CN208578658U - A kind of aviation piston engine pre-heating system - Google Patents
A kind of aviation piston engine pre-heating system Download PDFInfo
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- CN208578658U CN208578658U CN201821052749.0U CN201821052749U CN208578658U CN 208578658 U CN208578658 U CN 208578658U CN 201821052749 U CN201821052749 U CN 201821052749U CN 208578658 U CN208578658 U CN 208578658U
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- heating system
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Abstract
The utility model 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.Utility model has the advantages that can effectively be preheated by the system, the too low influence for starting of temperature is reduced.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 technique
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 at low ambient temperatures, is started by lighting gaseous mixture acting by igniter
Since mixed gas temperature is lower when engine, the function generated in compression process overcomes the process of resistance longer, thermal loss
It is larger, become difficult starting.In addition, influence the factor of Compression Engine cold-starting there are also 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 battery, to drag engine rotation, when environment temperature is lower, the performance of battery 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 matched pre-heating system of compression-ignited piston engine is although can satisfy -30 DEG C of cold-starting requirement,
The work-based logic of pre-heating system is limited by engine controller, the work of pre-heating system be not it is independent, 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 aviation field application when there are problems that increase engine controller complexity.
Summary of the invention
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 are as follows: 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 mounted on engine cylinder and covers, 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 connection, for powering for each component.
After power switch closure, engine temperature sensing unit, aircraft wheel load transducer start work for 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, which is controlled, is allowed to work to heater plug power supply.
Aircraft is judged 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, shows heater plug working condition for control instructions lamp.
Engine power supply detection module by detect the unlatching closed state of engine power circuit control switch come
Judge the power supply state of engine.
Enabled switch one end is connected electricity by enabled switch of the engine power circuit control switch as preheating controller
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 to indicate engine temperature.
The aircraft wheel load transducer is mounted on undercarriage wheel, for judging that aircraft is according to load data
It is no on the ground.
The present invention has the advantages that can effectively be preheated by the system, it is too low for starting to reduce temperature
It influences；Heater plug controller is given by meeting multiple input conditions simultaneously, heater plug controller just has output to heater plug, makes
Pre-heating system work；The work for terminating pre-heating system also has multiple conditions, as long as and meeting one in these conditions and can tie
The work of beam pre-heating system.Such system design is reduced so that the system of entire high power work becomes an independent system
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.
Detailed description of the invention
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 equal are as follows: 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 embodiment
A specific embodiment of the invention is made further detailed below against attached drawing by the description to optimum embodiment
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 mounted on engine cylinder and covers, 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 to indicate 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 is judged by detecting the unlatching closed state of engine power circuit control switch
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 connects, for powering for each component, so that sensor, controller work once electrified.
Its principle includes: after the closure of power switch 8, and engine temperature sensing unit 3, aircraft wheel load transducer 4 start
The data of acquisition are transferred in heater plug controller 1 by work, after temperature, wheel load data meet preheating condition, acquisition hair
Motivation power supply state information, when engine is in power supply state, the control of heater plug controller 1 is allowed to work to the power supply of heater plug 2
Make.Be equivalent at this time when engine temperature, aircraft on the ground, enabled switch 5 be all satisfied 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 switch state of electricity system, enabled switch 5 of the engine power circuit control switch as preheating controller enable switch 5
Install aboard start owner's electric switch, the control switch for powering 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.Acquiring low and high level signal by the pin of heater plug controller 1 so can determine power supply state, such as
When enabled switch 5 closure, 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 on-off between power supply 7 and pre-heating system, when the power switch 8 closure, engine temperature
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 according to the result of sensor feedback by calculate judge the two conditions whether meet open preheat condition (temperature is low
When setting value, temperature condition meets；According to wheel load state judge 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
Closure, at this point, engine temperature lower than a certain setting value (such as 0 DEG C), aircraft ground (such as wheel load signal be low level 0V),
The enabled closure of switch 5 (such as enable signal is high level 28V) meets simultaneously, then heater plug controller 1 can then be mentioned to heater plug 2
For being allowed to carry out heating work for electricity output, meanwhile, there are also preheating instruction outputs all the way for heater plug controller 1.Once engine
3 measurement result of temperature sensor is more than that the temperature (as being higher than 0 DEG C) for opening preheating condition or aircraft wheel load transducer 4 measure
The result shows that aircraft is at ground (such as wheel load signal is not high level 28V), heater plug controller 1 can receive this information simultaneously
It disconnects to heater plug 2 for electricity output, but only when enabled switch 5 disconnects, (such as enable signal becomes 28V by high level as low level
0V), then heater plug controller 1 cannot be made to disconnect to heater plug 2 for electricity output.It is inputted and output logical relation such as Fig. 2 institute
Show.The namely input of heater plug controller 1 is there are three condition: temperature, whether ground, the power supply of engine electricity system with
It is no, and these three conditions need to meet simultaneously (temperature lower than setting value, on the ground, engine electricity system powered operation), in advance
Heat plug controller 1 could start to work, but as long as meeting any one of enable signal and engine temperature signal condition (hair
Motivation 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 detecte 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 control instructions lamp 6.Indicator light 6 refers to including pre- thermal light 6, failure
Show lamp 6, when controlling the work of heater plug 2, the pre- control of thermal light 6 is lighted, 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 be not it is independent, controlled by the output of engine controller, be that one kind is opened
Ring control, triggering and the condition for terminating pre-heating system work are relatively simple, increase engine control in aviation field application
The complexity of device processed.The invention proposes a kind of designs of the pre-heating system 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 can independent acquisition signal, progress so that the system of entire high power work becomes an independent system
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 method concept and skill of the invention
The improvement for the various unsubstantialities that art scheme carries out, it is within the scope of the present invention.
Claims (8)
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
It is connect respectively with heater plug, preheating controller, engine temperature sensing unit, aircraft wheel load transducer, for being supplied for each component
Electricity.
4. 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, shows heater plug working condition for control instructions lamp.
5. a kind of aviation piston engine pre-heating system as described in claim 1-4 is any, it is characterised in that: the engine
Power supply detection module judges the power supply shape of engine by detecting the unlatching closed state of engine power circuit control switch
State.
6. a kind of aviation piston engine pre-heating system as described in claim 1-4 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.
7. a kind of aviation piston engine pre-heating system as described in claim 1-4 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.
8. a kind of aviation piston engine pre-heating system as described in claim 1-4 is any, it is characterised in that: the aircraft wheel
On the ground whether load transducer is mounted on undercarriage wheel, for being judged aircraft according to load data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821052749.0U CN208578658U (en) | 2018-07-04 | 2018-07-04 | A kind of aviation piston engine pre-heating system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821052749.0U CN208578658U (en) | 2018-07-04 | 2018-07-04 | A kind of aviation piston engine pre-heating system |
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| Publication Number | Publication Date |
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| CN208578658U true CN208578658U (en) | 2019-03-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201821052749.0U Active CN208578658U (en) | 2018-07-04 | 2018-07-04 | A kind of aviation piston engine pre-heating system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108644038A (en) * | 2018-07-04 | 2018-10-12 | 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 CN201821052749.0U patent/CN208578658U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108644038A (en) * | 2018-07-04 | 2018-10-12 | 芜湖钻石航空发动机有限公司 | A kind of aviation piston engine pre-heating system |
| CN108644038B (en) * | 2018-07-04 | 2024-04-23 | 芜湖钻石航空发动机有限公司 | Aviation piston engine preheating system |
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