CN113464271A - Closed-loop control method and system for pressure of supercharger for aviation two-stroke piston engine - Google Patents
Closed-loop control method and system for pressure of supercharger for aviation two-stroke piston engine Download PDFInfo
- Publication number
- CN113464271A CN113464271A CN202110887801.4A CN202110887801A CN113464271A CN 113464271 A CN113464271 A CN 113464271A CN 202110887801 A CN202110887801 A CN 202110887801A CN 113464271 A CN113464271 A CN 113464271A
- Authority
- CN
- China
- Prior art keywords
- supercharger
- engine
- supercharging
- inlet pressure
- pressure value
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 38
- 238000013528 artificial neural network Methods 0.000 claims abstract description 21
- 238000002347 injection Methods 0.000 claims abstract description 10
- 239000007924 injection Substances 0.000 claims abstract description 10
- 238000011156 evaluation Methods 0.000 claims description 13
- 239000000446 fuel Substances 0.000 claims description 10
- 230000007246 mechanism Effects 0.000 claims description 10
- 238000012545 processing Methods 0.000 claims description 6
- 238000004364 calculation method Methods 0.000 claims description 4
- 238000004458 analytical method Methods 0.000 claims description 3
- 230000004044 response Effects 0.000 abstract description 7
- 230000001052 transient effect Effects 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 230000008569 process Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 239000002912 waste gas Substances 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 230000004043 responsiveness Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000012549 training Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/12—Control of the pumps
- F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/12—Control of the pumps
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/27—Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Combustion & Propulsion (AREA)
- Evolutionary Computation (AREA)
- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Medical Informatics (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- Software Systems (AREA)
- Computer Vision & Pattern Recognition (AREA)
- Artificial Intelligence (AREA)
- Supercharger (AREA)
Abstract
The invention relates to a closed-loop control method and a closed-loop control system for pressure booster pressure of an aviation two-stroke piston engine, which are suitable for dynamic control of a pressurization system of the aviation piston engine. The method comprises the steps of obtaining target supercharging inlet pressure through the rotating speed and the torque of an engine, inputting the supercharging inlet pressure, state parameters of the engine and oil injection quantity into a BPNN-based MPC controller, controlling the position of a nozzle ring of a supercharger to adjust the supercharging inlet pressure of the engine, feeding the supercharging inlet pressure back to the BPNN-based MPC controller, comparing and judging the supercharging inlet pressure and the target supercharging inlet pressure by the controller, and continuously correcting model parameters to achieve the purpose of closed-loop accurate control. The closed-loop control and regulation method for the pressure of the supercharger is beneficial to improving the transient response performance of the supercharger, and the dynamic property and the economical efficiency of an engine. And the operation load of the controller is reduced by adopting the prediction model control based on the back propagation neural network.
Description
Technical Field
The invention relates to a booster pressure closed-loop control method and a booster pressure closed-loop control system for an aviation two-stroke piston engine, which can meet the requirements of high lift limit, short take-off at different altitudes and long endurance of an aircraft.
Background
The landform of China is complex, the total area of a plateau area is the first place in the world, the power attenuation of a natural suction engine at high altitude is serious, and the high altitude dynamic performance is poor. The method aims to solve the problems of insufficient high altitude power performance and poor fuel economy of the aviation piston engine. Therefore, a supercharging technology is needed to improve the air intake quantity of the engine and compensate the power attenuation of the engine caused by the rise of the working altitude. The turbocharging technology provided by the invention is a variable geometric section turbocharging technology (hereinafter referred to as 'VGT'), and the technology meets the dynamic requirements of an engine under different altitude flight conditions by a closed-loop control and adjustment method of the pressure of a supercharger.
In the matching process of the turbocharger, the engine has matching contradiction between a high-speed and high-load working condition and a low-speed and low-load working condition due to the characteristics of the turbocharger. In order to decouple the contradiction, the traditional waste gas bypass technology is generally adopted to solve the problem of overhigh supercharging pressure under the working conditions of high speed and high load. However, a large amount of exhaust gas is bypassed in the exhaust gas bypass process, so that the energy of the exhaust gas cannot be fully utilized.
