CN112727621A - Oil injection control system and method for two-stroke aviation piston engine - Google Patents
Oil injection control system and method for two-stroke aviation piston engine Download PDFInfo
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- 238000002347 injection Methods 0.000 title claims abstract description 174
- 239000007924 injection Substances 0.000 title claims abstract description 174
- 238000000034 method Methods 0.000 title claims abstract description 27
- 239000000446 fuel Substances 0.000 claims abstract description 77
- 238000012545 processing Methods 0.000 claims description 11
- 238000001914 filtration Methods 0.000 claims description 10
- 238000012937 correction Methods 0.000 claims description 9
- 238000005259 measurement Methods 0.000 claims description 5
- 239000007921 spray Substances 0.000 claims description 3
- 230000008719 thickening Effects 0.000 claims description 3
- 230000001276 controlling effect Effects 0.000 claims 4
- 230000001105 regulatory effect Effects 0.000 claims 1
- 239000003921 oil Substances 0.000 description 50
- 239000000295 fuel oil Substances 0.000 description 6
- 238000000889 atomisation Methods 0.000 description 5
- 230000002000 scavenging effect Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/30—Controlling fuel injection
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Abstract
The invention provides an oil injection control system and method for a two-stroke aviation piston engine, wherein the system comprises the following components: the data measuring unit is used for acquiring data of the rotating speed, the opening of a throttle valve, the temperature of an air cylinder and the exhaust temperature; the control unit judges the working state of the engine according to the acquired rotating speed data of the engine, calculates the fuel injection quantity and distributes the fuel injection proportion of the corresponding air inlet channel and the in-cylinder direct injection; the execution unit is used for starting the oil injection driving circuit to finish the oil injection process; the data measuring unit is connected with the execution unit through the control unit, and the fuel injection control system completes the distribution of the proportion of the air inlet channel injection and the in-cylinder direct injection fuel injection according to different working conditions so as to complete the fuel injection control of the engine under the full-operation working condition.
Description
[ technical field ] A method for producing a semiconductor device
The invention relates to the technical field of fuel injection control of two-stroke piston aircraft engines, in particular to a fuel injection control system and method of a two-stroke aircraft piston engine.
[ background of the invention ]
Fuel injection control can directly affect engine fuel atomization and fuel economy, and therefore fuel injection control is a key factor for efficient engine operation. At present, an aviation piston engine mainly adopts an air inlet channel for oil injection, the oil injection control of the air inlet channel is simple and easy to atomize, but the oil injection process and the scavenging process of a two-stroke piston engine are strongly coupled, so that the fuel oil capture rate is low, and the fuel oil economy is deteriorated and the hydrocarbon emission is serious.
The direct injection type fuel supply technology can decouple the fuel injection and scavenging processes, and effectively improves the fuel economy. However, the injection phase and the injection time of the direct injection technology are limited by the opening time of the scavenging port, and in addition, the problem of difficult starting due to poor atomization caused by too low temperature in the cylinder during cold starting is solved. The traditional direct injection type fuel supply system for the piston engine is complex in system and heavy in weight due to the fact that high-pressure injection is adopted, and cannot be applied to a small two-stroke aviation piston engine. At present, the patent of the technical scheme for realizing direct injection in the cylinder by the combined control of direct injection in the cylinder and injection in an air inlet passage aiming at the two-stroke aviation piston engine is provided.
Accordingly, there is a need to develop a fuel injection control system and method for a two-stroke aviation piston engine that addresses the deficiencies of the prior art to address or mitigate one or more of the problems set forth above.
[ summary of the invention ]
In view of the above, the invention provides an oil injection control system and method for a two-stroke aviation piston engine, which divide the working state of the engine into a cold start working condition, a warm working condition, a small load working condition, a medium load working condition and a large load working condition by collecting a rotating speed signal, a throttle opening and a temperature signal, and complete the distribution of the proportion of the fuel injection of the air inlet channel and the fuel injection of the direct injection in the cylinder according to different working conditions so as to complete the oil injection control of the full-operation working condition of the engine.
