CN106499562B - A kind of helicopter engine cold start control circuit - Google Patents
A kind of helicopter engine cold start control circuit Download PDFInfo
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- CN106499562B CN106499562B CN201510566520.3A CN201510566520A CN106499562B CN 106499562 B CN106499562 B CN 106499562B CN 201510566520 A CN201510566520 A CN 201510566520A CN 106499562 B CN106499562 B CN 106499562B
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- engine
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- starting
- control module
- cold start
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Abstract
The present invention relates to a kind of cold start control circuit, more particularly to a kind of helicopter engine cold start control circuit.The flight control of starting control switch (1) and slow train control terminal are connect with engine start control module (2) input terminal, the parking end of starting control switch is connect with engine cold starting control button input terminal, DC power supply controls the work of engine start igniter (6) and starter-generator (8) by rotational speed control module (4) and the contactor of starting control module (2), it is characterised in that：The cold start control button (7) of engine is connected on to the parking toll end of engine start control switch (1).The parking toll of starting control and engine is linked together, under the premise of not influencing the control of engine normal starting, it is possible to prevente effectively from engine work, implement the cold start control of engine, even if driver's maloperation will not influence the normal work of helicopter.
Description
Technical field
The present invention relates to a kind of cold start control circuit, more particularly to a kind of helicopter engine cold start control circuit.
Background technology
Current helicopter engine start control circuit referring to Fig. 1, it by engine start parking toll switch 1,
Dynamic control module 2, rotational speed control module 4, electromagnetic valve for braking 5, engine start igniter 6, is started park control module 3
Machine cold start control button 7, starter-generator 8 form.The flight control of starting control switch 1 and slow train control terminal and engine
2 input terminal of starting control module connects, and 2 control contactor of starting control module is connected, and DC power supply passes through rotational speed control module 4
With the contactor control engine start igniter 6 of starting control module 2 and the work of starter-generator 8, helicopter is driven
Engine start, when helicopter detect engine speed reach be able to maintain that from operating 45% when, rotational speed control module 4
The power supply of supply engine starting ignition device 6 is disconnected, helicopter engine is completed to start, and cuts off starting circuit.By starting
Machine starting control button can directly control the work of starter-generator 8, realize the cold start control of engine.
When engine start is unsuccessful, before next engine start, driver is needed to carry out cold start to engine
Control, blows the excess oil for being trapped in engine interior off, this action needs driver to be controlled after engine cut-off, it is only necessary to press
Hydraulic motor cold start control button 7, directly drives starter-generator 8, drives engine by starter-generator, realizes to hair
The cold start of motivation.
The disadvantage is that：Under normal circumstances, after engine completes normal starting, the effect of starter-generator starter/generator.The shape
State need not implement cold start to engine, and cold start is only needed to run under power-off conditions, normally be risen in engine
After dynamic, it may occur that the case where driver's maloperation cold start controls in this case, connects the starting of starter-generator
Function, it may occur that starter-generator overheat condition can influence helicopter to influence the normal work of starter-generator
Safety margin.
Invention content
The technical problem to be solved in the present invention：It proposes a kind of to prevent driver's maloperation engine after the engine is started up
The helicopter engine cold start control circuit of cold start.
Technical scheme of the present invention：The circuit includes engine start parking toll switch 1, starting control module 2, stops
Vehicle control module 3, rotational speed control module 4, electromagnetic valve for braking 5, engine start igniter 6, engine cold starting control are pressed
Button 7 and starter-generator 8, the flight control of starting control switch 1 and slow train control terminal are inputted with engine start control module 2
End connection, the parking end of starting control switch are connect with engine cold starting control button input terminal, and DC power supply passes through rotating speed
The contactor of control module 4 and starting control module 2 controls the work of engine start igniter 6 and starter-generator 8,
It is characterized in that：The cold start control button 7 of engine is connected on the parking toll end that engine start controls switch 1.
Beneficial effects of the present invention：The parking toll of starting control and engine is linked together, is not influencing to start
Under the premise of machine normal starting controls, it is possible to prevente effectively from engine work, implement the cold start control of engine,
Even if driver's maloperation will not influence the normal work of helicopter.
Description of the drawings
Fig. 1 is the circuit diagram of the prior art；
Fig. 2 is the schematic diagram of the technical program；
In figure：1 switchs in order to control, and 2 be starting control module, and 3 be park control module, and 4 be rotational speed control module, and 5 are
Electromagnetic valve for braking, 6 be engine start igniter, and 7 be engine cold starting control button, and 8 be starter-generator.
Specific implementation mode
Patent of the present invention is described in further details below.