Disclosure of Invention
The invention discloses a closed-loop control method and a closed-loop control system for pressure of a supercharger for an aviation two-stroke piston engine, which aim to solve any one of the technical problems and other potential problems in the prior art.
In order to solve the technical problems, the technical scheme of the invention is as follows: a closed-loop control method for pressure of a supercharger for an aviation two-stroke piston engine specifically comprises the following steps:
s1) obtaining a target supercharging inlet pressure value of the supercharger according to the engine speed and the engine load torque parameter;
s2) the acquisition unit acquires the working parameter data of the engine in real time and sends the working parameter data to the control unit;
s3) the control unit receives the working parameter data, the model predictive control algorithm based on the back propagation neural network is adopted for analysis and calculation to obtain the supercharging inlet pressure value of the real-time supercharger, the supercharging inlet pressure value of the real-time supercharger is compared with the target supercharging inlet pressure value obtained by S1), the optimal value of the target opening degree of the nozzle ring blade of the supercharger is determined according to the comparison result, and the signal is transmitted to the execution unit;
s4) the execution unit adjusts the position of the nozzle ring vane to a target position according to the instruction, and accurate closed-loop control of the opening of the nozzle ring vane of the supercharger is achieved.
Further, the operating parameter data of the engine in S2) includes: engine boost intake pressure, boost intake temperature, exhaust temperature, throttle position, engine speed, and fuel injection quantity.
Further, the specific steps of S3) are:
s3.1) taking the engine speed, the target supercharging inlet pressure, the supercharging inlet temperature, the exhaust temperature, the throttle position and other parameters as the input of a prediction model based on a back propagation neural network, outputting the supercharging inlet pressure value of the real-time supercharger,
s3.2) taking the square difference between the supercharging inlet pressure value of the real-time supercharger and the target supercharging inlet pressure value as an evaluation function, returning to S3.1 when the evaluation function is greater than a threshold value, and taking the evaluation function as the optimal value of the supercharging inlet pressure value when the evaluation function is equal to or less than the threshold value,
and optimizing the target position of the nozzle ring blade of the supercharger according to the optimal value of the air inlet pressure value to obtain the optimal position of the nozzle ring blade of the supercharger in the prediction period.
Further, the threshold is that the difference between the supercharging inlet pressure value of the real-time supercharger and the target supercharging inlet pressure value is less than or equal to 5%.
Another object of the present invention is to provide a control system for implementing the above method, the system comprising: the system comprises a data acquisition unit, a control unit and an execution unit;
the data acquisition unit is used for acquiring the data of the supercharged intake pressure, the supercharged intake temperature, the exhaust temperature, the throttle position and the engine speed of the engine in real time;
the control unit is used for predicting the real-time data by using a model based on a back propagation neural network, evaluating the output result and the target intake pressure value, determining the optimal value of the supercharging intake pressure value and sending the optimal value to the execution unit,
and the execution unit is used for converting the optimal value of the supercharging inlet pressure value into a control instruction, adjusting the opening of the nozzle ring blades of the supercharger and realizing the accurate closed-loop control of the opening of the nozzle ring blades of the supercharger.
Further, the data acquisition unit includes: a boost intake pressure sensor, a boost intake temperature sensor, an exhaust temperature sensor, a throttle position sensor, and an engine speed sensor.
Further, the control unit includes: an electric control unit, a pressure boost controller and a data processing module,
the data processing module is used for processing data, determining an optimal value of a supercharging intake pressure value, sending the optimal value of the supercharging intake pressure value to the supercharging system controller, and the supercharging system controller outputs a control signal and sends the control signal to the electric control unit.
Further, the execution unit comprises a supercharger and an execution mechanism;
the actuating mechanism is used for receiving a control signal of the electric control unit and adjusting the opening of nozzle ring blades of the supercharger.
Compared with the prior art, the invention has the following advantages:
(1) the invention discloses a closed-loop control and adjustment method for pressure of a supercharger for an aviation two-stroke piston engine.
