CN108644038A - A kind of aviation piston engine pre-heating system - Google Patents
A kind of aviation piston engine pre-heating system Download PDFInfo
- Publication number
- CN108644038A CN108644038A CN201810725056.1A CN201810725056A CN108644038A CN 108644038 A CN108644038 A CN 108644038A CN 201810725056 A CN201810725056 A CN 201810725056A CN 108644038 A CN108644038 A CN 108644038A
- Authority
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- China
- Prior art keywords
- engine
- heater plug
- power supply
- temperature
- heating system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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- 238000010438 heat treatment Methods 0.000 title claims abstract description 36
- 238000001514 detection method Methods 0.000 claims abstract description 16
- 230000005611 electricity Effects 0.000 claims description 12
- 230000008450 motivation Effects 0.000 claims description 5
- 239000000446 fuel Substances 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims description 3
- 239000010705 motor oil Substances 0.000 claims description 3
- 239000002826 coolant Substances 0.000 claims description 2
- 238000007906 compression Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 239000008246 gaseous mixture Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000007858 starting material Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M31/00—Apparatus for thermally treating combustion-air, fuel, or fuel-air mixture
- F02M31/02—Apparatus for thermally treating combustion-air, fuel, or fuel-air mixture for heating
- F02M31/12—Apparatus for thermally treating combustion-air, fuel, or fuel-air mixture for heating electrically
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02N—STARTING OF COMBUSTION ENGINES; STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDED FOR
- F02N19/00—Starting aids for combustion engines, not otherwise provided for
- F02N19/02—Aiding engine start by thermal means, e.g. using lighted wicks
- F02N19/04—Aiding engine start by thermal means, e.g. using lighted wicks by heating of fluids used in engines
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a kind of aviation piston engine pre-heating systems, including heater plug, heater plug controller, engine temperature sensing unit, aircraft wheel load transducer, engine power supply detection module, the engine temperature sensing unit, aircraft wheel load transducer, engine power supply detection module are connect with the input terminal of heater plug controller respectively, and the output end of the heater plug controller is connect with heater plug；The heater plug controller controls the work of heater plug according to the temperature, load, power supply state that receive.The advantage of the invention is that：It can effectively be preheated by the system, reduce the too low influence for startup of temperature.The input condition of system starts and the decision condition of power cut-off are increased, keeps the logic of system more rigorous thorough, and effectively reduce maloperation, improves the safety and reliability of system.
Description
Technical field
The present invention relates to aero-engine field more particularly to a kind of aviation piston engine pre-heating systems.
Background technology
Piston engine can be divided into compression-ignited and spark ignition type from sparking mode, and compression-ignited pressed by gaseous mixture in cylinder
Expansion work is fired, spark ignition type is by lighting gaseous mixture acting by igniter, at low ambient temperatures, starting
Since mixed gas temperature is relatively low when engine, the work(generated in compression process overcomes the process of resistance longer, thermal loss
It is larger, so that starting is become difficult.In addition, the factor for influencing Compression Engine cold-starting also has lubricating oil viscosity increase,
Each friction surface cannot get sufficient pre-lubrication, to increase the starting reactance of engine again.Common engine start is
Electric power is provided to starter by accumulator, to drag engine rotation, when environment temperature is relatively low, the performance of accumulator also can
Declined, causes repeatedly to provide electric power to starter for a long time.It is influenced by the principal element of this three aspect, compression
Engine starts extremely difficult at low ambient temperatures.
Currently, the mating pre-heating system of compression-ignited piston engine be although can meet -30 DEG C of cold-starting requirement,
The work-based logic of pre-heating system is limited by engine controller, and the work of pre-heating system is not independent, is controlled by engine
The output of device controls, and is a kind of opened loop control, and triggering and the condition for terminating pre-heating system work are relatively simple, and accuracy is stablized
Property it is poor, and there are problems that when aviation field is applied increasing the complexity of engine controller.
Invention content
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of piston engine pre-heating systems.
