CN205028767U - Aviation piston engine integrated form high energy ignition coil - Google Patents
Aviation piston engine integrated form high energy ignition coil Download PDFInfo
- Publication number
- CN205028767U CN205028767U CN201520817316.XU CN201520817316U CN205028767U CN 205028767 U CN205028767 U CN 205028767U CN 201520817316 U CN201520817316 U CN 201520817316U CN 205028767 U CN205028767 U CN 205028767U
- Authority
- CN
- China
- Prior art keywords
- armature winding
- primary winding
- ecu
- magnetizing
- winding
- 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.)
- Expired - Fee Related
Links
Landscapes
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The utility model provides an aviation piston engine integrated form high energy ignition coil, primary winding includes a primary winding and the 2nd primary winding, a primary winding and the 2nd primary winding's the work of magnetizing is all controlled according to the operating condition of gathering by automatically controlled unit ECU, when the engine is in the cold start situation, by a primary winding and the work of magnetizing jointly of the 2nd primary winding, and obtains great energy when making the spark plug light a fire, and when the aircraft took off afterwards and remains stable the flight situation, automatically controlled unit ECU then made the single primary winding work of magnetizing to keep lower energy consumption, and a primary winding and the 2nd primary winding look require or the one of which can work independently when breaking down, thereby guarantee the engine and stablize continued work. Because magnetizing of a primary winding and the 2nd primary winding can hocket, therefore can eliminate the required time of magnetizing of continuous ignition to realize lasting the action of igniteing.
Description
Technical field
The utility model relates to the technical field of aviation piston type engine, is a kind of aviation piston type engine integrated form high energy ignition coil specifically.
Background technology
At present, domestic small-sized aviation piston type engine all adopts diaphragm type carburator oil supply system, because carburetor is by trunnion vacuum degree and mechanical system metering fuel oil, thus can not meet engine climbing, cruise and under the various flight working condition such as underriding, under various environmental condition to the demand of combustion mixture optimal air-fuel ratio.And fuel oil electric-controlled injection technology can improve fuel-oil atmozation quality, the fuel tolerance meeting aviation piston type engine require and in flight course to the change demand of power.
Accurately can control the air-fuel ratio of engine under various operating mode by electric-controlled injection technology, make engine remain preferably performance, thus make the performance of engine each side, particularly high-level performance improves.But the electronic control technology of the aviation piston type engine of present small displacement still exists some problems, and when engine cold-start, existing ignition coil is subject to the restriction of fixing turn ratio, the requirement of required high ignition energy during cold start-up cannot be met.And the work of secondary winding depends on the igniting of magnetizing of single armature winding, and armature winding needs the time of magnetizing between twice igniting excites, and thus the ignition coil of prior art cannot be accomplished continually repeatedly to light a fire.
Utility model content
It is a kind of aviation piston type engine integrated form high energy ignition coil specifically that the technical problems to be solved in the utility model is to provide.
The technical scheme that the utility model is taked for the technical problem existed in solution known technology is:
Aviation piston type engine integrated form high energy ignition coil of the present utility model, comprise the armature winding and secondary winding that are around in same magnetic core, armature winding is connected with ECU (Electrical Control Unit) ECU with power supply respectively and magnetizes under the control of ECU (Electrical Control Unit) ECU, secondary winding is connected with spark plug, ECU (Electrical Control Unit) ECU is connected with multiple transducer, and armature winding comprises the first armature winding and the second armature winding; First armature winding is connected with ECU (Electrical Control Unit) ECU with power supply respectively with the second armature winding, and the first armature winding, the second armature winding and secondary winding are around in same magnetic core.
The utility model can also adopt following technical measures:
The first described armature winding is identical with the number of turn of the second armature winding and direction of winding is identical.
The transducer that described ECU (Electrical Control Unit) ECU connects comprises engine speed sensor, barometric pressure sensor, cooler-water temperature transducer and engine load sensor.
The advantage that the utility model has and good effect are:
In aviation piston type engine integrated form high energy ignition coil of the present utility model, armature winding comprises the first armature winding and the second armature winding, the time of magnetizing of the first armature winding and the second armature winding is all controlled according to the actual condition collected by ECU (Electrical Control Unit) ECU, when engine is in cold start-up situation, jointly to be magnetized work by the first armature winding and the second armature winding, but obtain larger energy during plug ignition; And when after aircraft takeoff and when keeping stabilized flight situation, ECU (Electrical Control Unit) ECU then makes single armature winding magnetize work, thus keep comparatively low energy consumption, and the first armature winding and the second armature winding depending on require or one breaks down time can work independently, thus ensure engine stabilizer continuous firing.Because the first armature winding and magnetizing of the second armature winding can be hocketed, thus can eliminate magnetizing the time needed for continuous ignition, thus realize constant ignition action.