In one aspect, the present invention provides a fuel injection control system for a two-stroke aviation piston engine, the system comprising:
the data measuring unit is used for acquiring data of the rotating speed, the opening of a throttle valve, the temperature of an air cylinder and the exhaust temperature;
the control unit judges the working state of the engine according to the acquired rotating speed data of the engine, calculates the fuel injection quantity and distributes the fuel injection proportion of the corresponding air inlet channel and the in-cylinder direct injection;
the execution unit is used for starting the oil injection driving circuit to finish the oil injection process;
the data measurement unit is connected with the execution unit through the control unit.
The above aspect and any possible implementation manner further provide an implementation manner, wherein the data measuring unit comprises a rotation speed sensor, a temperature sensor and a throttle opening degree signal feedback device;
the rotating speed sensor is used for acquiring the rotating speed of the engine;
the temperature sensor is used for measuring the air inlet temperature, the cylinder temperature and the exhaust temperature of the engine;
the throttle opening signal feedback device is a steering engine capable of providing position feedback, a motor capable of providing position feedback or a single position sensor capable of providing a throttle position signal.
The above aspects and any possible implementation manner further provide an implementation manner, where the control unit includes a single chip, a digital signal processing circuit and an amplifying and filtering circuit, one end of the digital signal processing circuit is connected to the rotation speed sensor, the other end of the digital signal processing circuit is connected to the single chip, one end of the amplifying and filtering circuit is simultaneously connected to the temperature sensor and the throttle opening signal feedback device, and the other end of the amplifying and filtering circuit is connected to the single chip.
The above aspect and any possible implementation further provide an implementation, where the control unit further includes a power supply circuit and an actuator power driving circuit; the power circuit is connected with the single chip microcomputer, one end of the actuator power driving circuit is connected with the single chip microcomputer, and the other end of the actuator power driving circuit is connected with the execution unit.
The above aspects and any possible implementation manners further provide an implementation manner, the power supply circuit provides a stable voltage for the whole system and provides overcurrent and overvoltage protection for the system, and the actuator power driving circuit receives a control signal from the single chip microcomputer to complete control of the corresponding actuator.
The above-mentioned aspects and any possible implementation manners further provide an implementation manner, and the single chip microcomputer judges the operation condition of the engine according to the collected rotating speed, temperature and throttle position signals, calculates the fuel injection phase and the fuel injection quantity, and distributes the ratio of the port injection to the in-cylinder direct injection fuel injection.
The above aspect and any possible implementation further provide an implementation in which the execution unit includes an oil pump, an oil injector, and an igniter.
The above-mentioned aspect and any possible implementation manner further provide a control method of an aviation piston engine in-cylinder direct fuel injection system, wherein the control method comprises the following steps:
s1: collecting data of the rotating speed of the engine, the opening of a throttle valve, the temperature of an air cylinder and the exhaust temperature, and judging the working state of the engine;
s2: under corresponding working conditions, inquiring the fuel injection quantity according to the rotating speed of the engine and the position of a throttle valve, and correcting the fuel injection quantity according to the state data of the engine;
s3: under the corresponding working condition, the combination mode of direct injection in the cylinder or air inlet channel injection or direct injection in the cylinder and air inlet channel injection is judged, the ratio of the fuel injection in the air inlet channel and the fuel injection in the direct injection is distributed, and the corresponding fuel injector is controlled to inject fuel.
As to the above-mentioned aspect and any possible implementation manner, there is further provided an implementation manner, where the S2 specifically includes:
s21: judging whether the cold start is performed, if so, performing S22, otherwise, performing S23;
s22: judging whether the engine is warmed up, if so, performing S23, and otherwise, performing S3;
s23: performing basic oil injection map table lookup;
s24: cold starting or warm-up thickening;
s25: performing oil injection correction according to the boundary parameters of the engine;
s26: and controlling the air inlet channel oil sprayer to spray oil.