(2) The closed-loop control and regulation method for the pressure of the supercharger is beneficial to improving the transient response performance of the supercharger, and the dynamic property and the economical efficiency of an engine.
(3) And the operation load of the controller is reduced by adopting the prediction Model (MPC) control based on the Back Propagation Neural Network (BPNN).
Drawings
FIG. 1 is a block diagram of the closed loop control process for the pressure of the supercharger of an aviation two-stroke piston engine.
FIG. 2 is a control logic diagram of a Back Propagation Neural Network (BPNN) based predictive Model (MPC) in accordance with the present invention.
FIG. 3 is a schematic diagram of a closed-loop control system for supercharger pressure for an aviation two-stroke piston engine according to the present invention.
Detailed Description
The technical solution of the present invention is further explained with reference to the accompanying drawings and specific embodiments.
The invention relates to a booster pressure control device for an aviation two-stroke piston engine and a booster pressure closed-loop control and adjustment method. The invention can improve the waste gas utilization efficiency of the turbocharger and the dynamic responsiveness of the turbocharger, so that the engine can meet the performance requirements under different working states.
And the VGT can effectively avoid the problems. The turbine efficiency is improved by reducing the geometric flow cross section area of the turbine under the low working condition and the low load, so that the dynamic property of the engine under the low-speed and low-load working condition is improved; the turbine flow capacity is improved by increasing the geometric flow cross section area of the turbine under the high-speed high-load working condition, and the supercharging pressure under the high-speed high-load working condition is improved. The VGT adopts a pressure closed-loop control matching method, so that the requirements of high and low working conditions on dynamic property and economy can be considered, the waste gas energy can be more fully utilized, the flow section and the airflow direction of the nozzle ring blade can be adjusted in time, and the transient response of the supercharger is improved. The invention provides a variable nozzle ring type turbine variable geometric cross section control device and a turbocharging pressure closed-loop control method.
As shown in figure 1, the closed-loop control block diagram of the pressure booster of the aviation two-stroke piston engine obtains target supercharging intake pressure through the rotating speed and the torque of the engine, inputs the supercharging intake pressure, state parameters of the engine and fuel injection quantity into the MPC controller based on BPNN, controls the position of a nozzle ring of the pressure booster to adjust the supercharging intake pressure of the engine, feeds the supercharging intake pressure back to the MPC controller based on BPNN, and the controller compares and judges the supercharging intake pressure with the target supercharging intake pressure and continuously corrects model parameters to achieve the purpose of accurately controlling the closed loop.
The invention discloses a closed-loop control method for pressure of a supercharger for an aviation two-stroke piston engine, which specifically comprises the following steps of:
s1) obtaining a target intake pressure value of the supercharger according to the engine speed and the engine load torque parameter;
s2) the acquisition unit acquires the working parameter data of the engine in real time and sends the working parameter data to the control unit;
s3) the control unit receives the working parameter data, the model predictive control algorithm based on the back propagation neural network is adopted for analysis and calculation to obtain the air inlet pressure value of the real-time supercharger, the air inlet pressure value of the real-time supercharger is compared with the target air inlet pressure value obtained by S1), the optimal value of the target opening degree of the nozzle ring blade of the supercharger is determined according to the comparison result, and the signal is transmitted to the execution unit;
s4) the execution unit adjusts the position of the nozzle ring vane to a target position according to the instruction, and accurate closed-loop control of the opening of the nozzle ring vane of the supercharger is achieved.
Further, the operating parameter data of the engine in S2) includes: engine boost intake pressure, boost intake temperature, exhaust temperature, throttle position, engine speed, and fuel injection quantity.
As shown in FIG. 2, the present invention is based on a Back Propagation Neural Network (BPNN) predictive model control (MPC) logic diagram. The closed-loop control and regulation method for the pressure of the supercharger determines and solves a target supercharging inlet pressure according to the rotating speed and the torque of an engine, a BPNN controller is adopted to identify the state of the supercharged engine, the result after neural network training is sent to an actuator to control the position of a nozzle ring, parameters for correcting the position of a nozzle ring blade of the supercharger are obtained by using an MPC based on the BPNN after a delay function, and the result is fed back to the neural network controller to achieve the purpose of controlling the position of the nozzle ring of the supercharger and further achieve the purpose of controlling the supercharging inlet pressure. At the moment, the ECU regulates and controls the oil injection pulse width of the engine by detecting the air intake state of the engine, and corrects the oil injection pulse width according to the air intake temperature to finally achieve the cooperative and accurate control.
