CN209785199U - Fire alarm detection device for aircraft engine compartment - Google Patents
Fire alarm detection device for aircraft engine compartment Download PDFInfo
- Publication number
- CN209785199U CN209785199U CN201920667689.1U CN201920667689U CN209785199U CN 209785199 U CN209785199 U CN 209785199U CN 201920667689 U CN201920667689 U CN 201920667689U CN 209785199 U CN209785199 U CN 209785199U
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- relay
- triode
- resistor
- detection circuit
- box body
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Abstract
The utility model relates to an aircraft engine cabin fire alarm detection device, including the inside box body that is the accommodation space, be connected the apron that forms the closing cap to the accommodation space in the box body with the box body, install the detection circuit board that has detection circuit in the accommodation space, one side at the box body is equipped with the wiring plug that supplies detection circuit wiring in the detection circuit board, detection circuit includes DC power supply input, triode Q1, triode Q2, triode Q3, relay K1, relay K2, light sense resistance, relay K1 is the single-pole double throw, relay K2 is the double-pole double throw; in a normal working state, the triode Q3 and the relay K2 work, the triode Q2 and the relay K1 do not work, and a fault signal and a fire alarm signal are not output. When a fire alarm signal exists, the triode Q2 and the relay K1 work to output the fire alarm signal, and the external fire indicator lamp is lightened. The utility model discloses can inspect the fire alarm condition in the engine compartment to in time show, in order to remind aircraft pilot, promote the safety of taking advantage of aircraft.
Description
Technical Field
The utility model relates to an aircraft engine cabin fire alarm detection device.
Background
in the use process of an aircraft engine, the conditions of abrasion, fuel leakage, electrical short circuit and the like of engine parts can occur, fire alarms can be generated in an engine compartment under the conditions, if the conditions are not monitored, the engine is easily damaged, and the flight safety is directly endangered.
SUMMERY OF THE UTILITY MODEL
In view of the above, it is an object of the present invention to provide an aircraft engine compartment fire detection device that can detect a fire in the engine compartment.
Realize the technical scheme of the utility model as follows
The fire alarm detection device for the aircraft engine cabin comprises a box body, a cover plate, a detection circuit board, a detection circuit and a light sensing resistor, wherein the box body is internally provided with a containing space, the cover plate is connected with the box body and forms a sealing cover for the containing space in the box body, the detection circuit board is provided with the detection circuit board, one side of the box body is provided with a wiring plug for wiring the detection circuit board, the detection circuit comprises a direct current power supply input, a triode Q1, a triode Q2, a triode Q3, a relay K1, a relay K2 and a light sensing resistor, the relay K1 is single-pole double-throw, the relay K2 is double-pole double-throw, one end of the direct current power supply input is connected with a first base point of the relay K2, the other end of a first normally closed contact of the relay K2 is connected out through a conductor and serves as a signal output terminal I, the other end of the direct current power supply input is connected in parallel with a coil of the, a normally open contact of the relay K1 is connected out through a wire and serves as a signal output terminal II, one end of a light sensing resistor is connected with a base electrode of a triode Q1, an emitting electrode of a triode Q2 and an emitting electrode of a triode Q3 in parallel, the other end of the light sensing resistor is connected with the emitting electrode of a triode Q1, the other end of the light sensing resistor is connected with a resistor R1 and a voltage stabilizing diode D1 in parallel, a resistor R1 is connected between the other end of the direct-current power supply input end and a coil of the relay K1, a voltage stabilizing diode D1 is grounded, a collector electrode of a triode Q1 is connected with the base electrode of a triode Q2, the base electrode of a triode Q1, the emitting electrode of a triode Q2 and the emitting electrode of a triode Q3 are grounded after being connected in parallel, the collector electrode of the triode Q2 is connected with a; the resistor R2 is connected with one end of the light sensing resistor, and the collector of the triode Q3 is connected with the coil of the relay K2; indicator lights are respectively connected between the first signal output terminal and the ground and between the second signal output terminal and the ground.
furthermore, after one end of the light sensing resistor is connected with the resistor R2 in parallel, the light sensing resistor is connected with the diode D2 and the resistor R6 in series, the resistor R6 is grounded, the base of the triode Q1 is connected with the resistor R5 and the capacitor C1 in series, the capacitor C1 is grounded, and the diode D2 and the resistor R6 are connected with the resistor R5 and the capacitor C1 through wires.
Further, an emitter of the transistor Q1 is connected in series with a diode D3, and a resistor R4 is connected in series between a collector of the transistor Q1 and a base of the transistor Q2.
