CN114229018B - Aircraft engine compartment fire detection system - Google Patents
Aircraft engine compartment fire detection system Download PDFInfo
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- CN114229018B CN114229018B CN202111614554.7A CN202111614554A CN114229018B CN 114229018 B CN114229018 B CN 114229018B CN 202111614554 A CN202111614554 A CN 202111614554A CN 114229018 B CN114229018 B CN 114229018B
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- 238000001514 detection method Methods 0.000 title claims abstract description 25
- 238000006243 chemical reaction Methods 0.000 claims description 68
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- 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
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- 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
- B64D2045/009—Fire detection or protection; Erosion protection, e.g. from airborne particles
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fire Alarms (AREA)
Abstract
The application belongs to the field of aeroengines, and particularly relates to an aircraft engine cabin fire detection system. The fire detectors in a single engine compartment are divided into two groups, and each group of 2 fire detectors which are arranged in parallel adopt a serial mode for fire alarm, so that the possibility of false alarm of a fire detection system caused by false alarm faults of the single fire detector is reduced, and the false alarm rate is reduced; the fire alarm detectors of the two groups are connected in parallel, so that the missing alarm is reduced, and the reliability of the fire alarm detection system is improved. The fire alarm in each engine compartment can be displayed in the aircraft cabin by a separate voice alarm and light alarm, and can be positioned to any engine compartment. The fault alarm of 4 fire detectors in each engine compartment adopts a parallel connection mode, and any fire detector fault can be displayed in the engine compartment through lamplight alarm. The fire alarm and fault information of each fire alarm detector are independently sent to a display control computer and a flight parameter system for recording.
Description
Technical Field
The application belongs to the field of aeroengines, and particularly relates to an aircraft engine cabin fire detection system.
Background
The fire disaster of the engine cabin of the aircraft seriously threatens the flight safety, and when the fire disaster happens in the engine cabin, the fire disaster can give an alarm to the unit timely and reliably. The engine compartment fire detection system is required to avoid missed warning and reduce false alarm rate. In a traditional single-loop fire alarm detection system, once a false alarm fault occurs in a fire alarm detector, the false fire alarm is easily generated, the burden of a crew is increased, and the flight task is influenced. The double-loop fire alarm detection system which carries out logic judgment through the electromechanical computer has higher requirements on the electromechanical management system of the aircraft.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide an aircraft engine compartment fire detection system that solves at least one of the problems of the prior art.
The technical scheme of the application is as follows:
an aircraft engine compartment fire detection system comprising:
the fire detector is provided with a fire signal output end and a fault signal output end, two groups of fire detectors are arranged in an engine compartment, each group comprises two fire detectors, namely a front group A of the fire detector, a front group B of the fire detector, a rear group A of the fire detector and a rear group B of the fire detector;
the signal conversion box is provided with a first conversion module, a second conversion module, a third conversion module and a fourth conversion module,
the input end of the first conversion module is respectively connected with the fire alarm signal output ends of the fire alarm detector front group A and the fire alarm detector front group B, and the first conversion module is a logic AND gate;
the input end of the second conversion module is respectively connected with the fire alarm signal output ends of the fire alarm detector rear group A and the fire alarm detector rear group B, and the second converter is a logic AND gate;
the input end of the third conversion module is respectively connected with the output ends of the first conversion module and the second conversion module, and the third conversion module is a logic OR gate;
the input end of the fourth conversion module is respectively connected with the fault signal output ends of the front fire detector group A, the front fire detector group B, the rear fire detector group A and the rear fire detector group B, and the fourth conversion module is a logic OR gate;
and the alarm system is connected with the output ends of the third conversion module and the fourth conversion module.
In at least one embodiment of the present application, the alarm system includes a voice alarm system and a light alarm system, where the voice alarm system is connected to the output end of the third conversion module, and the light alarm system is connected to the output ends of the third conversion module and the fourth conversion module, respectively.
In at least one embodiment of the present application, a display control computer is further included, and the display control computer is connected to the output ends of the third conversion module and the fourth conversion module respectively.
In at least one embodiment of the present application, the display control computer is connected to the front group of fire detectors a, the front group of fire detectors B, the rear group of fire detectors a, the rear group of fire detectors B, and the failure signal output end, respectively.
In at least one embodiment of the present application, the system further includes a flight parameter system, where the flight parameter system is connected to the output ends of the third conversion module and the fourth conversion module, respectively.
In at least one embodiment of the present application, the flight system is connected to the front group of fire detectors a, the front group of fire detectors B, the rear group of fire detectors a, the rear group of fire detectors B, and the failure signal output.