As to the above-mentioned aspect and any possible implementation manner, there is further provided an implementation manner, where the S3 specifically includes:
s31: judging the load condition, namely a small load, performing S3211, performing S3221 when the load is large;
s3211: performing basic oil injection map table lookup;
s3212: performing oil injection correction according to the boundary parameters of the engine;
s3213: controlling the in-cylinder semi-direct-injection oil injector to inject oil;
s3221: performing basic oil injection map table lookup;
s3222: performing oil injection correction according to the boundary parameters of the engine;
s3223: proportionally distributing oil injection of an air inlet channel and semi-direct injection in a cylinder;
s3224: and controlling the air inlet channel and the in-cylinder semi-direct injection injector to inject oil.
Compared with the prior art, the invention can obtain the following technical effects:
(1) the problems of limited oil injection phase and oil injection time and poor cold start fuel atomization in the direct injection technology are solved through a combined control mode of direct injection in a cylinder and air inlet channel injection; meanwhile, the advantage of direct injection fuel economy is integrated;
(2) according to the invention, through controlling one oil sprayer arranged on the air inlet channel and a plurality of oil sprayers arranged on the cylinders, the flexible switching of three oil spraying modes of direct injection in the cylinders, air inlet channel injection, direct injection in the cylinders and air inlet channel injection combination can be realized, so that the requirements of the engine under different working conditions are met.
Of course, it is not necessary for any one product in which the invention is practiced to achieve all of the above-described technical effects simultaneously.
[ description of the drawings ]
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a block diagram of a fuel injection control circuit according to an embodiment of the present invention;
FIG. 2 is a diagram of an exemplary fuel injection system for a two-cylinder, two-stroke aviation piston engine provided in accordance with an embodiment of the present invention;
FIG. 3 is a timing diagram illustrating fuel injection control provided by one embodiment of the present invention;
fig. 4 is a flow chart of fuel injection control according to the present invention.
[ detailed description ] embodiments
For better understanding of the technical solutions of the present invention, the following detailed descriptions of the embodiments of the present invention are provided with reference to the accompanying drawings.
It should be understood that the described embodiments are only some embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the examples of the present invention and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
The invention provides an oil injection control system and method of a two-stroke aviation piston engine, which divide the working state of the engine into a cold start working condition, a warm working condition, a small load working condition, a medium load working condition and a large load working condition by collecting a rotating speed signal, the opening of a throttle valve and a temperature signal, and complete the distribution of the injection proportion of an air inlet channel and the direct injection fuel oil according to different working conditions so as to complete the oil injection control of the full-running working condition of the engine. The system comprises:
the data measuring unit is used for acquiring data of the rotating speed, the opening of a throttle valve, the temperature of an air cylinder and the exhaust temperature;
the control unit judges the working state of the engine according to the acquired rotating speed data of the engine, calculates the fuel injection quantity and distributes the fuel injection proportion of the corresponding air inlet channel and the in-cylinder direct injection;
the execution unit is used for starting the oil injection driving circuit to finish the oil injection process;
the data measurement unit is connected with the execution unit through the control unit.
The data measuring unit comprises a rotating speed sensor, a temperature sensor and a throttle opening degree signal feedback device;
the rotating speed sensor is used for acquiring the rotating speed of the engine;
the temperature sensor is used for measuring the air inlet temperature, the cylinder temperature and the exhaust temperature of the engine;
the throttle opening signal feedback device is a steering engine capable of providing position feedback, a motor capable of providing position feedback or a single position sensor capable of providing a throttle position signal.
The control unit comprises a singlechip, a digital signal processing circuit, an amplifying and filtering circuit, a power circuit and an actuator power driving circuit; the power supply circuit is connected with the single chip microcomputer, one end of the actuator power driving circuit is connected with the single chip microcomputer, the other end of the actuator power driving circuit is connected with the execution unit, one end of the digital signal processing circuit is connected with the rotating speed sensor, the other end of the digital signal processing circuit is connected with the single chip microcomputer, one end of the amplification filtering circuit is simultaneously connected with the temperature sensor and the throttle opening degree signal feedback device, and the other end of the. The power circuit provides stable voltage for the whole system and overcurrent and overvoltage protection for the system, and the actuator power driving circuit receives a control signal from the single chip microcomputer to complete control of the corresponding actuator. The single chip microcomputer judges the operation condition of the engine according to the collected rotating speed, temperature and throttle position signals, calculates the oil injection phase and the oil injection quantity and distributes the ratio of air inlet channel injection to in-cylinder direct injection fuel injection.
