CN108644038B - Aviation piston engine preheating system - Google Patents
Aviation piston engine preheating system Download PDFInfo
- Publication number
- CN108644038B CN108644038B CN201810725056.1A CN201810725056A CN108644038B CN 108644038 B CN108644038 B CN 108644038B CN 201810725056 A CN201810725056 A CN 201810725056A CN 108644038 B CN108644038 B CN 108644038B
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- China
- Prior art keywords
- engine
- glow plug
- power supply
- preheating
- temperature
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- 238000001514 detection method Methods 0.000 claims abstract description 12
- 238000005259 measurement Methods 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 4
- 239000000110 cooling liquid Substances 0.000 claims description 3
- 239000010687 lubricating oil Substances 0.000 claims description 3
- 239000003921 oil Substances 0.000 claims 2
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- 238000007906 compression Methods 0.000 description 7
- 230000006835 compression Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000007858 starting material Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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- 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 an aviation piston engine preheating system, which comprises a preheating plug, a preheating plug controller, an engine temperature sensor, an aircraft wheel load sensor and an engine power supply detection module, wherein the engine temperature sensor, the aircraft wheel load sensor and the engine power supply detection module are respectively connected with the input end of the preheating plug controller, and the output end of the preheating plug controller is connected with the preheating plug; the glow plug controller controls the operation of the glow plug according to the received temperature, load and power supply state. The invention has the advantages that: the system can effectively preheat and reduce the influence of the too low temperature on the starting. The input conditions for starting and judging the working of the system are increased, so that the logic of the system is more strict, the misoperation performance is effectively reduced, and the safety and reliability of the system are improved.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to an aero-piston engine preheating system.
Background
The piston engine can be divided into compression ignition type and ignition type from the ignition mode, the compression ignition type is to make work by compression ignition expansion of the mixed gas in the cylinder, the ignition type is to make work by igniting the mixed gas by means of the ignition device, and under the condition of low ambient temperature, the process of overcoming resistance by the work generated in the compression process is longer due to low temperature of the mixed gas when the engine is started, and the heat loss is larger, so that the starting becomes difficult. In addition, the low temperature start of the compression engine is affected by the increase in viscosity of the lubricant, and the friction surfaces are not sufficiently pre-lubricated, thereby increasing the starting resistance of the engine. The common engine start is to supply power to the starter by the storage battery, so that the engine is dragged to rotate, and when the ambient temperature is low, the performance of the storage battery is also reduced, so that the starter cannot be supplied with power for a plurality of times for a long time. Under the influence of the main factors of the three aspects, the compression engine is very difficult to start in a low-temperature environment.
At present, although a preheating system matched with a compression ignition type piston engine can meet the low-temperature starting requirement of minus 30 ℃, the working logic of the preheating system is limited by an engine controller, the working of the preheating system is not independent and is controlled by the output of the engine controller, the preheating system is controlled in an open loop mode, the condition for triggering and ending the working of the preheating system is single, the accuracy and the stability are poor, and the problem of increasing the complexity of the engine controller exists when the preheating system is applied to the aviation field.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a preheating system of a piston engine.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: the preheating system of the aviation piston engine comprises a preheating plug, a preheating plug controller, an engine temperature sensor, an aircraft wheel load sensor and an engine power supply detection module, wherein the engine temperature sensor, the aircraft wheel load sensor and the engine power supply detection module are respectively connected with the input end of the preheating plug controller, and the output end of the preheating plug controller is connected with the preheating plug; the glow plug controller controls the operation of the glow plug according to the received temperature, load and power supply state.
The glow plug is mounted on the engine cylinder head for heating air adjacent the injector nozzle.
The power supply is respectively connected with the glow plug, the preheating controller, the engine temperature sensor and the aircraft wheel load sensor through the power supply switch and is used for supplying power to all the components.
After the power supply switch is closed, the engine temperature sensor and the aircraft wheel load sensor start to work, collected data are transmitted to the glow plug controller, after the temperature and the wheel load data meet the preheating conditions, the power supply state information of the engine is collected, and when the engine is in the power supply state, the glow plug controller controls the glow plug to supply power to the glow plug to work.
When the temperature of the engine exceeds the temperature of the preheating starting condition or the data acquired by the airplane wheel load sensor judges that the airplane is not on the ground, the glow plug controller controls the power supply of the glow plug to be disconnected, and the glow plug is stopped.
