CN104454289B - A kind of logic control circuit of engine health igniting - Google Patents
A kind of logic control circuit of engine health igniting Download PDFInfo
- Publication number
- CN104454289B CN104454289B CN201410716234.6A CN201410716234A CN104454289B CN 104454289 B CN104454289 B CN 104454289B CN 201410716234 A CN201410716234 A CN 201410716234A CN 104454289 B CN104454289 B CN 104454289B
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- Prior art keywords
- relay
- normally closed
- disembarking
- signal
- normally
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02P—IGNITION, OTHER THAN COMPRESSION IGNITION, FOR INTERNAL-COMBUSTION ENGINES; TESTING OF IGNITION TIMING IN COMPRESSION-IGNITION ENGINES
- F02P5/00—Advancing or retarding ignition; Control therefor
- F02P5/04—Advancing or retarding ignition; Control therefor automatically, as a function of the working conditions of the engine or vehicle or of the atmospheric conditions
- F02P5/145—Advancing or retarding ignition; Control therefor automatically, as a function of the working conditions of the engine or vehicle or of the atmospheric conditions using electrical means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The invention discloses the logic control circuit of a kind of engine health igniting, including 4 relays, relay III includes two relay K 1 in parallel and relay K 2；Ignition voltage is connected on the input of relay I, and the outfan of relay I is connected with the normally opened of relay II, and the normally closed point of relay II is connected with electromotor；Signal one tunnel of disembarking is connected on the line bag of relay I, and another road of signal of disembarking is connected on the normally-closed contact of relay K 2, the line bag of the normally closed connection relay II of relay K 1；Engine ignition instructs a road and is connected on the normally closed point of relay K 1, and engine ignition instructs another road and is connected on the normally closed point of relay IV, and the line bag of relay IV is connected with the normally closed of relay K 2.The engine igniting circuit of the present invention must first receive instruction of disembarking, then receives the engine ignition instruction that comprehensive control machine sends, could be to electromotor normal ignition；If sending engine ignition instruction in advance, then this engine ignition circuit will lose efficacy.
Description
Technical field
The present invention relates to the logic control circuit of a kind of engine health igniting.Belong to the logic control field to engine health igniting.
Background technology
For ensureing the safety of carrier aircraft, the electromotor of guided missile is all lighted a fire after leaving carrier aircraft.
In common design circuit, guided missile is combined control machine and is sent firing command, controls the igniting actuating of relay, completes engine ignition, its representative point ignition circuit such as Fig. 1.This firing circuit connect sequential be controlled the most in software, if engine ignition instruction send before premise of disembarking, electromotor will advanced ignition, carrier aircraft can be caused potential safety hazard.Accordingly, it is desirable to provide a kind of new technical scheme solves the problems referred to above.
Summary of the invention
The technical issues that need to address of the present invention are to provide the logic control circuit of a kind of engine health igniting.
For solving the technical problem of the present invention, the technical solution used in the present invention is:
The logic control circuit of a kind of engine health igniting, this this logic control circuit includes that relay I, relay II, relay III and relay IV, described relay III include two relay K 1 in parallel and relay K 2；Ignition voltage is connected on the input of relay I, and the outfan of described relay I is connected with the normally opened of relay II, and the normally closed point of described relay II is connected with electromotor；Signal one tunnel of disembarking is connected on the line bag of relay I, and another road of signal of disembarking is connected on the normally-closed contact of relay K 2, the line bag of the normally closed connection relay II of relay K 1, disembarks and refers to that guided missile leaves carrier aircraft；Engine ignition instructs a road and is connected on the normally closed point of relay K 1, and engine ignition instructs another road and is connected on the normally closed point of relay IV, and the line bag of described relay IV is connected with the normally closed of relay K 2.
Beneficial effects of the present invention: the engine igniting circuit of the present invention must first receive instruction of disembarking, then receives the engine ignition instruction that comprehensive control machine sends, could be to electromotor normal ignition；If sending engine ignition instruction in advance, then this engine ignition circuit will lose efficacy.
Accompanying drawing explanation
Fig. 1 is the structural representation of prior art general ignition circuit.
Fig. 2 is the circuit diagram of the present invention.