The S3) comprises the following specific steps:
s3.1) taking the engine speed, the target supercharging inlet pressure, the supercharging inlet temperature, the exhaust temperature, the throttle position and other parameters as the input of a prediction model based on a back propagation neural network, outputting the supercharging inlet pressure value of the real-time supercharger,
s3.2) taking the square difference between the supercharging inlet pressure value of the real-time supercharger and the target supercharging inlet pressure value as an evaluation function, returning to S3.1 when the evaluation function is greater than a threshold value, and taking the evaluation function as the optimal value of the inlet pressure value when the evaluation function is equal to or less than the threshold value,
and optimizing the target position of the nozzle ring blade of the supercharger according to the optimal value of the supercharging inlet pressure value to obtain the optimal position of the nozzle ring blade of the supercharger in the prediction period.
Further, the threshold is that the difference between the supercharging inlet pressure value of the real-time supercharger and the target supercharging inlet pressure value is less than or equal to 5%.
As shown in fig. 3, the pressure control device of the supercharger for the aviation two-stroke piston engine mainly comprises three parts, namely a data acquisition unit, a control unit and an execution unit. The data acquisition unit comprises an air inlet pressure sensor, an air inlet temperature sensor, an exhaust temperature sensor, a throttle position sensor, an engine speed sensor, a throttle position sensor, an oil injection quantity and other parameter acquisition sensors; the control system comprises an electric control unit (hereinafter referred to as 'ECU'), a supercharging system controller (hereinafter referred to as 'TCU') supercharger and a control algorithm; the execution unit comprises a supercharger and a VGT execution mechanism. In the working process of the device, engine parameter signals such as engine supercharging air inlet pressure, supercharging air inlet temperature, exhaust temperature, throttle position, engine rotating speed and the like are acquired through the data acquisition unit and are transmitted to the control unit. And an ECU in the control unit receives an engine parameter signal, calculates a target opening degree of the nozzle ring blades of the VGT through a control algorithm, and transmits the signal to the TCU. The TCU receives a target opening signal of the nozzle ring blade of the VGT and outputs an actuating mechanism control signal according to an actuating mechanism control algorithm. And the execution unit receives a control signal output by the TCU in the control unit, and realizes accurate closed-loop control of the opening of the nozzle ring blades of the VGT. The device adjusts VGT nozzle ring blade aperture according to the change of height above sea level and engine operating mode, realizes guaranteeing closed-loop control, realizes that the engine fuel consumption and the power are optimal under the different operating modes of different height above sea levels, and the high-efficient matching operation of turbocharging system and engine.
The invention discloses a closed-loop control and regulation method for the pressure of a supercharger for an aviation two-stroke piston engine, which adopts a pressure closed-loop control algorithm controlled by a prediction model (hereinafter referred to as MPC) based on a back propagation neural network (hereinafter referred to as BPNN) to control the position of a nozzle ring blade. Wherein the boost pressure closed-loop control algorithm is implemented in the boost pressure control device control unit. During the working process of the engine, the target supercharging inlet pressure of the engine is mainly determined by the engine rotating speed, the altitude and the engine fuel injection quantity, wherein the engine fuel injection quantity is related to the engine load torque. Thus, the engine target boost intake pressure may be determined from the engine speed and the engine torque.