Accompanying drawing explanation
Fig. 1 is the circuit diagram of aviation piston type engine integrated form high energy ignition coil of the present utility model.
Embodiment
Referring to the drawings and specific embodiments, the utility model is described in detail.
As shown in Figure 1, aviation piston type engine integrated form high energy ignition coil of the present utility model, comprise the armature winding and secondary winding that are around in same magnetic core, armature winding is connected with ECU (Electrical Control Unit) ECU with power supply respectively and magnetizes under the control of ECU (Electrical Control Unit) ECU, secondary winding is connected with spark plug, ECU (Electrical Control Unit) ECU is connected with multiple transducer, and armature winding comprises the first armature winding and the second armature winding; First armature winding 1a is connected with ECU (Electrical Control Unit) ECU with power supply respectively with the second armature winding 1b, and the first armature winding, the second armature winding and secondary winding 2 are around in same magnetic core.
First armature winding is identical with the number of turn of the second armature winding and direction of winding is identical, the first armature winding and the second armature winding co-operation when cold start-up is lighted a fire, thus form the voltage of when single armature winding works 1.5 times at secondary winding end, thus ensure that the normal work of spark plug.
The transducer that ECU (Electrical Control Unit) ECU connects comprises engine speed sensor, barometric pressure sensor, cooler-water temperature transducer and engine load sensor, and the data collected by each transducer judge engine operating state at that time.
When ignition coil of the present utility model runs, comprise the following steps:
A, ECU (Electrical Control Unit) ECU process each numerical value that engine speed sensor, barometric pressure sensor, cooler-water temperature transducer and engine load sensor collect respectively, and by each numerical value compared with corresponding each cold start parameter;
When numerical value in B, previous step conforms to cold start parameter, the judgement conclusion of ECU (Electrical Control Unit) ECU is system and is in cold start-up, first armature winding and the second armature winding magnetize work simultaneously, secondary winding produces high voltage under the acting in conjunction of the first armature winding and the second armature winding, makes plug ignition;
The numerical value that C, ECU (Electrical Control Unit) ECU continue each transducer to collect, respectively compared with operational factor, when each numerical value does not all meet operational factor, keeps the first armature winding and the second armature winding co-operation;
D, when the data collected by each transducer all meet operational factor, ECU (Electrical Control Unit) ECU makes the arbitrary armature winding in the first armature winding and the second armature winding magnetize work, and another armature winding is had a rest, secondary coil produces high voltage under the effect of single armature winding, makes plug ignition.
The first armature winding in step D and the second armature winding alternation.
When engine is in cold start-up situation, jointly to be magnetized work by the first armature winding and the second armature winding, and make to obtain during plug ignition larger energy; And when after aircraft takeoff and when keeping stabilized flight situation, ECU (Electrical Control Unit) ECU then makes single armature winding magnetize work, thus keep comparatively low energy consumption, and the first armature winding and the second armature winding depending on require or one breaks down time can work independently, thus ensure engine stabilizer continuous firing.Because the first armature winding and magnetizing of the second armature winding can be hocketed, thus can eliminate magnetizing the time needed for continuous ignition, thus realize constant ignition action.
Cold start parameter is: engine speed is less than or equal to 500 revs/min, atmospheric pressure is standard atmospheric pressure, the water temperature of cooling water is not zero higher than 50 DEG C or throttle opening.When each data all meet cold start parameter, the first armature winding and the second armature winding co-operation.
Operational factor is: engine speed be greater than 500 revs/min, atmospheric pressure be less than or equal to standard atmospheric pressure, cooling water water temperature higher than 90 DEG C and throttle opening is greater than zero.When meeting operational factor, the first armature winding or the second armature winding can be specified to work independently, or the first armature winding and the second armature winding alternation.
The above, it is only preferred embodiment of the present utility model, not any pro forma restriction is done to the utility model, although the utility model with preferred embodiment openly as above, but, and be not used to limit the utility model, any those skilled in the art, do not departing within the scope of technical solutions of the utility model, certainly the technology contents of announcement can be utilized to make a little change or modification, become the Equivalent embodiments of equivalent variations, in every case be the content not departing from technical solutions of the utility model, according to any simple modification that technical spirit of the present utility model is done above embodiment, equivalent variations and modification, all belong in the scope of technical solutions of the utility model.
