CN109667673A - The control method and device of miniature turbo-jet engine - Google Patents
The control method and device of miniature turbo-jet engine Download PDFInfo
- Publication number
- CN109667673A CN109667673A CN201811518646.3A CN201811518646A CN109667673A CN 109667673 A CN109667673 A CN 109667673A CN 201811518646 A CN201811518646 A CN 201811518646A CN 109667673 A CN109667673 A CN 109667673A
- Authority
- CN
- China
- Prior art keywords
- engine
- control
- module
- communication module
- control unit
- 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 25
- 238000004891 communication Methods 0.000 claims abstract description 44
- 238000012360 testing method Methods 0.000 claims abstract description 32
- 239000000446 fuel Substances 0.000 claims abstract description 21
- 238000004886 process control Methods 0.000 claims abstract description 3
- 238000011217 control strategy Methods 0.000 claims description 17
- 241001276404 Arius Species 0.000 claims description 5
- 238000013461 design Methods 0.000 claims description 5
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 239000000523 sample Substances 0.000 claims description 4
- 238000004088 simulation Methods 0.000 claims description 3
- 239000000295 fuel oil Substances 0.000 claims 2
- 239000007788 liquid Substances 0.000 abstract description 4
- 238000012544 monitoring process Methods 0.000 abstract description 4
- 238000012827 research and development Methods 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000011161 development Methods 0.000 description 2
- 230000010365 information processing Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 108091092878 Microsatellite Proteins 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000004807 localization Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000000153 supplemental effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a kind of control method and device of miniature turbo-jet engine, are related to turbojet engine control field.The invention is mainly to realize the whole process control of the turbojet engine of neat liquid fuel, completes the automatic starting of engine, the monitoring of operating status.The present invention is mainly by engine control unit (ECU), engine bench test console, host computer three parts composition.The invention, as main control chip, is mainly included that functional modules, the various modules such as sensor module, communication module, external control amount input module, display module are all made of preferred embodiment, has the performance advantages such as real-time is good, stability is high using STM32 series.Host computer writes realization using C# language, and constructs the storage of database realizing engine operating parameter, provides convenience for the subsequent research and development of engine.
Description
Technical field
The present invention relates to aviation turbojet engine control fields, and the miniature aviation whirlpool of liquid fuel is especially used only
The control method of fuel-injection engine.
Background technique
The features such as informationization gradually shown with modern war, electronization is unmanned, localization, small drone are high
Fast target drone, scout missile, autonomous attack ammunition of low cost etc. become one of the important directions of development of future war weapon.As matching
Power device is covered, micro turbojet engine is also rapidly developed and is widely applied in recent years.It, will be small in addition to military domain
Type jet engine is applied to civilian aviation model field, and the jet for realizing model plane movement is crossed over.Although micro-satellite cluster is most bright
Aobvious feature is miniaturization, but it does not cut down the demand for control of system at all relative to general aero-engine, and
And difficulty is brought to the development of micro turbojet engine control technology and the product realization of control system since size is limited.
Field is researched and developed in Micro Turbine Jet Engine controller, many research institutions have carried out Micro Turbine Jet Engine control in succession
The work such as the research of algorithm processed, the realization of principle prototype and HWIL simulation, purpose are more for aero-engine application
Advanced Control Strategies provide reference.But because control system hardware software design framework is there are problem, cause each sensor,
Inefficiency, control accuracy difference during servo mechanism co-ordination, and each module is that simple accumulation is realized, is limited to module knot
Configuration formula and module cost, it is difficult to realize engineering, commercialization production.
Summary of the invention
The present invention is to provide for a kind of control method and device of Micro-Aviation Engine, meets and liquid fuel is used only
Demand of the turbojet engine to control system overcomes control system hardware and software framework of the existing technology unreasonable, at high cost
Not the problem of not being able to achieve engineering.
To achieve the purpose of the present invention, present invention provide the technical scheme that
A kind of control device of miniature turbo-jet engine, including engine control unit, engine bench test console and host computer；
The engine control unit uses STM32F4xx Series MCU as hardware platform, including coupled sensor group
Part, first communication module and engine operation module.The sensor module includes EGT sensor, speed probe, air speed biography
Sensor, intake air temperature sensor and fuel pressure transmitter；Engine operation module includes igniter module, starting fuel valve mould
Block, main fuel valve module, fuel pump module and starting motor module；First communication module realizes that engine control unit and rack are surveyed
Try the communication between console.
