CN109667673B - Control method and device for miniature aviation turbojet engine - Google Patents
Control method and device for miniature aviation turbojet engine Download PDFInfo
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- CN109667673B CN109667673B CN201811518646.3A CN201811518646A CN109667673B CN 109667673 B CN109667673 B CN 109667673B CN 201811518646 A CN201811518646 A CN 201811518646A CN 109667673 B CN109667673 B CN 109667673B
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- 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
Abstract
The invention discloses a control method and a control device for a miniature aviation turbojet engine, and relates to the field of control of turbojet engines. The invention mainly realizes the full-flow control of the pure liquid fuel turbojet engine, and completes the automatic starting and the monitoring of the running state of the engine. The invention mainly comprises an Engine Control Unit (ECU), a bench test console and an upper computer. The STM32 series is used as a main control chip, and the STM32 series mainly comprises a sensor module, a communication module, an external control quantity input module, a display module and other functional modules, and various modules adopt an optimal scheme, so that the STM32 series has the performance advantages of good real-time performance, high stability and the like. The upper computer is compiled and realized by adopting C # language, and the database is constructed to realize the storage of the running parameters of the engine, thereby providing convenience for the subsequent research and development of the engine.
Description
Technical Field
The invention relates to the field of control of aviation turbojet engines, in particular to a control method of a miniature aviation turbojet engine only using liquid fuel.
Background
Along with the characteristics of informatization, electronization, unmanned, localization and the like which are gradually shown in modern war, a small unmanned aerial vehicle, a high-speed target drone, a patrol missile, low-cost autonomous attack ammunition and the like become one of important directions for the development of war weapons in the future. As a matched power device, the microminiature turbojet engine is also rapidly developed and widely applied in recent years. Except for the military field, the microminiature jet engine is applied to the field of civil aeromodelling, and jet crossing of aeromodelling movement is realized. Although the microminiature engine is most obviously characterized by miniaturization, the control requirement of the system is not reduced by a little compared with the general aircraft engine, and the size limit causes difficulty in the development of the microminiature turbojet engine control technology and the realization of the control system.
In the research and development field of the micro turbojet engine controller, a plurality of research organizations successively develop the research of the control algorithm of the micro turbojet engine, the realization of a principle prototype, semi-physical simulation and other works, and the purpose of the research organizations is to provide reference and reference for the application of advanced control strategies to the aero-engine. However, due to the problems of the hard and software design architectures of the control system, the efficiency and the control precision of the coordination working process of each sensor and the servo mechanism are low, and each module is realized by simple accumulation, is limited by the structural form and the cost of the module, and is difficult to realize engineering and production.
Disclosure of Invention
The invention aims to provide a control method and a control device of a miniature aero-engine, which meet the requirements of a turbojet engine only using liquid fuel on a control system and overcome the problems of hard control system, unreasonable software architecture, high cost and failure in engineering in the prior art.
In order to realize the purpose of the invention, the technical scheme provided by the invention is as follows:
a control device of a miniature aviation turbojet engine comprises an engine control unit, a rack test control console and an upper computer;
the engine control unit adopts STM32F4xx series MCU as a hardware platform, and comprises a sensor assembly, a first communication module and an engine working module which are connected with the engine control unit. The sensor assembly comprises an EGT sensor, a rotating speed sensor, an airspeed sensor, an air inlet temperature sensor and a fuel pressure sensor; the engine working module comprises an igniter module, a starting fuel valve module, a main fuel valve module, a fuel pump module and a starting motor module; the first communication module enables communication between the engine control unit and the bench test console.
Furthermore, the rack test console adopts STM32F103 series MCU as a hardware platform, and comprises a display module, a second communication module, a third communication module and a control quantity input module, wherein the second communication module is connected with the first communication module of the engine control unit, and the upper computer is connected with the third communication module of the rack test console; the platform is an operation platform for realizing engine control by a user, completes data exchange with an engine control unit and an upper computer, and displays data acquired by the engine control unit.
According to the control method of the miniature aviation turbojet engine, the second communication module in the bench test console is connected with the first communication module of the engine control unit by adopting an RS-485 communication protocol to realize data exchange; the upper computer is connected with a third communication module of the rack test console to realize data exchange between the upper computer and the rack test console; the invention designs a 'process-closed loop' combined 'multi-closed loop-full process' control strategy.
Furthermore, the flow-closed loop combined and multi-closed loop-full flow control strategy realizes information acquisition and operation control by using a multi-peripheral embedded analog and digital electronic control application technology; the design of combining detailed sub-process control and closed-loop fuzzy PID control strategy is adopted for each working process of the engine, and a multi-sensor multi-closed-loop control strategy is adopted in all the control sub-processes.