Wherein, 1, relay I, 2, relay II, 3, relay III, 4, relay IV, 5, electromotor.
Detailed description of the invention
The invention will be further described with specific embodiment below in conjunction with the accompanying drawings.Following example are merely to illustrate the present invention, are not limited to protection scope of the present invention.
With reference to Fig. 2, the logic control circuit of a kind of engine health igniting of the present invention, this logic control circuit includes relay I 1, relay II 2, relay III 3 and relay IV 4, and relay III 3 includes two relay K 1 in parallel and relay K 2；Ignition voltage is connected on the input of relay I 1, and the outfan of relay I 1 is connected with the normally opened of relay II 2, and the normally closed point of relay II 2 is connected with electromotor 5；Signal one tunnel of disembarking is connected on the line bag of relay I 1, and another road of signal of disembarking is connected on the normally-closed contact of relay K 2, the line bag of the normally closed connection relay II 2 of relay K 1, disembarks and refers to that guided missile leaves carrier aircraft；Engine ignition instructs a road and is connected on the normally closed point of relay K 1, and engine ignition instructs another road and is connected on the normally closed point of relay IV 4, and the line bag of relay IV is connected with the normally closed of relay K 2.
It is specifically described below:
When signal of disembarking sends prior to engine ignition instruction, road signal of disembarking drives relay I 1 so that it is time delay is connected, and ignition voltage output is to the normally opened point of relay II 2；Another road signal of disembarking drives relay IV 4, relay IV 4 action by the normally-closed contact of the relay K 2 in relay III, and normally closed point disconnects；When engine ignition instruction sends, the normally closed point of this instruction transmission to relay IV 4, because of relay IV 4 action, normally closed point disconnects, and engine ignition instruction cannot pass through relay IV 4；The normally closed output of the engine ignition instruction on another road relay K 1 in relay III, to the line bag of relay II 2, drives its action, and relay II is normally opened to be connected, and ignition voltage exports to electromotor 5, completes igniting.
When engine ignition instruction sends prior to signal of disembarking, riches all the way, and motivation firing command signal exports and drives relay II 2 by the normally closed of relay K 1 in relay III, the normally opened connection of relay II 2；Another road engine ignition command signal exports the normally closed relay K 1 exporting and driving in relay III to relay IV 4 and relay K 2, relay K 1 in relay III and the normally closed disconnection of relay K 2, engine ignition instruction cannot arrive relay II 2, the normally opened disconnection of relay II 2；When signal of disembarking sends, road signal of disembarking drives relay I 1, relay I 1 action, ignition voltage through certain time-delay output to the normally opened point of relay II 2；Signal output is disembarked to the normally closed point of the relay K 2 in relay III in another road, because relay K 1 and the normally closed point of relay K 2 of relay III are already off, signal of disembarking cannot continue transmission, so far, owing to the normally opened point of relay II 2 disconnects always, ignition voltage cannot export to electromotor 5, i.e. cannot complete igniting.
Wherein, relay I 1 selects time-delay relay, it is ensured that after signal of disembarking sends certain time, guided missile has moved away from carrier aircraft, and electromotor 5 could be lighted a fire, and enhances the safety of carrier aircraft.
The present invention, on the basis of Fig. 1 available circuit designs, utilizes the priority logical relation disembarked between signal and engine ignition instruction, uses relay interlocking, it is achieved the security control to engine igniting circuit.
Engine ignition instruction is prevented to send the situation causing electromotor mis-ignition in advance while present invention Reliable guarantee engine ignition under normal circumstances, it is ensured that the safety of carrier aircraft.
Claims (2)
1. the logic control circuit of engine health igniting, it is characterised in that: this logic control circuit includes that relay I, relay II, relay III and relay IV, described relay III include two relay K 1 in parallel and relay K 2；
Ignition voltage is connected on the input of relay I, and the outfan of described relay I is connected with the normally opened of relay II, and the normally closed point of described relay II is connected with electromotor；
Signal one tunnel of disembarking is connected on the line bag of relay I, and another road of signal of disembarking is connected on the normally-closed contact of relay K 2, the line bag of the normally closed connection relay II of relay K 1, disembarks and refers to that guided missile leaves carrier aircraft；
Engine ignition instructs a road and is connected on the normally closed point of relay K 1, and engine ignition instructs another road and is connected on the normally closed point of relay IV, and the line bag of described relay IV is connected with the normally closed of relay K 2.