According to the control method, the target supercharging pressure MAP of the supercharger is searched according to the engine speed and the engine load torque parameter, and the target control pressure of the supercharger in the current engine state is obtained. The method is characterized in that parameters such as the engine speed, the supercharged intake pressure, the supercharged intake temperature, the exhaust temperature and the throttle position are input as a model prediction control algorithm based on a back propagation neural network, and a target control position of a nozzle ring blade of a supercharger is output. In the algorithm, the engine gas path model constructed based on the back propagation neural network is input by using state parameters such as the engine rotating speed, the supercharging inlet air pressure, the supercharging inlet air temperature, the exhaust temperature, the throttle position and the like, and the target control position of the nozzle ring blade of the supercharger is output to predict the supercharging inlet air pressure of the engine. The target position of the nozzle ring blade of the supercharger is optimized and adjusted by taking the target supercharging inlet air pressure and the supercharging inlet air pressure square difference predicted by the model as an evaluation function to obtain the optimal position of the nozzle ring blade of the supercharger in a prediction period, and the algorithm can quickly and accurately track the target supercharging inlet air pressure and control the precision within 5 percent.
Obtaining an expression of a prediction model at the k moment according to the characteristics of the turbocharged engine and an MPC control theory:
Pim(k+i|k)＝Wi(X(k+i|k)),(i＝1,2,...N)
in the formula, mfTo quantity of injected fuel, θthIs throttle opening, NeIs the engine speed, PimW is the boost intake pressure, W is the weight.
The control increments can be expressed as:
ΔU(k)＝[Δu(k|k),Δu(k+1|k),…Δu(k+m-1|k)]
Δu(k+i|k)＝u(k+i|k)-u(k+i-1|k)(i＝0,1,…m-1)
in the formula, m is the number of steps, U is an input variable, and U is a single input variable.
The control inputs may be expressed as:
a model predictive control algorithm based on a back propagation neural network is implemented in an ECU in a control unit, and then the ECU outputs a target control position signal of the nozzle ring blade of the supercharger to a TCU. A supercharger control unit (TCU) controls an actuator to adjust the position of the nozzle ring vanes to a target position. According to the closed-loop control and regulation method for the pressure of the supercharger, a target supercharging inlet pressure is determined according to the requirements on the rotating speed and the torque of an engine, and then the position of a nozzle ring vane of the supercharger of the supercharged engine is controlled by using a model prediction algorithm based on BPNN (binary-harmonic neural network) so as to achieve the cooperative accurate control of controlling the supercharging inlet pressure. In addition, the throttle area is adjusted, meanwhile, the airflow direction is directly and quickly adjusted, the transient response performance of the supercharger is more favorably improved, the dynamic performance and the economical efficiency of the engine are obviously improved after the pressure closed-loop control is adopted, and particularly the low-speed dynamic performance and the dynamic response performance of the engine are improved.
The control system comprises an electric control unit (hereinafter referred to as 'ECU'), a supercharging controller (hereinafter referred to as 'TCU') supercharger and a control algorithm, and has the function of calculating and outputting control signals of an execution unit according to engine parameters;
the execution unit comprises a supercharger and a VGT execution mechanism, and the target opening degree of the nozzle ring blades of the supercharger is adjusted.
In the working process of the device, engine parameter signals such as engine supercharging air inlet pressure, supercharging air inlet temperature, exhaust temperature, throttle position, engine rotating speed and the like are acquired through the data acquisition unit and are transmitted to the control unit. And an ECU in the control unit receives an engine parameter signal, calculates a target opening degree of the nozzle ring blades of the VGT through a control algorithm, and transmits the signal to the TCU. The TCU receives a target opening signal of the nozzle ring blade of the VGT and outputs an actuating mechanism control signal according to an actuating mechanism control algorithm. And the execution unit receives a control signal output by the TCU in the control unit, and realizes accurate closed-loop control of the opening of the nozzle ring blades of the VGT. The device adjusts VGT nozzle ring blade aperture according to the change of height above sea level and engine operating mode, realizes guaranteeing closed-loop control, realizes that the engine fuel consumption and the power are optimal under the different operating modes of different height above sea levels, and the high-efficient matching operation of turbocharging system and engine.
The invention discloses a closed-loop control and regulation method for pressure of a supercharger for an aviation two-stroke piston engine, which adopts a pressure closed-loop control algorithm controlled by a prediction model (hereinafter referred to as MPC) based on a back propagation neural network (hereinafter referred to as BPNN) to control the position of a nozzle ring blade of the supercharger.