The execution unit comprises an oil pump, an oil injector and an igniter.
A control method for an aviation piston engine in-cylinder direct fuel injection system, the control method comprising the steps of:
s1: collecting data of the rotating speed of the engine, the opening of a throttle valve, the temperature of an air cylinder and the exhaust temperature, and judging the working state of the engine;
s2: under corresponding working conditions, inquiring the fuel injection quantity according to the rotating speed of the engine and the position of a throttle valve, and correcting the fuel injection quantity according to the state data of the engine;
s3: under the corresponding working condition, the combination mode of direct injection in the cylinder or air inlet channel injection or direct injection in the cylinder and air inlet channel injection is judged, the ratio of the fuel injection in the air inlet channel and the fuel injection in the direct injection is distributed, and the corresponding fuel injector is controlled to inject fuel.
The S2 specifically includes:
s21: judging whether the cold start is performed, if so, performing S22, otherwise, performing S23;
s22: judging whether the engine is warmed up, if so, performing S23, and otherwise, performing S3;
s23: performing basic oil injection map table lookup;
s24: cold starting or warm-up thickening;
s25: performing oil injection correction according to the boundary parameters of the engine;
s26: and controlling the air inlet channel oil sprayer to spray oil.
The S3 specifically includes:
s31: judging the load condition, namely a small load, performing S3211, performing S3221 when the load is large;
s3211: performing basic oil injection map table lookup;
s3212: performing oil injection correction according to the boundary parameters of the engine;
s3213: controlling the in-cylinder semi-direct-injection oil injector to inject oil;
s3221: performing basic oil injection map table lookup;
s3222: performing oil injection correction according to the boundary parameters of the engine;
s3223: proportionally distributing oil injection of an air inlet channel and semi-direct injection in a cylinder;
s3224: and controlling the air inlet channel and the in-cylinder semi-direct injection injector to inject oil.
The invention discloses an oil injection control method of a two-stroke aviation piston engine, which mainly comprises a data measurement unit, a control unit and an execution unit as shown in figure 1. The data measuring unit is composed of a rotating speed sensor, a temperature sensor and throttle position feedback, and the rotating speed sensor acquires the rotating speed of the engine; the temperature sensor measures the air inlet temperature, the cylinder temperature and the exhaust temperature of the engine; throttle opening signal feedback may be understood as a steering engine capable of providing position feedback, a motor capable of providing position feedback, or a throttle position signal provided by a separate position sensor. The control unit is an electronic control module, which comprises a singlechip, a power circuit, a digital signal processing circuit, an amplifying and filtering circuit and an actuator power driving circuit. The power supply circuit provides stable voltage for the whole system and provides overcurrent and overvoltage protection for the system; the digital signal processing circuit receives the signal from the rotating speed sensor and sends the signal to the singlechip; the amplifying and filtering circuit receives feedback signals from the temperature sensor and the throttle position, and the feedback signals are sent to the single chip microcomputer after being filtered and amplified; the single chip microcomputer judges the operation condition of the engine according to the collected rotating speed, temperature and throttle position signals, calculates the oil injection phase and the oil injection quantity and distributes the ratio of air inlet channel injection to in-cylinder direct injection fuel injection; the actuator power driving circuit receives a control signal from the singlechip to complete the control of the corresponding actuator.
