vectored flight unit operation.
Optionally, the fire extinguishing control unit, according to the warning information of the information process unit and external command control
Fire extinguishing system processed carries out fire extinguishing
When external command is self-extinguishing mode, fire extinguishing control unit is according to the warning information, automatic starting fire extinguishing
System is put out a fire；
When external command is manual modes of fire suppression, operational module input fire extinguishing instruction is manually operated by flight unit and is carried out
Fire extinguishing.
Optionally, the output unit, exports the warning information and the fire extinguishing information includes:
To airplane fault lamp and display outputting alarm information and fire extinguishing information.
At least there are following advantageous effects in the application:
The fireproof fire-extinguishing control system for aircraft engine of the application, compensates for traditional fire detection and fire extinguishing system
Existing deficiency, fire detection and fire extinguishing are integrated in one, and pass through fire detector and temperature parameter information comprehensive descision
Fire alarm has the characteristics that technologically advanced, false alarm rate is low, integration degree is high, be the following military secret, civil aircraft development direction with become
Gesture has extensive and far-reaching application prospect.
Detailed description of the invention
Fig. 1 is the schematic diagram of the fireproof fire-extinguishing control system for aircraft engine of one embodiment of the application；
Fig. 2 is the flow chart of the fireproof fire-extinguishing control system for aircraft engine of one embodiment of the application.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 to Fig. 2 the application is described in further details with reference to the accompanying drawing.
This application provides a kind of fireproof fire-extinguishing control systems for aircraft engine, including information acquisition unit, letter
Cease processing unit, fire extinguishing control unit and output unit.
Wherein, as shown in Figure 1, information acquisition unit is for acquiring fire detector information and temperature parameter；Information processing
Unit is used to generate warning information according to the fire detector information and temperature parameter of the information acquisition unit；Fire extinguishing control
Unit is used to control fire extinguishing system according to the warning information and external command of the information process unit and put out a fire, and generates
Fire extinguishing information；Output unit is for exporting the warning information and the fire extinguishing information.
In one embodiment, the fireproof fire-extinguishing control system for aircraft engine of the application can also include certainly
Unit is examined, self-test unit includes startup self-check module, period selftest module and maintenance selftest module.Startup self-check module is used for
Each unit and external cabling are checked, alerted in time after noting abnormalities.Period selftest module is used for according to scheduled
Time interval is monitored each abnormal unit.Maintenance selftest module is for being checked and being tieed up according to ground maintenance instruction
Shield.
Further, information acquisition unit includes detector information acquisition module and temperature parameter acquisition module.Detector
Information acquisition module include multiple fire detectors and with the matched acquisition interface of fire detector.Fire detector is by practical
Requirement is arranged in engine region to be measured accordingly, for detecting the fire alarm information in region to be measured.Acquisition interface is for adopting
Collect the fire alarm information of engine region, and acquisition interface includes the location information where corresponding fire detector, it is fiery when occurring
When alert or line fault, current fire alarm information and location information are sent to information process unit.Temperature parameter acquisition module
For acquiring the temperature parameter of engine region.In the present embodiment, fire detector is respectively in enging cabin, the cabin APU, engine
Fancase and combustion box at least arrange one.Temperature parameter includes: temperature after engine intake temperature, gas turbine
Degree, oil temperature, engine compartment temperature etc..
Information process unit includes detector information processing module and temperature parameter processing module.Detector information processing
One or more fire alarm informations and location information of module pick-up probe information acquisition module, and to the fire alarm information received
And location information such as is filtered, compares at the data processings, generates alarm signal.Temperature parameter processing module is by the real-time of engine
Temperature is compared with the alarm threshold value of predetermined temperature, if predetermined period real time temperature is persistently higher than predetermined temperature, judges that engine loses
Fire generates alarm signal.When detector information processing module and temperature parameter processing module judge fire alarm occur, at information
It manages unit and generates warning information.