According to the control method, the target supercharging inlet pressure of the supercharger is obtained through calculation according to state parameters such as the rotating speed of the engine, the torque demand and the like. And obtaining the target control position of the nozzle ring blade of the supercharger by a prediction model algorithm based on a reverse neural network according to the parameters of the engine speed, the actual supercharging inlet pressure, the target supercharging inlet pressure and the like.
And a supercharger system controller (TCU) controls an actuating mechanism according to the target position of the nozzle ring blade, and accurately adjusts the position of the nozzle ring blade to the target position.
According to the closed-loop control adjusting method for the supercharger pressure, a target supercharging inlet pressure is determined according to the requirements on the rotating speed and the torque of an engine, and then a model prediction algorithm based on BPNN is used for achieving the purpose of achieving the coordinated accurate control of the position of a nozzle ring blade of the supercharged engine. In addition, the throttle area is adjusted, meanwhile, the airflow direction is directly and quickly adjusted, the transient response performance of the supercharger is more favorably improved, the dynamic performance and the economical efficiency of the engine are obviously improved after the pressure closed-loop control is adopted, and particularly the low-speed dynamic performance and the dynamic response performance of the engine are improved.
The method and the system for closed-loop control of the pressure of the supercharger for the aviation two-stroke piston engine provided by the embodiment of the application are described in detail. 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 (8)
1. A closed-loop control method for pressure of a supercharger for an aviation two-stroke piston engine is characterized by comprising the following steps:
s1) obtaining a target supercharging inlet pressure value of the supercharger according to the engine speed and the engine load torque parameter;
s2) the acquisition unit acquires the working parameter data of the engine in real time and sends the working parameter data to the control unit;
s3) the control unit receives the working parameter data, the model predictive control algorithm based on the back propagation neural network is adopted for analysis and calculation to obtain the supercharging inlet pressure value of the real-time supercharger, the supercharging inlet pressure value of the real-time supercharger is compared with the target supercharging inlet pressure value obtained by S1), the optimal value of the target opening degree of the nozzle ring blade of the supercharger is determined according to the comparison result, and the signal is transmitted to the execution unit;
s4) the execution unit adjusts the position of the nozzle ring vane to a target position according to the instruction, and accurate closed-loop control of the opening of the nozzle ring vane of the supercharger is achieved.
2. The method as claimed in claim 1, wherein the operating parameter data of the engine in S2) includes: engine boost intake pressure, boost intake temperature, exhaust temperature, throttle position, engine speed, and fuel injection quantity.
3. The method as claimed in claim 1, wherein the specific steps of S3) are:
s3.1) taking the engine speed, the target supercharging inlet pressure, the supercharging inlet temperature, the exhaust temperature, the throttle position and other parameters as the input of a prediction model based on a back propagation neural network, outputting the supercharging inlet pressure value of the real-time supercharger,
s3.2) taking the square difference between the supercharging inlet pressure value of the real-time supercharger and the target supercharging inlet pressure value as an evaluation function, returning to S3.1 when the evaluation function is greater than a threshold value, and taking the evaluation function as the optimal value of the supercharging inlet pressure value when the evaluation function is equal to or less than the threshold value,
and optimizing the target position of the nozzle ring blade of the supercharger according to the optimal value of the supercharging inlet pressure value to obtain the optimal position of the nozzle ring blade of the supercharger in the prediction period.
4. The method of claim 3, wherein the threshold is less than or equal to 5% of a difference between a boost intake pressure value of the real-time supercharger and a target boost intake pressure value.
5. A control system for implementing the method according to any one of claims 1 to 4, characterized in that the system comprises: the system comprises a data acquisition unit, a control unit and an execution unit;
the data acquisition unit is used for acquiring the data of the supercharged intake pressure, the supercharged intake temperature, the exhaust temperature, the throttle position and the engine speed of the engine in real time;
the control unit is used for predicting the real-time data by using a model based on a back propagation neural network, evaluating the output result and the target supercharging inlet pressure value, determining the optimal value of the supercharging inlet pressure value and sending the optimal value to the execution unit,
and the execution unit is used for converting the optimal value of the supercharging inlet pressure value into a control instruction, adjusting the opening of the nozzle ring blades of the supercharger and realizing the accurate closed-loop control of the opening of the nozzle ring blades of the supercharger.