Compared with the prior art, the invention has the advantages that:
1. the device of the invention realizes the acquisition of the working condition of the engine by utilizing a high-speed embedded processor and a multi-sensor technology. And the information display and operation control are realized by utilizing a multi-peripheral embedded digital electronic control application technology. Efficient control strategies and control rules are designed to realize closed-loop control of the running state of the engine, and the control effect that the engine under the control of the device can not only run through manual operation tests, but also can independently realize efficient, safe and stable running is achieved.
2. The device can realize automatic starting of the engine, shorten the starting time to about 30S, and monitor the running state of the engine in real time.
3. The reasonable system architecture enables the sensors to work efficiently and coordinately, and the circuit design reduces the cost.
Drawings
FIG. 1 is a schematic diagram of the general structure of the present invention;
FIG. 2 is a block diagram of a multi-closed loop control strategy;
FIG. 3 is a schematic diagram of an engine operating process;
FIG. 4 is a hardware block diagram of an Engine Control Unit (ECU);
FIG. 5 is a flow chart of Engine Control Unit (ECU) software;
FIG. 6 is a block diagram of the bench test console hardware;
FIG. 7 is a flow chart of the bench test console software.
The specific implementation mode is as follows:
the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the embodiments of the present invention and the accompanying drawings.
Referring to fig. 1, the present invention provides a control device for a micro turbojet engine. The device mainly comprises an Engine Control Unit (ECU), a bench test console and an upper mechanism.
The engine control unit adopts STM32F4xx series MCU as a hardware platform, and comprises a sensor assembly, a first communication module and an engine working module which are connected with the engine control unit. The sensor assembly comprises an EGT sensor, a rotating speed sensor, an airspeed sensor, an air inlet temperature sensor and a fuel pressure sensor; the engine working module comprises an igniter module, a starting fuel valve module, a main fuel valve module, a fuel pump module and a starting motor module; the first communication module enables communication between the engine control unit and the bench test console.
The rack test console adopts STM32F103 series MCU as a hardware platform and comprises a display module, a second communication module, a third communication module and a control quantity input module, wherein the second communication module is connected with the first communication module of the engine control unit, and the upper computer is connected with the third communication module of the rack test console; the platform is an operation platform for realizing engine control by a user, completes data exchange with an engine control unit and an upper computer, and displays data acquired by the engine control unit.
According to the control method of the miniature aviation turbojet engine, the second communication module in the bench test console is connected with the first communication module of the engine control unit by adopting an RS-485 communication protocol to realize data exchange; the upper computer is connected with a third communication module of the rack test console to realize data exchange between the upper computer and the rack test console; the invention designs a 'process-closed loop' combined 'multi-closed loop-full process' control strategy.
Furthermore, the 'process-closed loop' combination and 'multi-closed loop-full process' control strategy realizes information acquisition and operation control by using a multi-peripheral embedded analog and digital electronic control application technology; the design of combining detailed sub-process control and closed-loop fuzzy PID control strategy is adopted for each working process of the engine, and a multi-sensor multi-closed-loop control strategy is adopted in all the control sub-processes.
In the whole device operation process, the starting mode and the fuel type of the engine are selected through the bench test console, the rotating speed of the starting motor, the opening degree of an accelerator, the power of an igniter and the like are controlled, and the control instructions are transmitted to the engine control unit. The engine control unit finishes the starting of the engine according to the received control instruction, and automatically and dynamically adjusts parameters such as igniter power, starting fuel supply, starting motor output, main fuel supply and the like during starting by utilizing a closed-loop PID control strategy, so that the full-automatic safe and stable operation of the turbojet engine is ensured. The engine control unit also needs to acquire data such as igniter power when the engine is started, rotating speed when the engine works, exhaust temperature and the like in real time and upload the data to the bench test console. And the bench test console displays the working condition of the engine during operation and uploads the information to the upper computer after processing. The upper computer displays richer data states in a more visual mode, constructs a database to record the working conditions of the engine in real time, and can issue control parameters needing to be adjusted according to requirements.
The present invention is directed to a liquid-fueled micro-aircraft turbojet engine.
As can be seen from fig. 2, the control device for a micro turbojet engine according to the present invention employs a PID closed-loop control strategy. The input end control quantity comprises parameters such as temperature, rotating speed and fuel pressure. The closed-loop control of each control quantity adopts a multi-closed-loop negative feedback mode, so that the safe and stable operation of the engine is ensured.
