CN103204239A - Alarming circuit for overtime faults of emergent extension of airplane undercarriage - Google Patents
Alarming circuit for overtime faults of emergent extension of airplane undercarriage Download PDFInfo
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- CN103204239A CN103204239A CN2013101453803A CN201310145380A CN103204239A CN 103204239 A CN103204239 A CN 103204239A CN 2013101453803 A CN2013101453803 A CN 2013101453803A CN 201310145380 A CN201310145380 A CN 201310145380A CN 103204239 A CN103204239 A CN 103204239A
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- photoelectric commutator
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Abstract
The invention belongs to a technology for controlling an airplane undercarriage and relates to an alarming circuit for overtime faults of emergent extension of the airplane undercarriage. The alarming circuit is characterized by comprising an emergent-extension signal conditioning circuit (1), a time delay circuit (2) and an alarming output circuit (3). The alarming circuit provided by the invention has the advantage that the safety of airplane landing is improved.
Description
Technical field
The invention belongs to the undercarriage control technology, relate to that a kind of undercarriage is emergent puts overtime failure alarm circuit.
Background technology
When aircraft is prepared to land, need first drop, the alighting gear state is indicated with indicator lamp, and viewing lamp just can determine whether alighting gear puts down.When alighting gear can not normally put down, the aviator started the emergent program of putting of alighting gear.So-called alighting gear is emergent to be put overtime fault and refer to: do not make gear down also lockedly in the scope in normal time, at this moment, undercarriage is emergent to be put overtime failure alarm circuit and should provide alerting signal, reminds the aviator to take measures, to guarantee safety.Do not retrieve the emergent open source literature of putting overtime failure alarm circuit of relevant undercarriage both at home and abroad.
Summary of the invention
The objective of the invention is: propose that a kind of undercarriage is emergent puts overtime failure alarm circuit, to increase the safety of aircraft landing.
Technical scheme of the present invention is: undercarriage is emergent puts overtime failure alarm circuit, it is characterized in that it is made up of emergent discharge signal modulate circuit 1, time delay circuit 2 and warning output circuit 3; Emergent discharge signal modulate circuit 1 is made up of normally open push button switch K, resistance R 1 and R2, the first photoelectric commutator U1 or door U4 and joint denial gate U5; Be connected with the input end of the first photoelectric commutator U1 behind the first contact Ka series resistance R1 of normally open push button switch K, the input grounding end ground connection of the first photoelectric commutator U1, the second contact Kb of normally open push button switch K is connected with positive 24V, the mouth of the first photoelectric commutator U1 with or the door U4 first input end U4a be connected, the output ground terminal ground connection of the first photoelectric commutator U1, resistance R 2 be connected positive 5V and or the door U4 first input end U4a between, or the second input end U4b of door U4 is connected with the down lock status signal mouth of undercarriage, or the mouth AND OR NOT gate U5 second input end U5b of U4 connection; Time delay circuit 2 is made up of resistance R 3 and R5, compound NPN aerotron G, diode D and the J of slug relay; Resistance R 3 is connected between the base stage of the mouth of joint denial gate U5 and compound NPN aerotron G, the grounded emitter of compound NPN aerotron G, the collecting electrode of compound NPN aerotron G is connected with the positive pole of diode D and an end of the J of slug relay coil respectively, the negative pole of diode D meets positive 24V, the positive 24V of another termination of the J of slug relay coil, the moving contact of the J of slug relay meets positive 24V, the normally closed contact Ja of the J of slug relay connects an end of run signal lamp, and the open contact Jb of the J of slug relay is connected with an end of resistance R 5; Warning output circuit 3 is made up of the second photoelectric commutator U2, resistance R 6 and not gate U6; The other end of resistance R 5 is connected with the input end of the second photoelectric commutator U2, the input grounding end ground connection of the second photoelectric commutator U2, the input end of the mouth difference NAND gate U6 of the second photoelectric commutator U2 and an end of resistance R 6 are connected, the positive 5V of another termination of resistance R 6, the output ground terminal ground connection of the second photoelectric commutator U2, the mouth output alighting gear of not gate U6 is met an urgent need and is put overtime failure alarm signal, and the mouth AND OR NOT gate U5 first input end U5a of not gate U6 connects.