As shown in fig. 2, an exemplary fuel injection system of the present invention is applied to a two-cylinder two-stroke aviation piston engine, but it should be understood that: the control method is also suitable for 4-cylinder, 6-cylinder or even multi-cylinder two-stroke aviation piston engines. The main difference lies in that the number of cylinders is different, and the number of direct injection injectors is correspondingly controlled to be different. The invention relates to a control method for direct injection in a low-pressure cylinder of a two-stroke aviation piston engine. The engine is divided into five working conditions of cold start, warm-up, small load, medium load and large load according to the engine state parameters. Under the working conditions of cold start and warm-up of the engine, the low temperature of the combustion chamber at the moment is not beneficial to direct injection fuel atomization in the cylinder, and the fuel is injected by adopting an air inlet channel to control the fuel injection of the fuel injector 2; under the working conditions of small load and medium load of the engine, the rotating speed of the engine is relatively low, the opening time of a scavenging port is relatively long, the in-cylinder direct injection fuel injection quantity and fuel atomization can meet the requirements, and in order to improve the fuel economy, in-cylinder direct injection is adopted to control the fuel injectors 1 and 3 to inject fuel; under the condition of large-load working of the engine, the rotating speed of the engine is high, the opening time of a scavenging port is short, the fuel injection quantity of direct injection in a cylinder cannot meet the requirement, and the fuel injectors 1, 2 and 3 are controlled to work simultaneously by adopting a combined mode of direct injection in the cylinder and injection of an air inlet channel. The timing chart of the fuel injection control is shown in fig. 3.
Fig. 4 shows a flow chart of the fuel injection control method according to the invention. Step one, judging the working state of an engine according to collected engine state data such as the current rotating speed, the opening degree of a throttle valve, the temperature and the like; secondly, under corresponding working conditions, inquiring the fuel injection quantity according to the rotating speed of the engine and the position of a throttle valve, and correcting the fuel injection quantity according to the state data of the engine; and thirdly, under the corresponding working condition, judging whether a mode of direct injection or air inlet channel injection or a combined mode of direct injection and air inlet channel injection in the cylinder is adopted, distributing the injection proportion of the fuel oil in the air inlet channel and the direct injection, and controlling the corresponding fuel oil injector to inject the fuel oil.
The detailed description is given above to the fuel injection control system and method for the two-stroke aviation piston engine provided by the embodiment of the application. The above description of the embodiments is only for the purpose of helping to understand the method of the present application and its core ideas; meanwhile, for a person skilled in the art, according to the idea of the present application, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present application.
As used in the specification and claims, certain terms are used to refer to particular components. As one skilled in the art will appreciate, manufacturers may refer to a component by different names. This specification and claims do not intend to distinguish between components that differ in name but not function. In the following description and in the claims, the terms "include" and "comprise" are used in an open-ended fashion, and thus should be interpreted to mean "include, but not limited to. "substantially" means within an acceptable error range, and a person skilled in the art can solve the technical problem within a certain error range to substantially achieve the technical effect. The description which follows is a preferred embodiment of the present application, but is made for the purpose of illustrating the general principles of the application and not for the purpose of limiting the scope of the application. The protection scope of the present application shall be subject to the definitions of the appended claims.
It is also noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a good or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such good or system. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a commodity or system that includes the element.
It should be understood that the term "and/or" as used herein is merely one type of association that describes an associated object, meaning that three relationships may exist, e.g., a and/or B may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.
The foregoing description shows and describes several preferred embodiments of the present application, but as aforementioned, it is to be understood that the application is not limited to the forms disclosed herein, but is not to be construed as excluding other embodiments and is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the application as described herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the application, which is to be protected by the claims appended hereto.
Claims (10)
1. A fuel injection control system for a two-stroke aviation piston engine, the system being applied to a two-stroke aviation piston engine, the system comprising:
the data measuring unit is used for acquiring data of the rotating speed, the opening of a throttle valve, the temperature of an air cylinder and the exhaust temperature of the engine;
the control unit judges the working state of the engine according to the acquired rotating speed data of the engine, calculates the fuel injection quantity and distributes the fuel injection proportion of the corresponding air inlet channel and the in-cylinder direct injection;
the execution unit is used for starting the oil injection driving circuit to finish the oil injection process of the engine;
the data measurement unit is connected with the execution unit through the control unit.