And the glow plug controller is connected with the indicator lamp and used for controlling the indicator lamp to display the working state of the glow plug.
The engine power supply detection module judges the power supply state of the engine by detecting the opening and closing states of the engine power circuit control switch.
The engine power utilization circuit control switch is used as an enabling switch of the preheating controller, one end of the enabling switch is connected with a power supply, and the other end of the enabling switch is respectively connected with input pins of the engine and the preheating controller.
The engine temperature sensor is used for collecting the temperature of a cooling liquid outlet of the engine or the temperature of a cylinder cover of the engine or the temperature of lubricating oil in the engine to represent the temperature of the engine.
The aircraft wheel load sensor is mounted on an aircraft landing gear wheel for determining whether the aircraft is on the ground based on the load data.
The invention has the advantages that: the system can effectively preheat, and reduce the influence of low temperature on starting; the glow plug controller outputs to the glow plug by simultaneously meeting a plurality of input conditions, so that the preheating system works; there are also a plurality of conditions for ending the operation of the preheating system, and the operation of the preheating system may be ended as long as one of these conditions is satisfied. By the system design, the whole high-power working system becomes an independent system, so that the dependence on other systems is reduced, and the complexity of an engine controller is reduced. As the input condition for starting the system and the judging condition for ending the system are increased, the logic of the system is more strict, the misoperation performance is effectively reduced, and the safety and the reliability of the system are improved.
Drawings
The contents of the drawings and the marks in the drawings of the present specification are briefly described as follows:
FIG. 1 is a schematic diagram of a preheating system according to the present invention;
FIG. 2 is a logic diagram of the control output of the glow plug controller of the present invention.
The labels in the above figures are: 1. a glow plug controller; 2. a glow plug; 3. an engine temperature sensor; 4. an aircraft wheel load sensor; 5. enabling the switch; 6. an indicator light; 7. a power supply; 8. and a power supply switch.
Detailed Description
The following detailed description of the invention refers to the accompanying drawings, which illustrate preferred embodiments of the invention in further detail.
The preheating system of the aviation piston engine comprises a preheating plug 2, a preheating plug controller 1, an engine temperature sensor 3, an aircraft wheel load sensor 4 and an engine power supply detection module, wherein the engine temperature sensor 3, the aircraft wheel load sensor 4 and the engine power supply detection module are respectively connected with the input end of the preheating plug controller 1, and the output end of the preheating plug controller 1 is connected with the preheating plug 2; the glow plug controller 1 controls the operation of the glow plug 2 in dependence on the received temperature, load, and power conditions.
A glow plug 2 is mounted on the engine cylinder head for heating the air in the vicinity of the injector nozzle.
The engine temperature sensor 3 is installed on the engine body, and the engine temperature sensor 3 collects the temperature of a cooling liquid outlet of the engine or the temperature of an engine cylinder cover or the temperature of lubricating oil in the engine to be used for representing the temperature of the engine.
An aircraft wheel load sensor 4 is mounted on the aircraft landing gear wheel for determining whether the aircraft is on the ground based on the load data.
The engine power supply detection module judges the power supply state of the engine by detecting the opening and closing states of the engine circuit control switch.
The power supply 7 is respectively connected with the glow plug controller 1, the glow plug 2, the engine temperature sensor 3 and the aircraft wheel load sensor 4 through the power supply switch 8 and is used for supplying power to all the components, so that the sensors and the controller work electrically.
The principle comprises the following steps: after the power supply switch 8 is closed, the engine temperature sensor 3 and the aircraft wheel load sensor 4 start to work, collected data are transmitted to the glow plug controller 1, after the temperature and wheel load data meet the preheating condition, engine power supply state information is collected, and when the engine is in a power supply state, the glow plug controller 1 controls the glow plug 2 to supply power to the glow plug to work. At this time, the power supply operation of the glow plug 2 is controlled when the engine temperature, the aircraft on the ground and the enabling switch 5 meet the conditions, otherwise, any condition is not met, and the glow plug 2 does not operate. After the glow plug 2 works, when the engine temperature exceeds the temperature of the preheating starting condition or the data acquired by the aircraft wheel load sensor 4 judges that the aircraft is not on the ground, the glow plug controller 1 controls the power supply of the glow plug 2 to be disconnected, the glow plug 2 stops working, and the preheating is finished.