6. The system of claim 5, wherein the data acquisition unit comprises: an intake pressure sensor, an intake temperature sensor, an exhaust temperature sensor, a throttle position sensor, and an engine speed sensor.
7. The system of claim 5, wherein the control unit comprises: a pressure increasing controller and a data processing module,
the data processing module is used for processing data, determining an optimal value of a supercharging intake pressure value, sending the optimal value of the supercharging intake pressure value to the supercharging system controller, and the supercharging system controller outputs a control signal and sends the control signal to the electric control unit.
8. The system of claim 7, wherein the actuator unit comprises a supercharger and an actuator;
the actuating mechanism is used for receiving a control signal of the electric control unit and adjusting the opening of nozzle ring blades of the supercharger.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110887801.4A CN113464271B (en) | 2021-08-03 | 2021-08-03 | Booster pressure closed-loop control method and system for aviation two-stroke piston engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110887801.4A CN113464271B (en) | 2021-08-03 | 2021-08-03 | Booster pressure closed-loop control method and system for aviation two-stroke piston engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113464271A true CN113464271A (en) | 2021-10-01 |
| CN113464271B CN113464271B (en) | 2023-01-06 |
Family
ID=77883927
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110887801.4A Active CN113464271B (en) | 2021-08-03 | 2021-08-03 | Booster pressure closed-loop control method and system for aviation two-stroke piston engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113464271B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114810337A (en) * | 2022-04-12 | 2022-07-29 | 潍柴动力股份有限公司 | Control method and related device of supercharger |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101328831A (en) * | 2008-08-04 | 2008-12-24 | 清华大学 | Diesel altitude-variable self-adapting supercharging control method and system |
| CN201953488U (en) * | 2011-01-27 | 2011-08-31 | 潍柴动力股份有限公司 | Device for controlling air system of diesel engine, and diesel engine |
| US20140196704A1 (en) * | 2011-04-22 | 2014-07-17 | Borgwarner Inc. | Turbocharger boost control using exhaust pressure estimated from engine cylinder pressure |
| CN104234821A (en) * | 2014-09-18 | 2014-12-24 | 北京航空航天大学 | Aviation supercharger control system and adjusting method thereof |
| CN109611193A (en) * | 2018-10-23 | 2019-04-12 | 航天时代飞鸿技术有限公司 | A kind of small-sized aviation piston two-stroke turbocharged engine control method |
| CN110529275A (en) * | 2018-05-23 | 2019-12-03 | 中国人民解放军陆军军事交通学院 | The double VGT second level adjustable pressurization systems of diesel engine and oil common rail system become height above sea level cooperative control method |
| CN111911307A (en) * | 2020-06-24 | 2020-11-10 | 中国人民解放军陆军军事交通学院 | Two-stage adjustable supercharging system of variable altitude diesel engine, oil injection system and cooling system optimal matching method |
| CN111963327A (en) * | 2020-07-06 | 2020-11-20 | 中国人民解放军陆军军事交通学院 | Altitude-variable boost pressure self-adaptive adjustment control method for two-stage adjustable supercharged diesel engine |
| CN112664282A (en) * | 2019-10-15 | 2021-04-16 | 上汽通用汽车有限公司 | Control method for variable turbocharger |
-
2021
- 2021-08-03 CN CN202110887801.4A patent/CN113464271B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101328831A (en) * | 2008-08-04 | 2008-12-24 | 清华大学 | Diesel altitude-variable self-adapting supercharging control method and system |
| CN201953488U (en) * | 2011-01-27 | 2011-08-31 | 潍柴动力股份有限公司 | Device for controlling air system of diesel engine, and diesel engine |
| US20140196704A1 (en) * | 2011-04-22 | 2014-07-17 | Borgwarner Inc. | Turbocharger boost control using exhaust pressure estimated from engine cylinder pressure |
| CN104234821A (en) * | 2014-09-18 | 2014-12-24 | 北京航空航天大学 | Aviation supercharger control system and adjusting method thereof |