2. The system of claim 1, wherein the data measurement unit comprises a rotational speed sensor, a temperature sensor, and a throttle opening signal feedback;
the rotating speed sensor is used for acquiring the rotating speed of the engine;
the temperature sensor is used for measuring the air inlet temperature, the cylinder temperature and the exhaust temperature of the engine;
the throttle opening signal feedback device is a steering engine capable of providing position feedback, a motor capable of providing position feedback or an independent position sensor capable of providing a throttle position signal.
3. The system according to claim 2, wherein the control unit comprises a single chip microcomputer, a digital signal processing circuit and an amplifying and filtering circuit, one end of the digital signal processing circuit is connected with the rotation speed sensor, the other end of the digital signal processing circuit is connected with the single chip microcomputer, one end of the amplifying and filtering circuit is simultaneously connected with the temperature sensor and the throttle opening degree signal feedback device, and the other end of the amplifying and filtering circuit is connected with the single chip microcomputer.
4. The system of claim 3, wherein the control unit further comprises a power supply circuit and an actuator power drive circuit; the power circuit is connected with the single chip microcomputer, one end of the actuator power driving circuit is connected with the single chip microcomputer, and the other end of the actuator power driving circuit is connected with the execution unit.
5. The system of claim 4, wherein the power circuit provides a regulated voltage to the entire system and overcurrent and overvoltage protection to the system, and the actuator power driving circuit receives a control signal from the single-chip microcomputer to control the corresponding actuator.
6. The system of claim 5, wherein the single chip microcomputer determines engine operating conditions from the collected speed, temperature and throttle position signals, calculates fuel injection phase and quantity, and distributes port injection and direct in-cylinder injection fuel injection ratios.
7. The system of claim 5, wherein the execution units include an oil pump, an oil injector, and an igniter.
8. A method for controlling a fuel injection control system for a two-stroke aviation piston engine, comprising a system according to any one of claims 1 to 7, characterized in that it comprises the steps of:
s1: collecting data of the rotating speed of the engine, the opening of a throttle valve, the temperature of an air cylinder and the exhaust temperature, and judging the working state of the engine;
s2: under corresponding working conditions, inquiring the fuel injection quantity according to the rotating speed of the engine and the position of a throttle valve, and correcting the fuel injection quantity according to the state data of the engine;
s3: under the corresponding working condition, the combination mode of direct injection in the cylinder or air inlet channel injection or direct injection in the cylinder and air inlet channel injection is judged, the ratio of the fuel injection in the air inlet channel and the fuel injection in the direct injection is distributed, and the corresponding fuel injector is controlled to inject fuel.
9. The control method according to claim 8, wherein the S2 specifically includes:
s21: judging whether the cold start is performed, if so, performing S22, otherwise, performing S23;
s22: judging whether the engine is warmed up, if so, performing S23, and otherwise, performing S3;
s23: performing basic oil injection map table lookup;
s24: cold starting or warm-up thickening;
s25: performing oil injection correction according to the boundary parameters of the engine;
s26: and controlling the air inlet channel oil sprayer to spray oil.
10. The control method according to claim 9, wherein the S3 specifically includes:
s31: judging the load condition, namely a small load, performing S3211, performing S3221 when the load is large;
s3211: performing basic oil injection map table lookup;
s3212: performing oil injection correction according to the boundary parameters of the engine;
s3213: controlling the in-cylinder semi-direct-injection oil injector to inject oil;
s3221: performing basic oil injection map table lookup;
s3222: performing oil injection correction according to the boundary parameters of the engine;
s3223: proportionally distributing oil injection of an air inlet channel and semi-direct injection in a cylinder;
s3224: and controlling the air inlet channel and the in-cylinder semi-direct injection injector to inject oil.
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| CN114992023A (en) * | 2022-06-09 | 2022-09-02 | 北京航空航天大学 | Aero-engine fuel injection control method adaptive to carbon-negative biofuel |
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| CN206917746U (en) * | 2017-06-23 | 2018-01-23 | 山东中宇航空科技发展有限公司 | A kind of aviation two-stroke kerosene engine injector controller |
| CN108468587A (en) * | 2018-05-29 | 2018-08-31 | 重庆隆鑫发动机有限公司 | The Heavy End Aviation Fuel engine and aircraft of composite injection |
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