The engine power supply detection module can be used for detecting the power supply state of the engine power utilization system, the engine power utilization circuit control switch can be used as the enabling switch 5 of the preheating controller by detecting the power supply state of the engine power utilization system, the enabling switch 5 is the engine main electric door arranged on the aircraft and is used for supplying power to the engine power utilization system, one end of the enabling switch 5 is connected with the power supply 7, the other end of the enabling switch is respectively connected with the engine power utilization system and the input pins of the preheating plug controller, and the power supply 7 is used for supplying power to the preheating system. Thus, the power supply state can be determined by collecting high-low level signals through the pins of the glow plug controller 1, for example, when the enabling switch 5 is closed, the engine is powered by the power system, and at the moment, the high level of the pins of the glow plug controller 1 is obtained; when the enabling switch 5 is turned off, the pin is at a low level, and the power supply state is judged according to the level signal.
When the power supply switch 8 is closed, the engine temperature sensor 3 and the airplane wheel load sensor 4 are powered on to feed back measurement results to the glow plug controller 1, the glow plug controller 1 can judge whether the two conditions meet the condition of starting the preheating (when the temperature is lower than a set value, the temperature condition is met, whether the airplane is on the ground or not according to the wheel load state, the condition is met when the airplane is on the ground) through calculation, if the condition is met, the glow plug controller 1 can further judge whether the enabling switch 5 is closed, namely whether the engine is powered on or not, if the condition is met, the engine temperature is lower than a certain set value (such as 0 ℃) at the moment, the airplane is on the ground (such as a low level 0V) at the moment, and the enabling switch 5 is closed (such as a high level 28V) at the moment, then the glow plug controller 1 can provide power supply output for the glow plug 2 to enable the glow plug to perform heating operation, and meanwhile, the glow plug controller 1 also has an indication output. Once the engine temperature sensor 3 measurement exceeds the temperature at which the warm-up condition is turned on (e.g., above 0 ℃) or the aircraft wheel load sensor 4 measurement indicates that the aircraft is not on the ground (e.g., the wheel load signal is high 28V), the glow plug controller 1 receives this information and turns off the power output to the glow plug 2, but only if the enable switch 5 is turned off (e.g., the enable signal changes from high 28V to low 0V), the glow plug controller 1 cannot be caused to turn off the power output to the glow plug 2. The logical relationship between inputs and outputs is shown in fig. 2. That is, the inputs to the glow plug controller 1 have three conditions: the glow plug controller 1 can start to operate if the temperature, whether the engine is on the ground or whether the engine is powered by the power system or not, and the three conditions need to be satisfied simultaneously (the temperature is lower than a set value, the engine is on the ground or the engine is powered by the power system), but the glow plug controller 1 can end to operate if any one of the enabling signal and the engine temperature signal (the engine temperature is higher than the set value or the aircraft is not on the ground) is satisfied.
The glow plug controller 1 can detect whether the glow plug 2 has a short circuit or open circuit fault condition through an output port or a detection module, and once such a fault is detected, the glow plug controller 1 outputs a fault indication signal to the indicator lamp 6 for controlling the indicator lamp 6 to display the working state of the glow plug 2. The indication lamp 6 comprises a preheating indication lamp 6 and a fault indication lamp 6, when the preheating plug 2 is controlled to work, the preheating indication lamp 6 is controlled to be turned on, and when a fault exists, the fault indication lamp 6 is turned on. A preheat indicator light 6 is mounted to the avionics system of the aircraft to indicate a preheat condition.
The preheating system in the prior art is not independent in operation and is controlled by the output of the engine controller, is open-loop control, has single conditions for triggering and ending the operation of the preheating system, and increases the complexity of the engine controller when applied to the field of aviation. The invention provides an independent closed-loop control preheating system design, which enables the preheating system to work by simultaneously meeting a plurality of input conditions to a preheating plug controller 1 and outputting the output of the preheating plug controller 1 to a preheating plug 2; there are also a plurality of conditions for ending the operation of the preheating system, and the operation of the preheating system may be ended as long as one of these conditions is satisfied. By the system design, the whole high-power working system becomes an independent system, signals can be independently collected, logic operation can be carried out, and the signals can be output according to operation results, so that the dependence on other systems is reduced, and the complexity of an engine controller is reduced. As the input condition for starting the system and the judging condition for ending the system are increased, the logic of the system is more strict, the misoperation performance is effectively reduced, and the safety and the reliability of the system are improved.