The decision logic whether information process unit catches fire to engine is as shown in the table (wherein, 0 to be indicated that fire does not occur
Alert, 1 indicates that fire alarm occurs):
| Detector information processing module | Engine parameter processing module | Working state of system |
| 0 | 0 | Normally |
| 0 | 1 | Normally |
| 1 | 0 | Normally |
| 1 | 1 | Fire alarm |
Fire extinguishing control unit includes operational module, and operational module can realize self-extinguishing by the manipulation of flight unit
The switching of mode and manual modes of fire suppression.Operational module includes control switch and indicator light, and control switch includes fire extinguishing control
Switch, fire-suppression bottle switch, left hair fire extinguishing switch, right hair fire extinguishing switch, APU fire extinguishing switch etc..Fire extinguishing control switch is for selecting
Modes of fire suppression, flight unit can switch automatic or manual mode according to actual needs and put out a fire.Aircraft equipped with main fire-suppression bottle and
Standby fire-suppression bottle, flight unit can operate fire-suppression bottle switch according to ignition point position and select main fire-suppression bottle or standby fire-suppression bottle.Left hair goes out
Fire switch, right hair fire extinguishing switch and APU fire extinguishing switch are put out a fire for left and right engine or APU.
Advantageously, each control switch is provided with indicator light, it is used to indicate the position of switch knob, vectored flight machine
Group operation.Preferably, put out a fire control switch, fire-suppression bottle switch is provided with green indicator light, be used to indicate fire extinguishing control switch,
The current location of fire-suppression bottle switch knob；Left hair fire extinguishing, the fire extinguishing of right hair and APU fire extinguishing switch are provided with red indicating light, work as hair
When fire alarm occurs for motivation or APU, corresponding red indicating light is ignited, for guiding flight unit operation fire extinguishing switch to go out
Fire.
Put out a fire control unit according to the warning information and external command of the information process unit control fire extinguishing system into
Row fire extinguishing procedure includes: when external command is self-extinguishing mode, and control unit of putting out a fire opens automatically according to the warning information
Dynamic fire extinguishing system is put out a fire；When external command is manual modes of fire suppression, operational module input is manually operated by flight unit
Fire extinguishing instruction is put out a fire.
In the fireproof fire-extinguishing control system for aircraft engine of the application, the outputting alarm information of output unit and
Fire extinguishing information includes: to airplane fault lamp and display outputting alarm information and fire extinguishing information, for reminding flight unit
It checks in time and makes disposition.
The fireproof fire-extinguishing control system for aircraft engine of the application passes through acquisition fire detector information and temperature
Parametric synthesis judges whether engine catches fire, and improves the reliability of fire detection, reduces false alarm rate；With self-extinguishing mould
Formula and manual modes of fire suppression both of which, substantially increase fire-fighting efficiency, reduce the working strength of flight unit.The application's
For the fireproof fire-extinguishing control system of aircraft engine, deficiency existing for traditional fire detection and fire extinguishing system is compensated for, it will be fiery
Police-spy surveys and is integrated in one with fire extinguishing, and by fire detector and temperature parameter information comprehensive descision fire alarm, has technology first
Into, false alarm rate is low, integration degree is high the features such as, be the following military secret, civil aircraft development direction and trend, have it is extensive and far-reaching
Application prospect.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of fireproof fire-extinguishing control system for aircraft engine characterized by comprising
Information acquisition unit, for acquiring fire detector information and temperature parameter；
Information process unit is alerted for being generated according to the fire detector information and temperature parameter of the information acquisition unit
Information；
Put out a fire control unit, for according to the warning information and external command of the information process unit control fire extinguishing system into
Row fire extinguishing, and generate fire extinguishing information；
Output unit, for exporting the warning information and the fire extinguishing information.
2. the fireproof fire-extinguishing control system according to claim 1 for aircraft engine, which is characterized in that further include:
Self-test unit, the self-test unit include startup self-check module, period selftest module and maintenance selftest module；
The startup self-check module alerts after noting abnormalities in time for checking each unit and external cabling；
The period selftest module, for being monitored at predetermined intervals to each abnormal unit；
The maintenance selftest module, for being checked and being safeguarded according to ground maintenance instruction.
3. the fireproof fire-extinguishing control system according to claim 1 for aircraft engine, which is characterized in that the information
Acquisition unit includes:
Detector information acquisition module, including fire detector and with the matched acquisition interface of fire detector, the fire alarm
Detector is used to detect the fire alarm information in region to be measured, and the acquisition interface is used to acquire the fire alarm information of engine region, and
The acquisition interface includes the location information where the corresponding fire detector, will when fire alarm or line fault occurs
Current fire alarm information and location information is sent to information process unit；
Temperature parameter acquisition module, for acquiring the temperature parameter of engine region.
4. the fireproof fire-extinguishing control system according to claim 3 for aircraft engine, which is characterized in that the fire alarm
Detector at least arranges one in enging cabin, the cabin APU, engine fan case and combustion box respectively.
5. the fireproof fire-extinguishing control system according to claim 3 for aircraft engine, which is characterized in that the temperature
Parameter includes: temperature, oil temperature, engine compartment temperature after engine intake temperature, gas turbine.
6. the fireproof fire-extinguishing control system according to claim 3 for aircraft engine, which is characterized in that the information
Processing unit includes:
Detector information processing module is believed for one or more fire alarm informations of pick-up probe information acquisition module and position
It ceases and is handled, generate alarm signal；
Temperature parameter processing module, by real time temperature compared with predetermined temperature, if predetermined period real time temperature be persistently higher than it is predetermined
Temperature judges engine fire, generates alarm signal；
When detector information processing module and temperature parameter processing module judge fire alarm occur, information process unit, which generates, is accused
Alert information.
7. the fireproof fire-extinguishing control system according to claim 6 for aircraft engine, which is characterized in that the fire extinguishing
Control unit includes:
Operational module, the operational module can realize self-extinguishing mode and manually fire extinguishing mould by the manipulation of flight unit
The switching of formula.
8. the fireproof fire-extinguishing control system according to claim 7 for aircraft engine, which is characterized in that the manipulation
Module includes control switch and indicator light, and the control switch includes fire extinguishing control switch, fire-suppression bottle switchs, the fire extinguishing of left hair is opened
It closes, right hair fire extinguishing switch, APU fire extinguishing switch, each control switch is provided with indicator light, is used to indicate the position of switch knob
It sets, vectored flight unit operation.
9. the fireproof fire-extinguishing control system according to claim 8 for aircraft engine, which is characterized in that the fire extinguishing
Control unit, carrying out fire extinguishing according to the warning information of the information process unit and external command control fire extinguishing system includes:
When external command is self-extinguishing mode, control unit of putting out a fire starts fire extinguishing system according to the warning information automatically
It puts out a fire；
When external command is manual modes of fire suppression, operational module input fire extinguishing instruction is manually operated by flight unit and is gone out
Fire.
10. the fireproof fire-extinguishing control system according to claim 9 for aircraft engine, which is characterized in that described defeated
Unit out, exports the warning information and the fire extinguishing information includes:
To airplane fault lamp and display outputting alarm information and fire extinguishing information.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811340614.9A CN109533348A (en) | 2018-11-12 | 2018-11-12 | A kind of fireproof fire-extinguishing control system for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811340614.9A CN109533348A (en) | 2018-11-12 | 2018-11-12 | A kind of fireproof fire-extinguishing control system for aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN109533348A true CN109533348A (en) | 2019-03-29 |
Family
ID=65846857
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|---|---|---|---|
| CN201811340614.9A Pending CN109533348A (en) | 2018-11-12 | 2018-11-12 | A kind of fireproof fire-extinguishing control system for aircraft engine |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110473377A (en) * | 2019-07-10 | 2019-11-19 | 芜湖市努尔航空信息科技有限公司 | A kind of intelligence aviation fire hazard monitoring system |
| CN110844092A (en) * | 2019-11-28 | 2020-02-28 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft fault warning method and system |
| WO2021077831A1 (en) * | 2019-10-21 | 2021-04-29 | 中车大连机车研究所有限公司 | Locomotive fire prevention and control system |
| CN112903299A (en) * | 2019-12-04 | 2021-06-04 | 中国航发商用航空发动机有限责任公司 | Aeroengine test bed and fire extinguishing method |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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Application publication date: 20190329 |
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