Advantage of the present invention is: proposed that a kind of undercarriage is emergent puts overtime failure alarm circuit, increased the safety of aircraft landing.
Description of drawings
Fig. 1 is schematic circuit diagram of the present invention.
The specific embodiment
Below the present invention is described in further details.Referring to Fig. 1, undercarriage is emergent puts overtime failure alarm circuit, it is characterized in that it is made up of emergent discharge signal modulate circuit 1, time delay circuit 2 and warning output circuit 3; Emergent discharge signal modulate circuit 1 is made up of normally open push button switch K, resistance R 1 and R2, the first photoelectric commutator U1 or door U4 and joint denial gate U5; Be connected with the input end of the first photoelectric commutator U1 behind the first contact Ka series resistance R1 of normally open push button switch K, the input grounding end ground connection of the first photoelectric commutator U1, the second contact Kb of normally open push button switch K is connected with positive 24V, the mouth of the first photoelectric commutator U1 with or the door U4 first input end U4a be connected, the output ground terminal ground connection of the first photoelectric commutator U1, resistance R 2 be connected positive 5V and or the door U4 first input end U4a between, or the second input end U4b of door U4 is connected with the down lock status signal mouth of undercarriage, or the mouth AND OR NOT gate U5 second input end U5b of U4 connection; Time delay circuit 2 is made up of resistance R 3 and R5, compound NPN aerotron G, diode D and the J of slug relay; Resistance R 3 is connected between the base stage of the mouth of joint denial gate U5 and compound NPN aerotron G, the grounded emitter of compound NPN aerotron G, the collecting electrode of compound NPN aerotron G is connected with the positive pole of diode D and an end of the J of slug relay coil respectively, the negative pole of diode D meets positive 24V, the positive 24V of another termination of the J of slug relay coil, the moving contact of the J of slug relay meets positive 24V, the normally closed contact Ja of the J of slug relay connects an end of run signal lamp, and the open contact Jb of the J of slug relay is connected with an end of resistance R 5; Warning output circuit 3 is made up of the second photoelectric commutator U2, resistance R 6 and not gate U6; The other end of resistance R 5 is connected with the input end of the second photoelectric commutator U2, the input grounding end ground connection of the second photoelectric commutator U2, the input end of the mouth difference NAND gate U6 of the second photoelectric commutator U2 and an end of resistance R 6 are connected, the positive 5V of another termination of resistance R 6, the output ground terminal ground connection of the second photoelectric commutator U2, the mouth output alighting gear of not gate U6 is met an urgent need and is put overtime failure alarm signal, and the mouth AND OR NOT gate U5 first input end U5a of not gate U6 connects.
Principle of work of the present invention is: when normally open push button switch K is not closed, the first contact Ka no signal of normally open push button switch K, the mouth of the first photoelectric commutator U1 and not conducting of ground terminal, the mouth of the first photoelectric commutator U1 is output as high level, then or the door U4 be output as high level, joint denial gate U5 is output as low level, not conducting of compound NPN aerotron G, then not conducting of the J of slug relay coil, the moving contact attonity of the J of slug relay, the mouth of the second photoelectric commutator U2 and not conducting of ground terminal, the mouth of the second photoelectric commutator U2 is output as high level, then not gate U6 is output as low level, does not namely have breakdown signal output.
When normally open push button switch K is closed, first contact of normally open push button switch K is connected with positive 24V, the mouth of the first photoelectric commutator U1 and ground terminal conducting, the mouth of the first photoelectric commutator U1 is output as low level, then or the door U4 first input end U4a be input as low level, if the alighting gear down lock is locked, or the door U4 the second input end U4b be input as high level, then or a door U4 be output as high level, then do not have breakdown signal output.