The logic control circuit of a kind of engine health the most according to claim 1 igniting, it is characterised in that:
When signal of disembarking sends prior to engine ignition instruction, road signal of disembarking drives relay I so that it is time delay is connected, and ignition voltage output is to the normally opened point of relay II；Another road signal of disembarking drives relay IV, relay IV action by the normally-closed contact of the relay K 2 in relay III, and normally closed point disconnects；When engine ignition instruction sends, the normally closed point of this instruction transmission to relay IV, because of relay IV action, normally closed point disconnects, and engine ignition instruction cannot pass through relay IV；The normally closed output of the engine ignition instruction on another road relay K 1 in relay III, to the line bag of relay II, drives its action, and the normally opened connection of relay II, ignition voltage exports to electromotor, completes igniting；
When engine ignition instruction sends prior to signal of disembarking, riches all the way, and motivation firing command signal exports and drives relay II by the normally closed of relay K 1 in relay III, the normally opened connection of relay II；Another road engine ignition command signal exports the normally closed relay K 1 exporting and driving in relay III to relay IV and relay K 2, relay K 1 in relay III and the normally closed disconnection of relay K 2, engine ignition instruction cannot arrive relay II, the normally opened disconnection of relay II；When signal of disembarking sends, road signal of disembarking drives relay I, relay I action, ignition voltage through certain time-delay output to the normally opened point of relay II；Signal output is disembarked to the normally closed point of the relay K 2 in relay III in another road, because relay K 1 and the normally closed point of relay K 2 of relay III are already off, signal of disembarking cannot continue transmission, so far, owing to the normally opened point of relay II disconnects always, ignition voltage cannot export to electromotor, i.e. cannot complete igniting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410716234.6A CN104454289B (en) | 2014-12-02 | 2014-12-02 | A kind of logic control circuit of engine health igniting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410716234.6A CN104454289B (en) | 2014-12-02 | 2014-12-02 | A kind of logic control circuit of engine health igniting |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104454289A CN104454289A (en) | 2015-03-25 |
| CN104454289B true CN104454289B (en) | 2016-08-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410716234.6A Active CN104454289B (en) | 2014-12-02 | 2014-12-02 | A kind of logic control circuit of engine health igniting |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4305004A (en) * | 1979-03-20 | 1981-12-08 | Nissan Motor Co. Ltd. | Current supply circuit for electronic equipment of an automotive vehicle |
| CN2302349Y (en) * | 1997-03-17 | 1998-12-30 | 冯中兴 | Electronic cipher ignitor for vehicle |
| CN101072936A (en) * | 2004-12-08 | 2007-11-14 | 丰田自动车株式会社 | Control device of internal combustion engine |
| CN204283703U (en) * | 2014-12-02 | 2015-04-22 | 江西洪都航空工业集团有限责任公司 | A kind of logic control circuit of engine health igniting |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6722353B2 (en) * | 2002-05-06 | 2004-04-20 | Taiwan Atv Industrial Co., Ltd. | Safety remote control and emergency safety switch power shutoff device of a motorized beach vehicle |
-
2014
- 2014-12-02 CN CN201410716234.6A patent/CN104454289B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4305004A (en) * | 1979-03-20 | 1981-12-08 | Nissan Motor Co. Ltd. | Current supply circuit for electronic equipment of an automotive vehicle |
| CN2302349Y (en) * | 1997-03-17 | 1998-12-30 | 冯中兴 | Electronic cipher ignitor for vehicle |
| CN101072936A (en) * | 2004-12-08 | 2007-11-14 | 丰田自动车株式会社 | Control device of internal combustion engine |
| CN204283703U (en) * | 2014-12-02 | 2015-04-22 | 江西洪都航空工业集团有限责任公司 | A kind of logic control circuit of engine health igniting |
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| Publication number | Publication date |
|---|---|
| CN104454289A (en) | 2015-03-25 |
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