To achieve the goals above, the technical solution adopted by the present invention is：A kind of aviation piston engine pre-heating system, packet
Include heater plug, heater plug controller, engine temperature sensing unit, aircraft wheel load transducer, engine power supply detection module, institute
It is defeated with heater plug controller respectively to state engine temperature sensing unit, aircraft wheel load transducer, engine power supply detection module
Enter end connection, the output end of the heater plug controller is connect with heater plug；The heater plug controller is according to the temperature received
Degree, load, power supply state control the work of heater plug.
The heater plug is covered mounted on engine cylinder, for heating the air near fuel injector nozzle opening.
Power supply is passed with heater plug, preheating controller, engine temperature sensing unit, aircraft wheel load respectively by power switch
Sensor, for powering for each component.
After power switch closure, engine temperature sensing unit, aircraft wheel load transducer start work by the number of acquisition
According to being transferred in heater plug controller, after temperature, wheel load data meet preheating condition, acquisition engine power supply state is believed
Breath, when engine is in power supply state, heater plug controller is controlled is allowed to work to heater plug power supply.
Judge aircraft more than the data of preheating unlocking condition temperature or the acquisition of aircraft wheel load transducer in engine temperature
Not at ground, the control of heater plug controller disconnects the power supply of heater plug, stops heater plug work.
The heater plug controller is connect with indicator light, and heater plug working condition is shown for controlling indicator light.
Engine power supply detection module by detect the control of engine power circuit switch on closed state come
Judge the power supply state of engine.
Enabled switch of the engine power circuit control switch as preheating controller, electricity is connected by enabled switch one end
Source, the other end are separately connected the input pin of engine, preheating controller.
The coolant liquid outlet temperature or engine cylinder cover temperature or hair of the engine temperature sensing unit acquisition engine
Oil temperature in motivation is indicating engine temperature.
The aircraft wheel load transducer is mounted on undercarriage wheel, for being to judge aircraft according to load data
It is no on the ground.
The advantage of the invention is that：It can effectively be preheated by the system, it is too low for startup to reduce temperature
It influences；Heater plug controller, heater plug controller is given just to have output to heater plug, make by meeting multiple input condition simultaneously
Pre-heating system works；The work for terminating pre-heating system also has multiple conditions, as long as and meeting one in these conditions and can tie
Beam pre-heating system works.Such system design so that the system of entire high power work becomes an independent system, reduces
To the dependence of other systems, the complexity of engine controller is reduced.Due to increasing the input of system starts
The decision condition of condition and power cut-off keeps the logic of system more rigorous thorough, and effectively reduces maloperation, improves
The safety and reliability of system.
Description of the drawings
Below to each width attached drawing of description of the invention expression content and figure in label be briefly described：
Fig. 1 is pre-heating system structure principle chart of the present invention；
Fig. 2 is heater plug controller of the present invention control output logic chart.
Label in above-mentioned figure is：1, heater plug controller；2, heater plug；3, engine temperature sensing unit；4, aircraft
Wheel load sensor；5, switch is enabled；6, indicator light；7, power supply；8, power switch.
Specific implementation mode
The specific implementation mode of the present invention is made further detailed by the description to optimum embodiment below against attached drawing
Thin explanation.
A kind of aviation piston engine pre-heating system, including heater plug 2, heater plug controller 1, engine temperature sensing unit
3, aircraft wheel load transducer 4, engine power supply detection module, engine temperature sensing unit 3, aircraft wheel load transducer 4, hair
Motivation power supply detection module is connect with the input terminal of heater plug controller 1 respectively, the output end and heater plug of heater plug controller 1
2 connections；Heater plug controller 1 controls the work of heater plug 2 according to the temperature, load, power supply state that receive.
Heater plug 2 is covered mounted on engine cylinder, for heating the air near fuel injector nozzle opening.
Engine temperature sensing unit 3 is mounted on engine body, and engine temperature sensing unit 3 acquires the cooling of engine
Liquid outlet temperature or engine cylinder cover temperature or in-engine oil temperature are indicating engine temperature.