By adopting the technical scheme, in a normal working state, the triode Q3 and the relay K2 work, the triode Q2 and the relay K1 do not work, and a fault signal and a fire alarm signal are not output. When a fire alarm signal exists, the triode Q2 and the relay K1 work to output the fire alarm signal, and the external fire indicator lamp is lightened. When the external control switch is placed in a test state, a fire alarm signal is simulated to be input, the triode Q2 and the relay K1 work to output a fire alarm signal, and the external fire indicator lamp is lightened. When power supply is abnormal or the internal circuit is in fault, the relay K2 does not work, a fault signal is output, and an external fault indicator lamp is lightened. The utility model discloses can inspect the fire alarm condition in the engine compartment to in time show, in order to remind aircraft pilot, promote the safety of taking advantage of aircraft.
drawings
Fig. 1 is a schematic structural view of the present invention;
Fig. 2 is a schematic diagram of the connection between the probing circuit board and the plug of the present invention;
Fig. 3 is a circuit diagram of the middle detection circuit of the present invention.
Detailed Description
In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the drawings of the embodiments of the present invention are combined below to clearly and completely describe the technical solution of the embodiments of the present invention. It is to be understood that the embodiments described are only some of the embodiments of the present invention, and not all of them. All other embodiments, which can be obtained by a person skilled in the art without any inventive work based on the described embodiments of the present invention, belong to the protection scope of the present invention.
Referring to fig. 1, 2 and 3, the fire alarm detection device for the aircraft engine cabin comprises a box body 1 with a square accommodating space inside, mounting plates 2 with mounting holes are bent outwards on two sides of the box body, a cover plate 3 which is connected with the box body and forms a sealing cover for the accommodating space in the box body is connected with the box body, the cover plate is mounted on the box body by inserting screws into the mounting holes, a detection circuit board 4 with a detection circuit is mounted in the accommodating space, the detection circuit board is horizontally arranged in the accommodating space, and four corners are connected in the box body through screws; the connection plug 5 for the detection circuit connection in the detection circuit board is arranged on one side of the box body, namely, an assembly opening is arranged on one side of the box body for the insertion assembly of the connection plug.
The detection circuit comprises a direct current power supply input, a triode Q1, a triode Q2, a triode Q3 and a relay K1, the relay K2, light sense resistor, relay K1 is single-pole double-throw, relay K2 is double-pole double-throw, the one end of DC power supply input is connected with the first base point of relay K2, the other end conductor of the first normally closed contact of relay K2 is connected out, as signal output terminal I, the other end of DC power supply input and relay K1 base point, relay K1 coil, relay K2 coil form and connect in parallel, relay K1 coil and relay K2 second base point are connected, relay K1 normally open contact is connected out through the wire, as signal output terminal II, be connected with the pilot lamp between signal output terminal I and the ground, be connected with the pilot lamp between signal output terminal II and the ground respectively, the pilot lamp is installed in the aircraft cockpit, so that the pilot can observe.
One end of the light sensing resistor is connected with a base electrode of a triode Q1, an emitter electrode of a triode Q2 and an emitter electrode of a triode Q3 in parallel, the other end of the light sensing resistor is connected with an emitter electrode of a triode Q1, the other end of the light sensing resistor is connected with a resistor R1 and a voltage stabilizing diode D1 in parallel between the other end of the light sensing resistor and an emitter electrode of a triode Q1, the resistor R1 is connected between the other end of the direct current power supply input end and a coil of a relay K1, the voltage stabilizing diode D1 is grounded, a collector electrode of the triode Q1 is connected with a base electrode of a triode Q2, a base electrode of a triode Q1, an emitter electrode of a triode Q2 and an emitter electrode of a triode Q3 are connected with the ground after being connected with the; the resistor R2 is connected with one end of the light sensing resistor, and the collector of the triode Q3 is connected with the coil of the relay K2.
One end of the light sensing resistor is connected in parallel with the resistor R2 and then connected in series with the diode D2 and the resistor R6, the resistor R6 is grounded, the base of the triode Q1 is connected in series with the resistor R5 and the capacitor C1, the capacitor C1 is grounded, and the diode D2 and the resistor R6 are connected with the resistor R5 and the capacitor C1 through leads. The emitting electrode of the triode Q1 is connected in series with a diode D3, and a resistor R4 is connected between the collector electrode of the triode Q1 and the base electrode of the triode Q2.
The utility model discloses a wiring and theory of operation as follows:
1. The pins 13 and 25 of the wiring plug are externally connected with a flame detector (light-sensitive resistor) and a control switch.