Further, the engine bench test console is using STM32F103 Series MCU as hardware platform, including display
The of module, second communication module, third communication module and control amount input module, second communication module and engine control unit
One communication module is connected, and host computer is connected with the third communication module of engine bench test console；The platform is that user's realization is started
The operating platform of machine control, and the data exchange with engine control unit and host computer is completed, the acquisition of display engine control unit
Data.
According to a kind of control method of above-mentioned miniature turbo-jet engine, in the engine bench test console second
Communication module is connected using RS-485 communication protocol with the first communication module of engine control unit, realizes data exchange；It is upper
Machine is connected with the third communication module of engine bench test console, realizes the data exchange of host computer and engine bench test console；This
Invention devise " process-closed loop " combine, the control strategy of " more closed loop-whole processes ".
Further, described " process-closed loop " combines, " more closed loop-whole processes " control strategy is embedded in using more peripheral hardwares
Formula simulation, digital and electronic control application technology realize information collection and operation control；To each course of work of engine using refinement
The design that is combined with closed loop fuzzy PID control strategy of Arius process control, and more biographies are all made of in all control Arius journeys
The control strategy of the more closed loops of sensor.
Compared with prior art, the invention has the advantages that
1, apparatus of the present invention realize the acquisition of engine operating condition using High Speed Embedded Processor and multi-sensor technology.Using more
Peripheral hardware embedded digital electronic control application technology realizes that information shows and run control.Design efficient control strategy and control
Rule realize engine operating state closed-loop control, reach " device control under engine can not only pass through manual operation
Test run also can independently realize highly effective and safe stable operation " control effect.
2, it is able to achieve engine using the device to start automatically, the starting time is reduced to 30S or so, and can monitor in real time
The operating status of engine.
3, reasonable system architecture makes the efficient co-ordination of each sensor, and circuit design reduces costs.
Detailed description of the invention
Fig. 1 is general structure schematic diagram of the invention；
Fig. 2 is more Closed-loop Control Strategy block diagrams；
Fig. 3 is engine operation process schematic diagram；
Fig. 4 is engine control unit (ECU) hardware block diagram；
Fig. 5 is engine control unit (ECU) software flow pattern；
Fig. 6 is engine bench test console hardware block diagram；
Fig. 7 is engine bench test console software flow pattern.
Specific embodiment:
Below in conjunction with the embodiment of the present invention and attached drawing, technical solution in the embodiment of the present invention is clearly and completely retouched
It states.
Referring to Fig. 1, a kind of control device of miniature turbine jet engines provided by the invention.The device is mainly by engine
Control unit (ECU), engine bench test console, upper structure at.
Engine control unit uses STM32F4xx Series MCU as hardware platform, including coupled sensor group
Part, first communication module and engine operation module.The sensor module includes EGT sensor, speed probe, air speed biography
Sensor, intake air temperature sensor and fuel pressure transmitter；Engine operation module includes igniter module, starting fuel valve mould
Block, main fuel valve module, fuel pump module and starting motor module；First communication module realizes that engine control unit and rack are surveyed
Try the communication between console.
Engine bench test console is using STM32F103 Series MCU as hardware platform, including display module, the second communication
Module, third communication module and control amount input module, the first communication module phase of second communication module and engine control unit
Even, host computer is connected with the third communication module of engine bench test console；The platform is the operation that user realizes engine control
Platform, and the data exchange with engine control unit and host computer is completed, the data of display engine control unit acquisition.
According to a kind of control method of above-mentioned miniature turbo-jet engine, second in engine bench test console is communicated
Module is connected using RS-485 communication protocol with the first communication module of engine control unit, realizes data exchange；Host computer with
The third communication module of engine bench test console is connected, and realizes the data exchange of host computer and engine bench test console；The present invention
Devise " process-closed loop " combine, the control strategy of " more closed loop-whole processes ".
Further, " process-closed loop " combines, " more closed loop-whole processes " control strategy utilizes the embedded mould of more peripheral hardwares
Quasi-, digital and electronic control application technology realizes information collection and operation control；To each course of work of engine using the Asia of refinement
The design that Row control is combined with closed loop fuzzy PID control strategy, and multisensor is all made of in all control Arius journeys
The control strategy of more closed loops.