It is obvious that the specific implementation of the present invention is not limited by the above-mentioned modes, and that it is within the scope of protection of the present invention only to adopt various insubstantial modifications made by the method conception and technical scheme of the present invention.
Claims (6)
1. An aero-piston engine preheating system comprising a glow plug, characterized by: the engine temperature sensor, the aircraft wheel load sensor and the engine power supply detection module are respectively connected with the input end of the glow plug controller, and the output end of the glow plug controller is connected with the glow plug; the glow plug controller controls the work of the glow plug according to the received temperature, load and power supply state; the glow plug is arranged on the engine cylinder cover and is used for heating air near the oil injection hole of the oil injector; the power supply is respectively connected with the glow plug, the preheating controller, the engine temperature sensor and the aircraft wheel load sensor through the power supply switch and is used for supplying power to all the components; after the power supply switch is closed, the engine temperature sensor and the aircraft wheel load sensor start to work, collected data are transmitted to the glow plug controller, after the temperature and the wheel load data meet the preheating conditions, the power supply state information of the engine is collected, and when the engine is in the power supply state, the glow plug controller controls the glow plug to supply power to the glow plug to work; when the temperature of the engine exceeds the temperature of a preheating starting condition or the data acquired by an airplane wheel load sensor judges that the airplane is not on the ground, the glow plug controller controls the power supply of the glow plug to be disconnected, and the glow plug is stopped;
A power supply switch is arranged between the power supply and the preheating system to control on-off, when the power supply switch is closed, an engine temperature sensor and an aircraft wheel load sensor are powered on to feed back measurement results to the glow plug controller, the glow plug controller can judge whether the two conditions meet the condition of starting preheating through calculation according to the feedback results of the sensors, and when the temperature is lower than a set value, the temperature condition is met; judging whether the aircraft is on the ground or not according to the wheel load state, wherein the condition is met on the ground; if yes, the glow plug controller further judges whether the enabling switch is closed, namely whether the engine is powered, if yes, at the moment, the temperature of the engine is lower than a certain set value, the aircraft is on the ground, and the enabling switch is closed and meets the condition simultaneously, then the glow plug controller provides a power supply output for the glow plug to heat the glow plug, and meanwhile, the glow plug controller also provides a path of preheating indication output; once the engine temperature sensor measurement exceeds the temperature of the on-warm condition (or the aircraft wheel load sensor measurement indicates that the aircraft is not on the ground), the glow plug controller receives this information and disconnects the power output to the glow plug, but only when the enable switch is turned off, the glow plug controller cannot be caused to disconnect the power output to the glow plug.
2. An aero-piston engine preheating system as claimed in claim 1, wherein: and the glow plug controller is connected with the indicator lamp and used for controlling the indicator lamp to display the working state of the glow plug.
3. An aero-piston engine preheating system according to any of claims 1-2, wherein: the engine power supply detection module judges the power supply state of the engine by detecting the opening and closing states of the engine power circuit control switch.
4. An aero-piston engine preheating system according to any of claims 1-2, wherein: the engine power utilization circuit control switch is used as an enabling switch of the preheating controller, one end of the enabling switch is connected with a power supply, and the other end of the enabling switch is respectively connected with input pins of the engine and the preheating controller.
5. An aero-piston engine preheating system according to any of claims 1-2, wherein: the engine temperature sensor is used for collecting the temperature of a cooling liquid outlet of the engine or the temperature of a cylinder cover of the engine or the temperature of lubricating oil in the engine to represent the temperature of the engine.
6. An aero-piston engine preheating system according to any of claims 1-2, wherein: the aircraft wheel load sensor is mounted on an aircraft landing gear wheel for determining whether the aircraft is on the ground based on the 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 CN108644038A (en) | 2018-10-12 |
| CN108644038B true CN108644038B (en) | 2024-04-23 |
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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 (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4506145A (en) * | 1978-07-10 | 1985-03-19 | Isuzu Motors Ltd. | Device for controlling engine preheating |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100380069B1 (en) * | 2000-09-20 | 2003-04-14 | 현대자동차주식회사 | A method for controlling glow plugs for diesel engine |
-
2018
- 2018-07-04 CN CN201810725056.1A patent/CN108644038B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4506145A (en) * | 1978-07-10 | 1985-03-19 | Isuzu Motors Ltd. | Device for controlling engine preheating |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN108644038A (en) | 2018-10-12 |
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