The application has at least the following beneficial technical effects:
according to the aircraft engine cabin fire alarm detection system, the fire alarm detectors are divided into two groups, each group of two fire alarm detectors form a double loop, and the fire alarm of the two groups of fire alarm detectors adopts OR logic, so that missed alarms can be reduced; the fire alarm of the single group of two fire detectors adopts AND logic, so that the false alarm rate can be effectively reduced.
Drawings
FIG. 1 is a schematic illustration of an aircraft engine compartment fire detection system according to one embodiment of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are illustrative and intended to explain the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present application.
The application is described in further detail below with reference to fig. 1.
The application provides a fire detection system of an aircraft engine cabin, which comprises the following components: fire detector, signal conversion box and alarm system.
Specifically, as shown in fig. 1, the fire detector is provided with a fire signal output end and a fault signal output end, in the application, two groups of fire detectors are arranged in an engine compartment, each group comprises two groups, namely a front fire detector group A, a front fire detector group B, a rear fire detector group A and a rear fire detector group B, the front fire detector group A and the front fire detector group B are arranged side by side in the engine compartment, and the rear fire detector group A and the rear fire detector group B are arranged side by side in the engine compartment.
The signal conversion box is internally provided with a first conversion module, a second conversion module, a third conversion module and a fourth conversion module, wherein the input end of the first conversion module is respectively connected with the fire alarm signal output ends of the fire alarm detector front group A and the fire alarm detector front group B, and the first conversion module is a logic AND gate; the input end of the second conversion module is respectively connected with the fire alarm signal output ends of the fire alarm detector rear group A and the fire alarm detector rear group B, and the second converter is a logic AND gate; the input end of the third conversion module is respectively connected with the output ends of the first conversion module and the second conversion module, and the third conversion module is a logic OR gate; the input end of the fourth conversion module is respectively connected with fault signal output ends of the front fire detector group A, the front fire detector group B, the rear fire detector group A and the rear fire detector group B, and the fourth conversion module is a logic OR gate. According to the fire alarm detection system of the aircraft engine cabin, each group A, B of fire alarm signals of two fire alarm detectors adopts AND logic, the fire alarm signals of the front group and the rear group adopt OR logic, the fault alarm signals of 4 fire alarm detectors adopt OR logic, and the system logic design is realized through a relay box, a switch and an electric circuit, so that the requirements on the electromechanical management system of the aircraft are low.
Further, the alarm system is connected with the output ends of the third conversion module and the fourth conversion module. It will be appreciated that the fire alarm signal and the fault signal may alert the crew in a variety of ways. In one embodiment of the application, the alarm system comprises a voice alarm system and a light alarm system, wherein the voice alarm system is connected with the output end of the third conversion module, and the light alarm system is respectively connected with the output ends of the third conversion module and the fourth conversion module. In this embodiment, the system further includes a display control computer and a flight parameter system, the display control computer is respectively connected with the output ends of the third conversion module and the fourth conversion module, the flight parameter system is respectively connected with the output ends of the third conversion module and the fourth conversion module, and in addition, the display control computer and the flight parameter system are also respectively connected with the fire alarm signal output ends and the fault signal output ends of the fire alarm detector front group A, the fire alarm detector front group B, the fire alarm detector rear group A and the fire alarm detector rear group B. In this embodiment, the fire alarm signal can send out the warning to the crew through multiple modes such as voice alarm system, light alarm system, head-up display, and the like, and the fault signal can be shown through modes such as light alarm, head-up display, and in addition, the fire alarm signal, the fault signal of every fire alarm detector can all be through showing accuse computer and flight system and record.
According to the fire detection system of the aircraft engine compartment, the fire detectors in the single engine compartment are divided into two groups, and each group of 2 fire detectors which are arranged in parallel adopt a serial mode for fire alarm, so that the possibility of false alarm of the fire detection system caused by false alarm fault of the single fire detector is reduced, and the false alarm rate is reduced; the fire alarm detectors of the two groups are connected in parallel, so that the missing alarm is reduced, and the reliability of the fire alarm detection system is improved. The fire alarm in each engine compartment can be displayed in the aircraft cabin by a separate voice alarm and light alarm, and can be positioned to any engine compartment. The fault alarm of 4 fire detectors in each engine compartment adopts a parallel connection mode, and any fire detector fault can be displayed in the engine compartment through lamplight alarm. The fire alarm and fault information of each fire alarm detector are independently sent to a display control computer and a flight parameter system for recording.