Claims (3)
1. an aviation piston type engine integrated form high energy ignition coil, comprise the armature winding and secondary winding that are around in same magnetic core, armature winding is connected with ECU (Electrical Control Unit) ECU with power supply respectively and magnetizes under the control of ECU (Electrical Control Unit) ECU, secondary winding is connected with spark plug, ECU (Electrical Control Unit) ECU is connected with multiple transducer, it is characterized in that: armature winding comprises the first armature winding and the second armature winding; First armature winding is connected with ECU (Electrical Control Unit) ECU with power supply respectively with the second armature winding, and the first armature winding, the second armature winding and secondary winding are around in same magnetic core.
2. aviation piston type engine integrated form high energy ignition coil according to claim 1, is characterized in that: the first armature winding is identical with the number of turn of the second armature winding and direction of winding is identical.
3. aviation piston type engine integrated form high energy ignition coil according to claim 1 and 2, is characterized in that: the transducer that ECU (Electrical Control Unit) ECU connects comprises engine speed sensor, barometric pressure sensor, cooler-water temperature transducer and engine load sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520817316.XU CN205028767U (en) | 2015-10-22 | 2015-10-22 | Aviation piston engine integrated form high energy ignition coil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520817316.XU CN205028767U (en) | 2015-10-22 | 2015-10-22 | Aviation piston engine integrated form high energy ignition coil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205028767U true CN205028767U (en) | 2016-02-10 |
Family
ID=55261282
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520817316.XU Expired - Fee Related CN205028767U (en) | 2015-10-22 | 2015-10-22 | Aviation piston engine integrated form high energy ignition coil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205028767U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105304297A (en) * | 2015-10-22 | 2016-02-03 | 天津大学 | Integrated high-energy ignition coil of aviation piston type engine and operation method thereof |
-
2015
- 2015-10-22 CN CN201520817316.XU patent/CN205028767U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105304297A (en) * | 2015-10-22 | 2016-02-03 | 天津大学 | Integrated high-energy ignition coil of aviation piston type engine and operation method thereof |
| CN105304297B (en) * | 2015-10-22 | 2017-11-10 | 天津大学 | The operation method of aviation piston type engine integrated form high energy ignition coil |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108252809B (en) | Power control system and aircraft | |
| CN106704012B (en) | Methanol-Diesel Dual-Fuel Engine control system and method | |
| CN103114951B (en) | Controlling method of gasoline direct injection engine optimal ignition advance angle | |
| CN102146853B (en) | Control system for natural gas/gasoline dual-fuel engine | |
| CN103782025A (en) | Ignition control apparatus for internal combustion engine | |
| CN103998768B (en) | Igniting correct timing controller and ITCS Ignition Timing Control System | |
| CN103557071A (en) | System and method for utilizing gas cold energy to improve engine heat efficiency and achieve aims of saving energy and reducing emission | |
| CN102146854B (en) | Method for correcting ignition timing of natural gas and gasoline dual fuel engine | |
| CN102602294A (en) | Method and device for displaying fuel economy state of car engine | |
| CN205028767U (en) | Aviation piston engine integrated form high energy ignition coil | |
| CN104373207A (en) | Lean-combustion gas dual-fuel ignition type internal combustion engine system and control method | |
| CN101619684A (en) | Design of electric control system ECU of CNG engine | |
| CN202033658U (en) | Measurement and control system using oil field and coalfield associated gas as power and used for oil pumping unit and air exhauster | |
| CN105304297B (en) | The operation method of aviation piston type engine integrated form high energy ignition coil | |
| CN102396148B (en) | Power-generation control device | |
| CN101865020B (en) | Ignition type internal-combustion engine system for on-line hydrogen production and local hydrogen enrichment and control method | |
| CN109184929A (en) | A kind of dual fuel engine ignition integrated system and its control method | |
| CN114592977A (en) | Dual-fuel engine control method and system | |
| CN205047346U (en) | Aviation piston engine ignition drive circuit's anti -interference structure | |
| CN218542434U (en) | Aviation heavy oil piston engine carburetor heating device | |
| CN101922397B (en) | Ignition system of engine and control method thereof | |
| US20180274463A1 (en) | Fast torque control with electric accessories | |
| CN204921175U (en) | Natural gas engine's electrical system | |
| CN204299688U (en) | A kind of lean-burn gas double fuel ignition type internal-combustion engine system | |
| CN202914191U (en) | Automotive energy saving and emission reduction manual/automatic electric control system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160922 Address after: 300072 Tianjin City, Nankai District Wei Jin Road No. 92 Patentee after: Tianjin internal combustion engine Research Institute (Tianjin Motorcycle Technology Center) Patentee after: Tianjin University Address before: 300072 Tianjin City, Nankai District Wei Jin Road No. 92 Patentee before: Tianjin University |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160210 Termination date: 20161022 |