Referring to Fig. 2, helicopter engine start control circuit, including engine start parking toll switch 1, starting control
Module 2, park control module 3, rotational speed control module 4, electromagnetic valve for braking 5, engine start igniter 6, cold of engine
Dynamic control button 7, starter-generator 8.The flight control of starting control switch 1 and slow train control terminal control mould with engine start
2 input terminal of block connects, and the parking end of starting control switch is connect with engine cold starting control button input terminal, starting control mould
2 control contactor of block is connected, and DC power supply controls engine by rotational speed control module 4 and the contactor of starting control module 2
The work of starting ignition device 6 and starter-generator 8 drives the engine start of helicopter, when helicopter detects engine
When rotating speed reaches be able to maintain that operating certainly 45%, rotational speed control module 4 disconnects the electricity of supply engine starting ignition device 6
Source, helicopter engine are completed to start, and cut off starting circuit.Starting hair can be directly controlled by engine start control button
The cold start control of engine is realized in the work of motor 8.It is characterized in that：The cold start control button 7 of engine is connected on hair
Engine start controls the parking toll end of switch 1, and engine start controls switch 1 in slow train or state of flight, cannot achieve
The cold start of engine controls, and when only engine start control switch 1 is in dead ship condition, could implement cold of engine
Dynamic control, when avoiding engine work, driver implements maloperation to the cold start of engine.
The operation principle of patent of the present invention is：
Starting and the dead ship condition that control engine is switched by controlling, when helicopter is in slow train or state of flight,
Even if driver is not turned on cold start control circuit if pressing the cold start control button engine of hydraulic motor.Only when driving
The person's of sailing operation-control switch, after making engine cut-off, driver could be sent out by pressing engine cold starting control button
The cold start of motivation controls., can be to avoid in engine work by the design of the logic control, engine cold starting
The work of state.
Claims (1)
1. a kind of helicopter engine cold start control circuit, the circuit includes engine start parking toll switch (1), rises
Dynamic control module (2), park control module (3), rotational speed control module (4), electromagnetic valve for braking (5), engine start igniting dress
(6), engine cold starting control button (7) and starter-generator (8) are set, engine start parking toll switchs the flight of (1)
Control and slow train control terminal are connect with engine start control module (2) input terminal, and DC power supply passes through rotational speed control module (4)
Contactor with starting control module (2) is engine start igniter (6) and starter-generator (8) provides electric energy, special
Sign is：The cold start control button (7) of engine is connected on the parking toll end that engine start parking toll switchs (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510566520.3A CN106499562B (en) | 2015-09-08 | 2015-09-08 | A kind of helicopter engine cold start control circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510566520.3A CN106499562B (en) | 2015-09-08 | 2015-09-08 | A kind of helicopter engine cold start control circuit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106499562A CN106499562A (en) | 2017-03-15 |
| CN106499562B true CN106499562B (en) | 2018-07-24 |
Family
ID=58287274
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510566520.3A Active CN106499562B (en) | 2015-09-08 | 2015-09-08 | A kind of helicopter engine cold start control circuit |
Country Status (1)
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| CN (1) | CN106499562B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110966098B (en) * | 2019-12-04 | 2021-08-06 | 中国直升机设计研究所 | Helicopter brake starting control circuit, brake starting system and control method |
| CN113911375B (en) * | 2021-11-03 | 2023-06-23 | 哈尔滨哈飞航空工业有限责任公司 | Manual starting control circuit of helicopter engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0966897A (en) * | 1995-08-30 | 1997-03-11 | Yanmar Agricult Equip Co Ltd | Remotely piloted helicopter |
| US5742137A (en) * | 1994-07-05 | 1998-04-21 | Chrysler Corporation | Starter motor control circuit and method |
| CN2908835Y (en) * | 2006-05-17 | 2007-06-06 | 厦门金龙联合汽车工业有限公司 | Protection device of starting device |
| CN201802538U (en) * | 2010-08-12 | 2011-04-20 | 徐工集团工程机械股份有限公司科技分公司 | Engine starting protection device and system |
| CN202811082U (en) * | 2012-08-09 | 2013-03-20 | 中国南方航空工业(集团)有限公司 | Starting control device of engine |
| EP2779422A1 (en) * | 2013-03-11 | 2014-09-17 | Bell Helicopter Textron Inc. | Series battery start controller |
-
2015
- 2015-09-08 CN CN201510566520.3A patent/CN106499562B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5742137A (en) * | 1994-07-05 | 1998-04-21 | Chrysler Corporation | Starter motor control circuit and method |
| JPH0966897A (en) * | 1995-08-30 | 1997-03-11 | Yanmar Agricult Equip Co Ltd | Remotely piloted helicopter |
| CN2908835Y (en) * | 2006-05-17 | 2007-06-06 | 厦门金龙联合汽车工业有限公司 | Protection device of starting device |
| CN201802538U (en) * | 2010-08-12 | 2011-04-20 | 徐工集团工程机械股份有限公司科技分公司 | Engine starting protection device and system |
| CN202811082U (en) * | 2012-08-09 | 2013-03-20 | 中国南方航空工业(集团)有限公司 | Starting control device of engine |
| EP2779422A1 (en) * | 2013-03-11 | 2014-09-17 | Bell Helicopter Textron Inc. | Series battery start controller |
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| Publication number | Publication date |
|---|---|
| CN106499562A (en) | 2017-03-15 |
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| TR01 | Transfer of patent right |
Effective date of registration: 20191204 Address after: 150066 Heilongjiang city of Harbin province Harbin Pingfang District Youxie Street No. 15 Patentee after: Harbin Hafei Aviation Industry Co. Ltd. Address before: 150066 Heilongjiang Province, Harbin city Youxie Street Pingfang District No. 15 Patentee before: Harbin Aircraft Industrial (Group) Co., Ltd. |