In whole device operational process, Starting mode, the fuel type of engine are selected by engine bench test console,
Control starting motor speed, accelerator open degree, igniter power etc., and engine control unit will be transmitted under these control instructions.Draw
The starting that control unit completes engine according to the control instruction received is held up, and utilizes the autonomous dynamic of closed loop PID control strategy
The parameters such as igniter power, starting fuel supply, the output of starting motor, main fuel supply when adjustment starting, it is ensured that turbine spray
The automatic safety stable operation of gas engine.Engine control unit will also acquire igniter function when engine start in real time
The data such as revolving speed, delivery temperature when rate, work, upload the data to engine bench test console.Engine bench test console is shown
Operating condition when engine is run, and these information processings are uploaded into host computer.Host computer is shown richer in a manner of more intuitive
Rich data mode, building database records engine operating condition in real time, and can issue the control parameter for needing to adjust as needed.
The present invention is directed the miniature aviation turbojet engine of neat liquid fuel.
As shown in Figure 2, a kind of control device of miniature turbine jet engines provided by the invention uses PID closed-loop control
Strategy.Input terminal control amount includes the parameters such as temperature, revolving speed, fuel pressure.The closed-loop control of each control amount is all made of close more
Ring negative feedback mode, it is ensured that engine being capable of safe and stable operation.
The start-up operation that engine is completed by engine bench test console mainly has automatic starting and manually boots two kinds of sides
Formula, engine operation process are as shown in Figure 3.Idling rating is initially entered after starting successfully, engine can stablize fortune at this time
Row but requirement when being not achieved use, then manual operation or adjust automatically operating parameter, reach engine work shape
State.It stops in emergency if the device that breaks down in the process can be realized, is generated with accident prevention.
As shown in Figure 4, engine control unit (ECU) includes sensor module, first communication module and engine operation mould
Block.First communication module receives the control information that rack test console transmits, and operational module is on according to the control information
Motor air inlet is opened igniter and is preheated, and being on fuel valve makes engine enter idling rating, opens main combustion at this time
Oil valve, engine enter normal operating conditions.It realizes in the process by each sensor to the monitoring of this process and timely
Adjust each parameter.EGT sensor realizes the test to delivery temperature, and speed probe realizes the monitoring to revolving speed, fuel pressure
Sensor realizes the monitoring to oil mass, and the data that each sensor obtains upload to engine bench test control by first communication module
Platform.
The software flow pattern of ECU is as shown in figure 5, each parameter initialization, detects working condition at this time, start if detecting
Machine is that automatic starting then carries out automatic Booting sequence, and engine starting process is as described above, if engine is to manually boot
It to be operated manually by console, complete the start-up course of engine.
It will be appreciated from fig. 6 that engine bench test console includes display module, second communication module, third communication module and control
Measure input module.Second communication module is connected with the first communication module of engine control unit, receives the engine work of its acquisition
Make situation.Engine behavior is shown using display module after the processing of main control chip completion information, while logical using third
Letter module uploads to host computer and carries out finer display and storage.External input list when control amount input module is manual operation
Control information processing is passed through first communication module later and descends into engine control unit realization to engine by member, main control unit
Control.Control amount input module mainly includes Starting mode control amount, oil pump control amount, motor control amount and fuel selection control
Amount processed.
Engine bench test console software flow reads the control amount of input as shown in fig. 7, system initialization, by data group
Packet is transferred to ECU, and receives the data that host computer and ECU are returned and carry out status display.
Host computer realizes the display of each parameter in engine operation process, and utilizes each in data-base recording operational process
Supplemental characteristic, to carry out later period inquiry.Engine under normal operating conditions join by EGT, thrust magnitude, real-time revolving speed, oil pump etc.
Number preferably must be held in zone of reasonableness.The variation that operating status parameter is recorded by host computer, when a failure occurs can basis
Parameter Variation debugging.
The foregoing is merely the preferred embodiment of the present invention, are not intended to limit the scope of the invention.
Claims (4)
1. a kind of control device of miniature turbo-jet engine, it is characterised in that: including engine control unit, engine bench test control
Platform and host computer processed；
The engine control unit uses STM32F4xx Series MCU as hardware platform, including coupled sensor group
Part, first communication module and engine operation module；
The sensor module includes EGT sensor, speed probe, airspeed sensor, intake air temperature sensor and fuel oil pressure
Force snesor；Engine operation module includes igniter module, starting fuel oil valve module, main fuel valve module, fuel pump module
With starting motor module；First communication module realizes the communication between engine control unit and engine bench test console.