The aircraft engine cabin fire alarm detection system is easy to realize, has obvious effect, can effectively reduce fire alarm omission and false alarm, reduces the requirements on control of an on-board core computer, improves the reliability of the system, and reduces the cost of the system.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. An aircraft engine compartment fire detection system, comprising:
the fire detector is provided with a fire signal output end and a fault signal output end, two groups of fire detectors are arranged in an engine compartment, each group comprises two fire detectors, namely a front group A of the fire detector, a front group B of the fire detector, a rear group A of the fire detector and a rear group B of the fire detector;
the signal conversion box is provided with a first conversion module, a second conversion module, a third conversion module and a fourth conversion module,
the input end of the first conversion module is respectively connected with the fire alarm signal output ends of the fire alarm detector front group A and the fire alarm detector front group B, and the first conversion module is a logic AND gate;
the input end of the second conversion module is respectively connected with the fire alarm signal output ends of the fire alarm detector rear group A and the fire alarm detector rear group B, and the second conversion module is a logic AND gate;
the input end of the third conversion module is respectively connected with the output ends of the first conversion module and the second conversion module, and the third conversion module is a logic OR gate;
the input end of the fourth conversion module is respectively connected with the fault signal output ends of the front fire detector group A, the front fire detector group B, the rear fire detector group A and the rear fire detector group B, and the fourth conversion module is a logic OR gate;
and the alarm system is connected with the output ends of the third conversion module and the fourth conversion module.
2. The aircraft engine compartment fire detection system of claim 1, wherein the warning system comprises a voice warning system and a light warning system, wherein the voice warning system is connected to an output of the third conversion module and the light warning system is connected to outputs of the third and fourth conversion modules, respectively.
3. The aircraft engine compartment fire detection system of claim 2, further comprising a display and control computer connected to the outputs of the third and fourth conversion modules, respectively.
4. The aircraft engine compartment fire detection system of claim 3, wherein the display and control computer is respectively connected with the fire signal output ends and the fault signal output ends of the fire detector front group a, the fire detector front group B, the fire detector rear group a and the fire detector rear group B.
5. The aircraft engine compartment fire detection system of claim 4, further comprising a flight system connected to outputs of the third and fourth conversion modules, respectively.
6. The aircraft engine compartment fire detection system of claim 5, wherein the flight system is connected to the fire signal output and the fault signal output of the front fire detector set a, the front fire detector set B, the rear fire detector set a, and the rear fire detector set B, respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111614554.7A CN114229018B (en) | 2021-12-27 | 2021-12-27 | Aircraft engine compartment fire detection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111614554.7A CN114229018B (en) | 2021-12-27 | 2021-12-27 | Aircraft engine compartment fire detection system |
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| Publication Number | Publication Date |
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| CN114229018A CN114229018A (en) | 2022-03-25 |
| CN114229018B true CN114229018B (en) | 2023-08-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111614554.7A Active CN114229018B (en) | 2021-12-27 | 2021-12-27 | Aircraft engine compartment fire detection system |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115565328A (en) * | 2022-10-11 | 2023-01-03 | 中国航空工业集团公司西安飞机设计研究所 | Cabin smoke detection method and device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104700547A (en) * | 2014-07-11 | 2015-06-10 | 成都飞亚航空设备应用研究所有限公司 | Fire early warning device for aircraft engine |
| CN106205012A (en) * | 2015-05-04 | 2016-12-07 | 中国航空工业集团公司西安飞机设计研究所 | A kind of three bellows pneumatic type fire-detecting system alarm logic design methods |
| US9988160B1 (en) * | 2017-05-04 | 2018-06-05 | The Boeing Company | Airplane fire detection system |
| CN113525700A (en) * | 2020-04-15 | 2021-10-22 | 桂林航天工业学院 | Health monitoring system for single-machine structure of airplane |
-
2021
- 2021-12-27 CN CN202111614554.7A patent/CN114229018B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104700547A (en) * | 2014-07-11 | 2015-06-10 | 成都飞亚航空设备应用研究所有限公司 | Fire early warning device for aircraft engine |
| CN106205012A (en) * | 2015-05-04 | 2016-12-07 | 中国航空工业集团公司西安飞机设计研究所 | A kind of three bellows pneumatic type fire-detecting system alarm logic design methods |
| US9988160B1 (en) * | 2017-05-04 | 2018-06-05 | The Boeing Company | Airplane fire detection system |
| CN113525700A (en) * | 2020-04-15 | 2021-10-22 | 桂林航天工业学院 | Health monitoring system for single-machine structure of airplane |
Non-Patent Citations (1)
| Title |
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| 飞机发动机舱火警探测系统改进研究;尹梅莉;田永堂;;航空科学技术(第12期);39-42 * |
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