If the alighting gear down lock is not locked, or the second input end U4b of door U4 is input as low level, then or the door U4 be output as low level, the joint denial gate U5 second input end U5b is low level, when alerting signal not occurring, be that joint denial gate U5 first input end U5a is low level, joint denial gate U5 is output as high level, compound NPN aerotron G conducting, the then J of slug relay coil conducting, the J of slug relay just can move after waiting for the time that has arranged, if the alighting gear down lock is locked during this period, then the J of slug relay returns to normal, if the alighting gear down lock is not locked during this period, and the then moving contact of the J of slug relay action, the mouth of the second photoelectric commutator U2 and ground terminal conducting, the mouth of the second photoelectric commutator U2 is output as low level, and then not gate U6 is output as high level, and breakdown signal output is namely arranged; Breakdown signal be high level then joint denial gate U5 first input end U5a be high level, according to above principle then breakdown signal revert to low level, namely Shu Chu breakdown signal is transient signal, carries out latching of breakdown signal by subsequent conditioning circuit.
In one embodiment of the present of invention, photoelectric commutator or door, joint denial gate, compound NPN aerotron, not gate and slug relay all adopt commercially available finished parts.Photoelectric commutator be TLP521 or door for 74LS32, joint denial gate be that 74LS02, compound NPN aerotron are 62083, not gate is that 74LS04, slug relay are H3Y-2.
Claims (1)
1. undercarriage is emergent puts overtime failure alarm circuit, it is characterized in that it is made up of emergent discharge signal modulate circuit (1), time delay circuit (2) and warning output circuit (3); Emergent discharge signal modulate circuit (1) is made up of normally open push button switch K, resistance R 1 and R2, the first photoelectric commutator U1 or door U4 and joint denial gate U5; Be connected with the input end of the first photoelectric commutator U1 behind the first contact Ka series resistance R1 of normally open push button switch K, the input grounding end ground connection of the first photoelectric commutator U1, the second contact Kb of normally open push button switch K is connected with positive 24V, the mouth of the first photoelectric commutator U1 with or the door U4 first input end U4a be connected, the output ground terminal ground connection of the first photoelectric commutator U1, resistance R 2 be connected positive 5V and or the door U4 first input end U4a between, or the second input end U4b of door U4 is connected with the down lock status signal mouth of undercarriage, or the mouth AND OR NOT gate U5 second input end U5b of U4 connection; Time delay circuit (2) is made up of resistance R 3 and R5, compound NPN aerotron G, diode D and the J of slug relay; Resistance R 3 is connected between the base stage of the mouth of joint denial gate U5 and compound NPN aerotron G, the grounded emitter of compound NPN aerotron G, the collecting electrode of compound NPN aerotron G is connected with the positive pole of diode D and an end of the J of slug relay coil respectively, the negative pole of diode D meets positive 24V, the positive 24V of another termination of the J of slug relay coil, the moving contact of the J of slug relay meets positive 24V, the normally closed contact Ja of the J of slug relay connects an end of run signal lamp, and the open contact Jb of the J of slug relay is connected with an end of resistance R 5; Warning output circuit (3) is made up of the second photoelectric commutator U2, resistance R 6 and not gate U6; The other end of resistance R 5 is connected with the input end of the second photoelectric commutator U2, the input grounding end ground connection of the second photoelectric commutator U2, the input end of the mouth difference NAND gate U6 of the second photoelectric commutator U2 and an end of resistance R 6 are connected, the positive 5V of another termination of resistance R 6, the output ground terminal ground connection of the second photoelectric commutator U2, the mouth output alighting gear of not gate U6 is met an urgent need and is put overtime failure alarm signal, and the mouth AND OR NOT gate U5 first input end U5a of not gate U6 connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310145380.3A CN103204239B (en) | 2013-04-24 | 2013-04-24 | Alarming circuit for overtime faults of emergent extension of airplane undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310145380.3A CN103204239B (en) | 2013-04-24 | 2013-04-24 | Alarming circuit for overtime faults of emergent extension of airplane undercarriage |