The starting operation of the engine is completed through the bench test console, two modes of automatic starting and manual starting are mainly adopted, and the running process of the engine is shown in figure 3. After the starting is successful, the slow-speed vehicle enters a slow-speed vehicle state firstly, the engine can stably run but cannot meet the requirement in use, and then the running parameters are manually operated or automatically adjusted to reach the normal working state of the engine. If faults occur in the process, the device can realize emergency stop so as to prevent accidents.
As can be seen from fig. 4, an Engine Control Unit (ECU) includes a sensor assembly, a first communication module, and an engine operation module. The first communication module receives control information transmitted by the bench test console, the working module opens the starting motor to admit air according to the control information, opens the igniter to preheat, opens the starting fuel valve to enable the engine to enter a slow-speed vehicle state, opens the main fuel valve at the moment, and enables the engine to enter a normal working state. In the process, the monitoring of the process is realized by each sensor, and each parameter is adjusted in time. The EGT sensor realizes the test of exhaust temperature, and speed sensor realizes the control to the rotational speed, and fuel pressure sensor realizes the control to the oil mass, and the rack test control platform is uploaded to the data that each sensor obtained through first communication module.
As shown in fig. 5, the software flowchart of the ECU initializes each parameter, detects the operating state at that time, and performs the automatic start process if it is detected that the engine is automatically started, and the engine start process is as described above.
As can be seen from fig. 6, the bench test console includes a display module, a second communication module, a third communication module, and a control quantity input module. The second communication module is connected with the first communication module of the engine control unit and receives the collected working conditions of the engine. The main control chip displays the working state of the engine by using the display module after finishing the processing of information, and uploads the working state to the upper computer by using the third communication module for more detailed display and storage. The control quantity input module is an external input unit during manual operation, and the main control unit processes the control information and then downloads the control information to the engine control unit through the first communication module to realize control over the engine. The control quantity input module mainly comprises a starting mode control quantity, an oil pump control quantity, a motor control quantity and a fuel selection control quantity.
The software flow of the bench test console is shown in fig. 7, the system is initialized, the input control quantity is read, the data packet is transmitted to the ECU, and the data returned by the upper computer and the ECU are received for state display.
The upper computer realizes the display of each parameter in the running process of the engine, and records the data of each parameter in the running process by utilizing the database so as to carry out later-stage query. Parameters such as EGT, thrust value, real-time rotating speed, oil pump and the like of the engine in a normal running state must be kept in a reasonable range. The upper computer records the change of each parameter of the running state, and when a fault occurs, the fault can be eliminated according to the parameter change rule.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention.
Claims (3)
1. The utility model provides a control device of miniature aviation turbojet engine which characterized in that: the system comprises an engine control unit, a bench test console and an upper computer;
the engine control unit adopts an STM32F4xx series MCU as a hardware platform and comprises a sensor assembly, a first communication module and an engine working module which are connected with the engine control unit;
the sensor assembly comprises an EGT sensor, a rotating speed sensor, an airspeed sensor, an air inlet temperature sensor and a fuel pressure sensor; the engine working module comprises an igniter module, a starting fuel valve module, a main fuel valve module, a fuel pump module and a starting motor module; the first communication module realizes communication between the engine control unit and the bench test console;
the control device designs a 'process-closed loop' combined 'multi-closed loop-full process' control strategy;
the flow-closed loop combined and multi-closed loop-full flow control strategy realizes information acquisition and operation control by using a multi-peripheral embedded analog and digital electronic control application technology; the design of combining detailed sub-process control and closed-loop fuzzy PID control strategy is adopted for each working process of the engine, and a multi-sensor multi-closed-loop control strategy is adopted in all the control sub-processes.
2. The control device of a micro-aero turbojet engine as claimed in claim 1, wherein: the bench test console adopts STM32F103 series MCU as a hardware platform and comprises a display module, a second communication module, a third communication module and a control quantity input module, wherein the second communication module is connected with the first communication module of the engine control unit, and the upper computer is connected with the third communication module of the bench test console; the platform is an operation platform for realizing engine control by a user, completes data exchange with an engine control unit and an upper computer, and displays data acquired by the engine control unit.
3. The control device of a micro-aero turbojet engine as claimed in claim 1, wherein: a second communication module in the rack test console is connected with a first communication module of the engine control unit by adopting an RS-485 communication protocol to realize data exchange; the upper computer is connected with a third communication module of the rack test console, and data exchange between the upper computer and the rack test console is realized.
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| 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 |
| 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 |
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