| CN110529275A (en) * | 2018-05-23 | 2019-12-03 | 中国人民解放军陆军军事交通学院 | The double VGT second level adjustable pressurization systems of diesel engine and oil common rail system become height above sea level cooperative control method |
| CN109611193A (en) * | 2018-10-23 | 2019-04-12 | 航天时代飞鸿技术有限公司 | A kind of small-sized aviation piston two-stroke turbocharged engine control method |
| CN112664282A (en) * | 2019-10-15 | 2021-04-16 | 上汽通用汽车有限公司 | Control method for variable turbocharger |
| CN111911307A (en) * | 2020-06-24 | 2020-11-10 | 中国人民解放军陆军军事交通学院 | Two-stage adjustable supercharging system of variable altitude diesel engine, oil injection system and cooling system optimal matching method |
| CN111963327A (en) * | 2020-07-06 | 2020-11-20 | 中国人民解放军陆军军事交通学院 | Altitude-variable boost pressure self-adaptive adjustment control method for two-stage adjustable supercharged diesel engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114810337A (en) * | 2022-04-12 | 2022-07-29 | 潍柴动力股份有限公司 | Control method and related device of supercharger |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113464271B (en) | 2023-01-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8447500B2 (en) | Control method of internal combustion engine | |
| EP0965740B1 (en) | Turbocharger control system for turbocharged internal combustion engines equipped with exhaust gas recirculation control system | |
| EP3103991B1 (en) | Control apparatus for internal combustion engine | |
| JP4306703B2 (en) | Control device for an internal combustion engine with a supercharger | |
| US7047740B2 (en) | Boost pressure estimation apparatus for internal combustion engine with supercharger | |
| EP0189121B1 (en) | Method and apparatus for controlling supercharge pressure for a turbocharger | |
| US9803612B2 (en) | Control device for internal combustion engine | |
| US9057320B2 (en) | Control device and control method for an internal combustion engine | |
| US9695771B2 (en) | Spark and valve control for different air/fuel ratios | |
| CN103233825B (en) | The controlling method of secondary adjustable supercharging control system | |
| WO2011074475A1 (en) | Internal combustion engine control device | |
| CN105673191A (en) | Diesel engine variable-altitude boost pressure control method | |
| CN109469567B (en) | EGR valve and throttle valve coupling control method | |
| CN110529275B (en) | Variable altitude cooperative control method for double VGT (variable gas turbine) two-stage adjustable supercharging system and fuel common rail system of diesel engine | |
| US20110036332A1 (en) | Supercharger control device for internal combustion engine | |
| CN203257533U (en) | Two-stage adjustable pressurizing control system | |
| CN113464271B (en) | Booster pressure closed-loop control method and system for aviation two-stroke piston engine | |
| CN111608790B (en) | Gas circuit optimization control system of electric auxiliary turbocharged diesel engine | |
| CN113982745B (en) | Composite supercharging system suitable for aviation piston supercharged engine and control method | |
| JP4378701B2 (en) | Control device for an internal combustion engine with a supercharger | |
| EP1302644B1 (en) | Method for controlling an exhaust-gas turbocharger with a variable turbine geometry | |
| CN106150714B (en) | Control device and control method for internal combustion engine | |
| JP3956458B2 (en) | Fuel injection control device for internal combustion engine | |
| US10519881B2 (en) | Compressor pressure ratio control | |
| EP2354501B1 (en) | Control apparatus for internal combustion engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240626 Address after: No. 58 Xindong Road, Huaqiao Town, Kunshan City, Suzhou City, Jiangsu Province, 215332 Patentee after: Feihong (Kunshan) Energy Power Technology Co.,Ltd. Country or region after: China Address before: Room 149, building 2, East Ring Road, Yanqing Park, Zhongguancun, Yanqing District, Beijing 102100 Patentee before: AEROSPACE TIMES FEIHONG TECHNOLOGY Co.,Ltd. Country or region before: China |