Publications (2)
| Publication Number | Publication Date |
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| CN103204239A true CN103204239A (en) | 2013-07-17 |
| CN103204239B CN103204239B (en) | 2015-04-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310145380.3A Expired - Fee Related CN103204239B (en) | 2013-04-24 | 2013-04-24 | Alarming circuit for overtime faults of emergent extension of airplane undercarriage |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104533617A (en) * | 2014-11-14 | 2015-04-22 | 中航飞机股份有限公司西安飞机分公司 | Protecting device for engine of turboprop aircraft |
| CN105083541A (en) * | 2015-09-14 | 2015-11-25 | 江西洪都航空工业集团有限责任公司 | Monitoring method for preventing airplane landing gear from being not locked during landing |
| CN107000832A (en) * | 2017-01-19 | 2017-08-01 | 深圳市大疆创新科技有限公司 | Unmanned plane undercarriage control method, device, unmanned plane and its system |
| CN108502145A (en) * | 2017-02-24 | 2018-09-07 | 赛峰起落架系统公司 | Emergency extension system for landing gear of aircraft |
| GB2569354A (en) * | 2017-12-14 | 2019-06-19 | Airbus Operations Ltd | Landing gear controller |
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| CN1164496A (en) * | 1996-03-12 | 1997-11-12 | 起重机公司液压气压分部 | Monitor for uncommanded braking |
| US6311927B1 (en) * | 2000-07-11 | 2001-11-06 | Lockheed Martin Corporation | Emergency landing gear extension system using pyrotechnic operated high pressure bottle |
| CN102508028A (en) * | 2011-10-10 | 2012-06-20 | 江苏科技大学 | Device and method for detecting and analyzing harmonic |
| CN102530244A (en) * | 2012-02-14 | 2012-07-04 | 南京航空航天大学 | All-electric retractable actuator cylinder suitable for laying landing gear down emergently and operating mode thereof |
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2013
- 2013-04-24 CN CN201310145380.3A patent/CN103204239B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1164496A (en) * | 1996-03-12 | 1997-11-12 | 起重机公司液压气压分部 | Monitor for uncommanded braking |
| US6311927B1 (en) * | 2000-07-11 | 2001-11-06 | Lockheed Martin Corporation | Emergency landing gear extension system using pyrotechnic operated high pressure bottle |
| CN102508028A (en) * | 2011-10-10 | 2012-06-20 | 江苏科技大学 | Device and method for detecting and analyzing harmonic |
| CN102530244A (en) * | 2012-02-14 | 2012-07-04 | 南京航空航天大学 | All-electric retractable actuator cylinder suitable for laying landing gear down emergently and operating mode thereof |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104533617A (en) * | 2014-11-14 | 2015-04-22 | 中航飞机股份有限公司西安飞机分公司 | Protecting device for engine of turboprop aircraft |
| CN105083541A (en) * | 2015-09-14 | 2015-11-25 | 江西洪都航空工业集团有限责任公司 | Monitoring method for preventing airplane landing gear from being not locked during landing |
| CN107000832A (en) * | 2017-01-19 | 2017-08-01 | 深圳市大疆创新科技有限公司 | Unmanned plane undercarriage control method, device, unmanned plane and its system |
| WO2018133006A1 (en) * | 2017-01-19 | 2018-07-26 | 深圳市大疆创新科技有限公司 | Landing gear control method and device for unmanned aerial vehicle, unmanned aerial vehicle, and system for same |
| CN107000832B (en) * | 2017-01-19 | 2019-03-26 | 深圳市大疆创新科技有限公司 | Unmanned plane undercarriage control method, device, unmanned plane and its system |
| US11834197B2 (en) | 2017-01-19 | 2023-12-05 | SZ DJI Technology Co., Ltd. | Unmanned aerial vehicle landing gear control method, apparatus, unmanned aerial vehicle, and system thereof |
| CN108502145A (en) * | 2017-02-24 | 2018-09-07 | 赛峰起落架系统公司 | Emergency extension system for landing gear of aircraft |
| CN108502145B (en) * | 2017-02-24 | 2021-12-10 | 赛峰起落架系统公司 | Emergency extension system for aircraft landing gear |
| GB2569354A (en) * | 2017-12-14 | 2019-06-19 | Airbus Operations Ltd | Landing gear controller |
| EP3498602A1 (en) * | 2017-12-14 | 2019-06-19 | Airbus Operations Limited | Landing gear controller |
| US10894598B2 (en) | 2017-12-14 | 2021-01-19 | Airbus Operations Limited | Landing gear controller |
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| Publication number | Publication date |
|---|---|
| CN103204239B (en) | 2015-04-08 |
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Granted publication date: 20150408 Termination date: 20170424 |