2. the pins 9 and 12 of the wiring plug are externally connected with a 28V power supply, and the pin 20 is grounded.
3. And the No. 10 and No. 11 pins of the wiring plug are externally connected with indicator lamps and respectively output fault signals and fire alarm signals.
4. in a normal working state, the triode Q3 and the relay K2 work, the triode Q2 and the relay K1 do not work, and a fault signal and a fire alarm signal are not output.
5. When a fire alarm signal exists, the triode Q2 and the relay K1 work to output the fire alarm signal, and the external fire indicator lamp is lightened.
6. When the external control switch is placed in a test state, a fire alarm signal is simulated to be input, the triode Q2 and the relay K1 work to output a fire alarm signal, and the external fire indicator lamp is lightened.
7. When power supply is abnormal or the internal circuit is in fault, the relay K2 does not work, a fault signal is output, and an external fault indicator lamp is lightened.
Claims (3)
1. The fire alarm detection device for the aircraft engine compartment is characterized by comprising a box body, a cover plate, a detection circuit board, a wiring plug and a control circuit, wherein the box body is internally provided with a containing space, the cover plate is connected with the box body and forms a sealing cover for the containing space in the box body, the detection circuit board with a detection circuit is arranged in the containing space, one side of the box body is provided with the wiring plug for wiring the detection circuit in the detection circuit board,
The detection circuit comprises a direct current power supply input, a triode Q1, a triode Q2, a triode Q3, a relay K1, a relay K2 and a light sensing resistor,
The relay K1 is single-pole double-throw relay K2 is double-pole double-throw relay K,
One end of the direct current power supply input is connected with a first base point of a relay K2, the other end conductor of a first normally closed contact of the relay K2 is connected out to be used as a signal output terminal I,
the other end of the direct current power supply input is connected in parallel with a relay K1 base point, a relay K1 coil and a relay K2 coil, the relay K1 coil is connected with a second base point of the relay K2, a normally open contact of the relay K1 is connected out through a lead to serve as a signal output terminal II,
One end of the light sensing resistor is connected with the base electrode of the triode Q1, the emitter electrode of the triode Q2 and the emitter electrode of the triode Q3 in parallel, the other end of the light sensing resistor is connected with the emitter electrode of the triode Q1, the other end of the light sensing resistor and the emitter electrode of the triode Q1 are connected with the resistor R1 and the voltage stabilizing diode D1 in parallel, the resistor R1 is connected between the other end of the direct-current power supply input and the coil of the relay K1, the voltage stabilizing diode D1,
The collector of the transistor Q1 is connected with the base of the transistor Q2,
the base electrode of the triode Q1, the emitter electrode of the triode Q2 and the emitter electrode of the triode Q3 are grounded after being connected in parallel,
a collector of the triode Q2 is connected with a second normally open contact of the relay K2, a base of the triode Q3 is connected with a resistor R2 and a resistor R3 in parallel, and a resistor R3 is grounded; the resistor R2 is connected to one end of the light sensing resistor,
the collector of the triode Q3 is connected with the coil of the relay K2;
indicator lights are respectively connected between the first signal output terminal and the ground and between the second signal output terminal and the ground.
2. The fire detector as claimed in claim 1, wherein the light sensing resistor is connected in series with a diode D2 and a resistor R6 after being connected in parallel with a resistor R2, the resistor R6 is grounded, the base of the transistor Q1 is connected in series with a resistor R5 and a capacitor C1, the capacitor C1 is grounded, and the diode D2 and the resistor R6 are connected with the resistor R5 and the capacitor C1 by wires.
3. an aircraft engine compartment fire alarm detection device as claimed in claim 1, wherein a diode D3 is connected in series with the emitter of the transistor Q1, and a resistor R4 is connected in series between the collector of the transistor Q1 and the base of the transistor Q2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920667689.1U CN209785199U (en) | 2019-05-10 | 2019-05-10 | Fire alarm detection device for aircraft engine compartment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920667689.1U CN209785199U (en) | 2019-05-10 | 2019-05-10 | Fire alarm detection device for aircraft engine compartment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209785199U true CN209785199U (en) | 2019-12-13 |
Family
ID=68805230
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920667689.1U Expired - Fee Related CN209785199U (en) | 2019-05-10 | 2019-05-10 | Fire alarm detection device for aircraft engine compartment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209785199U (en) |
-
2019
- 2019-05-10 CN CN201920667689.1U patent/CN209785199U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191213 Termination date: 20210510 |