2. a kind of control device of miniature turbo-jet engine according to claim 1, it is characterised in that: the rack
Test console is using STM32F103 Series MCU as hardware platform, including display module, second communication module, the third communication
Module and control amount input module, second communication module are connected with the first communication module of engine control unit, host computer and platform
The third communication module of frame test console is connected；The platform be user realize engine control operating platform, and complete with
The data exchange of engine control unit and host computer, the data of display engine control unit acquisition.
3. a kind of control method of miniature turbo-jet engine according to claim 1, it is characterised in that: the rack
Second communication module in test console is connected using RS-485 communication protocol with the first communication module of engine control unit,
Realize data exchange；Host computer is connected with the third communication module of engine bench test console, realizes host computer and engine bench test control
The data exchange of platform processed；The present invention devise " process-closed loop " combine, the control strategy of " more closed loop-whole processes ".
4. a kind of control method of miniature turbo-jet engine according to claim 3, it is characterised in that: " the stream
Journey-closed loop " combines, " more closed loop-whole processes " control strategy is controlled using the embedded simulation of more peripheral hardwares, digital and electronic using skill
Art realizes information collection and operation control；Arius process control and closed loop fuzzy PID to each course of work of engine using refinement
The design that control strategy combines, and the control strategies of the more closed loops of multisensor is all made of in all control Arius journeys.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811518646.3A CN109667673B (en) | 2018-12-12 | 2018-12-12 | Control method and device for miniature aviation turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811518646.3A CN109667673B (en) | 2018-12-12 | 2018-12-12 | Control method and device for miniature aviation turbojet engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109667673A true CN109667673A (en) | 2019-04-23 |
| CN109667673B CN109667673B (en) | 2021-04-06 |
Family
ID=66144352
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811518646.3A Expired - Fee Related CN109667673B (en) | 2018-12-12 | 2018-12-12 | Control method and device for miniature aviation turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109667673B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113074949A (en) * | 2021-04-02 | 2021-07-06 | 南京赛恩通航科技有限公司 | System and method for detecting parameters of miniature aviation turbojet engine |
| CN114508421A (en) * | 2021-12-14 | 2022-05-17 | 泸州懋威科技有限公司 | Microminiature aircraft engine control system and operation method thereof |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1298512A2 (en) * | 2001-09-26 | 2003-04-02 | Coltec Industries Inc. | Adaptive aero-thermodynamic engine model |
| CN103161579A (en) * | 2011-12-14 | 2013-06-19 | 西安广融电气有限公司 | RTOS based turbojet engine digital control system |
| CN102507204B (en) * | 2011-11-18 | 2014-11-26 | 北京航空航天大学 | Movable micro turbine jet engine test bed |
| CN104819847A (en) * | 2015-04-20 | 2015-08-05 | 四川迈迪测控技术有限公司 | Miniature turbojet aero-engine ground measurement and control system |
| EP3054125A1 (en) * | 2015-02-06 | 2016-08-10 | United Technologies Corporation | Variable geometry gas turbine engine for use in inclement weather |
| CN205605310U (en) * | 2016-04-22 | 2016-09-28 | 山东元一动力科技有限公司 | Miniature turbojet engine integrated control system |
| CN106872172A (en) * | 2017-04-19 | 2017-06-20 | 成都信息工程大学 | The method for real time discriminating and system of Aero Engine Testing security parameter monitoring |
| CN107905900A (en) * | 2017-10-25 | 2018-04-13 | 北京航天宏恩动力技术有限公司 | Miniature turbine jet engines fuel oil control method and device, storage medium |
| CN108150294A (en) * | 2017-11-29 | 2018-06-12 | 北京动力机械研究所 | A kind of Micro Turbine Jet Engine variable-gain speed closed loop control method |
| CN208206488U (en) * | 2018-06-15 | 2018-12-07 | 上海睿瑞航空设备科技有限公司 | A kind of new micro turbojet engine is test bed |
-
2018
- 2018-12-12 CN CN201811518646.3A patent/CN109667673B/en not_active Expired - Fee Related
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1298512A2 (en) * | 2001-09-26 | 2003-04-02 | Coltec Industries Inc. | Adaptive aero-thermodynamic engine model |