Aircraft wheel load transducer 4 is mounted on undercarriage wheel, for whether judging aircraft according to load data
On the ground.
Engine power supply detection module switches on closed state to judge by detection engine power circuit control
The power supply state of engine.
Power supply 7 by power switch 8 respectively with heater plug controller 1, heater plug 2, engine temperature sensing unit 3, aircraft
Wheel load sensor 4, for powering for each component so that sensor, controller work once electrified.
Its principle includes：After the closure of power switch 8, engine temperature sensing unit 3, aircraft wheel load transducer 4 start
Work is by the data transfer of acquisition to heater plug controller 1, and after temperature, wheel load data meet preheating condition, acquisition is sent out
Motivation power supply state information, when engine is in power supply state, the control of heater plug controller 1 is powered to heater plug 2 is allowed to work
Make.Be equivalent at this time when engine temperature, aircraft on the ground, enabled switch 5 be satisfied by condition when just control the power supply of heater plug 2
Work, otherwise either condition is unsatisfactory for, and heater plug 2 does not work.It is more than that preheating is opened in engine temperature after heater plug 2 works
It opens the data that Conditions Temperature or aircraft wheel load transducer 4 acquire and judges aircraft not at ground, the control of heater plug controller 1 is disconnected
The power supply of heater plug 2 is opened, stops heater plug 2 and works, preheating terminates.
Engine power supply detection module can pass through by the power supply state of detection engine electricity system and detect engine
The on off state of electricity system, enabled switch 5 of the engine power circuit control switch as preheating controller, enables switch 5
Install aboard start owner's electric switch, the control switch for power to engine electricity system, by enabled switch 5 one
End connection power supply 7, the other end are separately connected the input pin of engine electricity system, heater plug controller, and power supply 7 is used for pre-
Hot systems provide electric power.Low and high level signal is acquired by the pin of heater plug controller 1 in this way and can determine power supply state, such as
When enabled switch 5 is closed, engine electricity system is powered, at this time 1 pin high level of heater plug controller；When enabled switch 5
When disconnection, pin low level judges power supply state according to level signal.
There is a power switch 8 to control break-make, when the power switch 8 is closed, engine temperature between power supply 7 and pre-heating system
Sensor 3 and 4 work once electrified of aircraft wheel load transducer are spent by measurement feedback to heater plug controller 1, heater plug control
Device 1 can judge whether the two conditions meet and open the condition preheated (temperature is low according to the result of sensor feedback by calculating
When setting value, temperature condition meets；According to wheel load condition adjudgement aircraft whether on the ground when, on the ground when meet item
Part), if satisfied, heater plug controller 1 also will continue to judge whether enabled switch 5 is closed, that is, whether engine powers, if
Be closed, at this point, engine temperature less than a certain setting value (such as 0 DEG C), aircraft ground (such as wheel load signal be low level 0V),
Enabled switch 5 is closed (such as enable signal is high level 28V) and meets simultaneously, then heater plug controller 1 can then be carried to heater plug 2
For being allowed to carry out heating work for electricity output, meanwhile, the also preheating instruction output all the way of heater plug controller 1.Once engine
3 measurement result of temperature sensor is more than to open the temperature (as being higher than 0 DEG C) or the measurement knot of aircraft wheel load transducer 4 of preheating condition
Fruit shows aircraft not at ground (such as wheel load signal is high level 28V), and heater plug controller 1 can receive this information and break
Open to heater plug 2 for electricity output, but only when enabled switch 5 disconnect (such as enable signal by high level become 28V into low level 0V),
Heater plug controller 1 cannot then disconnected to heater plug 2 for electricity output.It inputs as shown in Figure 2 with output logical relation.
It is exactly the input of heater plug controller 1 there are three condition：Temperature, whether ground, engine electricity system power supply whether, and this
Three conditions need to meet simultaneously (temperature less than setting value, on the ground, engine electricity system powered operation), heater plug control
Device 1 could start to work, but as long as meeting any one of enable signal and engine temperature signal condition (engine temperature
Be greater than the set value or aircraft not on the ground), heater plug controller 1 can power cut-off.
Whether heater plug controller 1 can detect pre-heating system by output port to heater plug 2 or detection module
In the presence of the fault condition of short circuit or open circuit, once detecting such failure, heater plug controller 1 can export indicating fault letter all the way
Number to indicator light 6,2 working condition of heater plug is shown for controlling indicator light 6.Indicator light 6 refers to including pre- thermal light 6, failure
Show lamp 6, when controlling the work of heater plug 2, the control of pre- thermal light 6 lights, and when there are failures, malfunction indicator lamp 6 lights.In advance
In the installation to the avionics system of aircraft of thermal light 6, for showing pre- Warm status.
The work of the pre-heating system of the prior art is not independent, is controlled by the output of engine controller, is that one kind is opened
Ring controls, and triggering and the condition for terminating pre-heating system work are relatively simple, and engine control is increased when aviation field is applied
The complexity of device processed.The present invention proposes a kind of pre-heating system design of independent closed-loop control, multiple defeated by meeting simultaneously
Enter condition to heater plug controller 1, heater plug controller 1 just has output to heater plug 2, and pre-heating system is made to work；Terminate pre-
The work of hot systems also has multiple conditions, as long as and meet one in these conditions can terminate pre-heating system work.In this way
System design so that the system of entire high power work becomes an independent system, can independent acquisition signal, progress
Logical operation is simultaneously exported by operation result, is reduced the dependence to other systems, is reduced the complexity of engine controller
Degree.Due to increasing the input condition of system starts and the decision condition of power cut-off, make the logic of system more rigorous week
Entirely, and maloperation is effectively reduced, improves the safety and reliability of system.
Obviously present invention specific implementation is not subject to the restrictions described above, as long as using the methodology and skill of the present invention
The improvement for the various unsubstantialities that art scheme carries out, within protection scope of the present invention.
Claims (10)
1. a kind of aviation piston engine pre-heating system, including heater plug, it is characterised in that：Further include heater plug controller, hair
Motivation temperature sensor, aircraft wheel load transducer, engine power supply detection module, the engine temperature sensing unit, aircraft
Wheel load sensor, engine power supply detection module are connect with the input terminal of heater plug controller respectively, the heater plug control
The output end of device is connect with heater plug；The heater plug controller controls pre- according to the temperature, load, power supply state that receive
The work of heat plug.
2. a kind of aviation piston engine pre-heating system as described in claim 1, it is characterised in that：The heater plug is mounted on
Engine cylinder covers, for heating the air near fuel injector nozzle opening.
3. a kind of aviation piston engine pre-heating system as described in claim 1, it is characterised in that：Power supply passes through power switch
Respectively with heater plug, preheating controller, engine temperature sensing unit, aircraft wheel load transducer, it is used to power for each component.
4. a kind of aviation piston engine pre-heating system as described in claim 1 or 3, it is characterised in that：It is closed in power switch
After conjunction, engine temperature sensing unit, aircraft wheel load transducer start work by the data transfer of acquisition to heater plug controller
In, after temperature, wheel load data meet preheating condition, engine power supply state information is acquired, power supply shape is in engine
Heater plug controller is controlled when state is allowed to work to heater plug power supply.
5. a kind of aviation piston engine pre-heating system as claimed in claim 4, it is characterised in that：It is more than in engine temperature
Preheating unlocking condition temperature or the data of aircraft wheel load transducer acquisition judge aircraft not at ground, heater plug controller control
System disconnects the power supply of heater plug, stops heater plug work.
6. a kind of aviation piston engine pre-heating system as described in claim 1, it is characterised in that：The heater plug controller
It is connect with indicator light, heater plug working condition is shown for controlling indicator light.
7. a kind of aviation piston engine pre-heating system as described in claim 1-6 is any, it is characterised in that：The engine
Power supply detection module switches on closed state to judge the power supply shape of engine by detection engine power circuit control
State.
8. a kind of aviation piston engine pre-heating system as described in claim 1-6 is any, it is characterised in that：Engine electricity consumption
Enabled switch one end is connected power supply by enabled switch of the circuit controling switch as preheating controller, and the other end is separately connected hair
The input pin of motivation, preheating controller.
9. a kind of aviation piston engine pre-heating system as described in claim 1-6 is any, it is characterised in that：The engine
The coolant liquid outlet temperature or engine cylinder cover temperature of temperature sensor acquisition engine or in-engine oil temperature are used
To indicate engine temperature.
10. a kind of aviation piston engine pre-heating system as described in claim 1-6 is any, it is characterised in that：The aircraft
On the ground whether wheel load sensor is mounted on undercarriage wheel, for judging aircraft according to load data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810725056.1A CN108644038B (en) | 2018-07-04 | 2018-07-04 | Aviation piston engine preheating system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810725056.1A CN108644038B (en) | 2018-07-04 | 2018-07-04 | Aviation piston engine preheating system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108644038A true CN108644038A (en) | 2018-10-12 |
| CN108644038B CN108644038B (en) | 2024-04-23 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810725056.1A Active CN108644038B (en) | 2018-07-04 | 2018-07-04 | Aviation piston engine preheating system |
Country Status (1)
| Country | Link |
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| CN (1) | CN108644038B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4506145A (en) * | 1978-07-10 | 1985-03-19 | Isuzu Motors Ltd. | Device for controlling engine preheating |
| US20020033155A1 (en) * | 2000-09-20 | 2002-03-21 | Jae-Yoon Jung | Method for controlling a glow plug for diesel engine |
| CN103821655A (en) * | 2014-03-04 | 2014-05-28 | 广西玉柴机器股份有限公司 | Preheating control device for engine start and control method thereof |
| CN105134444A (en) * | 2015-09-01 | 2015-12-09 | 东风朝阳朝柴动力有限公司 | Diesel engine automatic preheating device |
| CN106246434A (en) * | 2015-06-15 | 2016-12-21 | 现代自动车株式会社 | For preheating the apparatus and method of the electromotor of light hybrid vehicle |
| CN206513470U (en) * | 2016-12-20 | 2017-09-22 | 陕西北方动力有限责任公司 | A kind of diesel engine low temperature starting control system and cold-starting device |
| CN208578658U (en) * | 2018-07-04 | 2019-03-05 | 芜湖钻石航空发动机有限公司 | A kind of aviation piston engine pre-heating system |
-
2018
- 2018-07-04 CN CN201810725056.1A patent/CN108644038B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4506145A (en) * | 1978-07-10 | 1985-03-19 | Isuzu Motors Ltd. | Device for controlling engine preheating |
| US20020033155A1 (en) * | 2000-09-20 | 2002-03-21 | Jae-Yoon Jung | Method for controlling a glow plug for diesel engine |
| CN103821655A (en) * | 2014-03-04 | 2014-05-28 | 广西玉柴机器股份有限公司 | Preheating control device for engine start and control method thereof |
| CN106246434A (en) * | 2015-06-15 | 2016-12-21 | 现代自动车株式会社 | For preheating the apparatus and method of the electromotor of light hybrid vehicle |
| CN105134444A (en) * | 2015-09-01 | 2015-12-09 | 东风朝阳朝柴动力有限公司 | Diesel engine automatic preheating device |
| CN206513470U (en) * | 2016-12-20 | 2017-09-22 | 陕西北方动力有限责任公司 | A kind of diesel engine low temperature starting control system and cold-starting device |
| CN208578658U (en) * | 2018-07-04 | 2019-03-05 | 芜湖钻石航空发动机有限公司 | A kind of aviation piston engine pre-heating system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108644038B (en) | 2024-04-23 |
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