| CN102507204B (en) * | 2011-11-18 | 2014-11-26 | 北京航空航天大学 | Movable micro turbine jet engine test bed |
| CN103161579A (en) * | 2011-12-14 | 2013-06-19 | 西安广融电气有限公司 | RTOS based turbojet engine digital control system |
| EP3054125A1 (en) * | 2015-02-06 | 2016-08-10 | United Technologies Corporation | Variable geometry gas turbine engine for use in inclement weather |
| CN104819847A (en) * | 2015-04-20 | 2015-08-05 | 四川迈迪测控技术有限公司 | Miniature turbojet aero-engine ground measurement and control system |
| CN205605310U (en) * | 2016-04-22 | 2016-09-28 | 山东元一动力科技有限公司 | Miniature turbojet engine integrated control system |
| CN106872172A (en) * | 2017-04-19 | 2017-06-20 | 成都信息工程大学 | The method for real time discriminating and system of Aero Engine Testing security parameter monitoring |
| CN107905900A (en) * | 2017-10-25 | 2018-04-13 | 北京航天宏恩动力技术有限公司 | Miniature turbine jet engines fuel oil control method and device, storage medium |
| CN108150294A (en) * | 2017-11-29 | 2018-06-12 | 北京动力机械研究所 | A kind of Micro Turbine Jet Engine variable-gain speed closed loop control method |
| CN208206488U (en) * | 2018-06-15 | 2018-12-07 | 上海睿瑞航空设备科技有限公司 | A kind of new micro turbojet engine is test bed |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113074949A (en) * | 2021-04-02 | 2021-07-06 | 南京赛恩通航科技有限公司 | System and method for detecting parameters of miniature aviation turbojet engine |
| CN114508421A (en) * | 2021-12-14 | 2022-05-17 | 泸州懋威科技有限公司 | Microminiature aircraft engine control system and operation method thereof |
| CN114508421B (en) * | 2021-12-14 | 2023-05-05 | 泸州懋威科技有限公司 | Microminiature aeroengine control system and operation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109667673B (en) | 2021-04-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2020093264A1 (en) | Design method for optimizing aero-engine transition state control law | |
| CN106321252B (en) | The starting process fuel oil control method and system of a kind of aero-engine | |
| CN1966955B (en) | Estimation system of gas turbine engine component qualities | |
| US9481473B2 (en) | Distributed control system with smart actuators and sensors | |
| EP3135885A1 (en) | Feed forward exhaust throttle and wastegate control for an engine | |
| Montazeri-Gh et al. | Real-time multi-rate HIL simulation platform for evaluation of a jet engine fuel controller | |
| CN109441644A (en) | A kind of fanjet stable state transition state multi-variant control method based on active disturbance rejection theory | |
| CN109667673A (en) | The control method and device of miniature turbo-jet engine | |
| CN102400735A (en) | Control and diagnostic systems for a variable capacity engine oil pump and an engine oil pressure sensor | |
| CN101256117A (en) | Device and method for testing synthesis parameter of aviation piston engine | |
| CN102345529A (en) | Method of model-based multivariable control of egr and boost for internal combustion engines | |
| CN102419222A (en) | Outside air temperature sensor diagnostic systems for a vehicle | |
| CN105606368A (en) | Solid rocket engine gas flow adjustment cold-flow and hot-flow ground test systems | |
| Főző et al. | Description of an intelligent small turbo-compressor engine with variable exhaust nozzle | |
| CN201526375U (en) | On-chip distributed aircraft engine electronic controller based on FPGA | |
| CN116220919A (en) | Aviation piston two-stroke electronic injection control method and device | |
| CN102733978A (en) | Control system and method for a homogeneous charge compression ignition (hcci) engine | |
| CN103235519B (en) | A kind of engine signal Intelligence Simulation and system | |
| CN108150294A (en) | A kind of Micro Turbine Jet Engine variable-gain speed closed loop control method | |
| EP2971651B1 (en) | Methods for operating a gas turbine engine | |
| CN112947378A (en) | Turbojet engine fault-tolerant test system and method based on unmanned aerial vehicle carrying platform | |
| Beneda et al. | Development of data acquisition system and hardware simulator for turbojet engine test bench using alternative fuels | |
| Chen et al. | Design of control laws based on inverted decoupling and LMI for a turboprop engine | |
| CN112081671A (en) | Gas turbine fuel control device and simulation test method based on same | |
| CN104948327B (en) | The system and method for managing the cycle of the control loop of 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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210406 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |