Electrical control system suitable for aero-engine ground modification application

Abstract

The utility model discloses an electrical control system suitable for aero-engine ground modification application, which comprises a power supply module (1), a control module (2), a human-computer interface (3), a console (4), an accelerator control module (5) and a starting module (6), and the power supply module (1) is respectively connected with the control module (2), the human-computer interface (3) and the starting module (6). The accelerator control module (5) comprises a fuel oil supply assembly and an accelerator opening degree control assembly, the control module (2) is electrically connected with the human-computer interface (3), the starting module (6), the fuel oil supply assembly and the accelerator opening degree control assembly, the fuel oil supply assembly is connected with the aero-engine (7), and the accelerator opening degree control assembly is connected with a fuel adjusting rocker arm of the aero-engine (7). And the human-computer interface (3) is arranged on the console (4).

Description

Technical Field

[0001] The utility model belongs to the technical field of electrical control, and in particular relates to an electrical control system suitable for ground modification of aircraft engines. Background Art

[0002] When an aircraft engine is installed on an aircraft, it is controlled by an onboard control system. These control components are usually installed on the aircraft and are not equipped with the engine, such as the starter box, air starter / electric starter, mechanical throttle assembly, etc. When the aircraft engine is transferred to ground use, these control components remain on the aircraft and are not equipped with the engine, so they cannot form a complete engine control system, and manual control signals cannot be transmitted to the engine itself. The missing control components need to be redesigned.

[0003] When aircraft engines are used on aircraft, they usually require special power supplies of various types. Most control components are powered by DC 27V, and some components require special power supplies, such as the intake angular displacement sensor requires a 36V / 400Hz excitation power supply, the surge pressure signal requires a 12V / 2KHz excitation power supply, and the engine vibration sensor signal is an AC voltage signal. These power supply methods and signal types are different from those on the ground, which also limits the modification and use of aircraft engines on the ground. Therefore, it is necessary to re-develop the design or selection of the power supply, sensors, actuators, etc. in the engine control system.

[0004] In addition, the control operation of aircraft engines is relatively professional and cumbersome, and usually requires professional training before operation. Operators need to pay attention to the many instruments in the cockpit at all times, manually operate the switch and throttle lever, and make real-time control adjustments according to the engine status. After the change to ground application, the user becomes an ordinary operator, who cannot perform correct operation. Therefore, a series of simplifications are needed to its electrical control system to make it easy to operate, one-button control, and over-control protection.

[0005] At present, many solutions still use mechanical starter boxes and mechanical push rods to control the throttle. The advantage of mechanical rod control is that it is simple and direct, and does not rely on the power supply system; the problem is that the processing, manufacturing and installation are cumbersome, and the work efficiency is low; secondly, the movement clearance of the connecting rod mechanism is large, and the connecting rod is easy to deform.

[0006] The onboard starter box is large in size, complex in structure, and has a high failure rate, making it unsuitable for ground use. The circuit principle of the starter box on an aircraft is complex, and the circuit is composed of numerous switches, relays, cams and other mechanisms. It is exquisitely designed, but the structure is complex, and the failure rate will inevitably be high after long-term use.

[0007] Servo motors are commonly used in throttle control in electronic control solutions. Compared with mechanical levers, servo motors have higher control accuracy, but they are expensive, heavy, difficult to install, have high power consumption, and require a lot of electricity.

[0008] In the electronic control scheme, a controller combining a single-chip microcomputer and a simple circuit is generally used to control the fuel. This scheme has poor scalability and reliability and is not suitable for use in harsh industrial environments.

[0009] In the onboard control system, there is no automatic detection of the prohibited start conditions, which mainly rely on manual inspection, and there is no automated method to detect with high reliability.

[0010] Therefore, it is necessary to simplify the electrical control to make it easy to operate, one-button controllable and with over-control protection. Utility Model Content

[0011] The purpose of the utility model is to solve the problems of the prior art and to provide an electrical control system suitable for ground modification applications of aircraft engines. The technical problem solved is how to ensure that the aircraft engine can achieve start-up and throttle control, electrical control and power supply, manual operation and override automatic safety protection on the ground.

[0012] In order to solve the technical problem, the technical solution of the utility model is: an electrical control system suitable for ground modification applications of aircraft engines, including a power supply module, a control module, a human-machine interface, a console, a throttle control module and a starting module, the power supply module is respectively connected to the control module, the human-machine interface and the starting module, the throttle control module includes a fuel supply component and a throttle opening control component, the control module is respectively electrically connected to the human-machine interface, the starting module, the fuel supply component and the throttle opening control component, the fuel supply component is connected to the aircraft engine, the throttle opening control component is connected to the fuel adjustment rocker arm of the aircraft engine, and the human-machine interface is installed on the console.

[0013] Preferably, the power supply module consists of a main power system and a redundant power supply, the main power system is 24V, and the main power system and the redundant power supply are electrically connected to the control module, the human-machine interface and the starting module respectively.

[0014] Preferably, the control module includes a PLC controller, a sensor, a transmitter, an isolation module and an actuator, the output ends of the sensor and the transmitter are respectively connected to the isolation module, the output end of the isolation module is connected to the PLC controller, the output end of the PLC controller is connected to the actuator, and the PLC controller is respectively electrically connected to the human-machine interface, the throttle control module and the starting module.

[0015] Preferably, the fuel supply assembly includes a fuel tank, a fuel pump, a fuel pipeline, a pipeline solenoid valve, a manual master valve and a fuel pressure transmitter. The fuel tank is connected to the fuel pump through the fuel pipeline. A manual master valve is provided on the fuel pipeline between the fuel tank and the fuel pump. The fuel pump is connected to the aircraft engine through the fuel pipeline. A pipeline solenoid valve and a fuel pressure transmitter are provided on the fuel pipeline between the fuel pump and the aircraft engine. The pipeline solenoid valve and the fuel pressure transmitter are electrically connected to the PLC controller respectively.

[0016] Preferably, the throttle opening control component includes a throttle lever, a forward relay, a reverse relay and a throttle motor, the throttle lever is installed on the console, the throttle lever is connected to the isolation module, the isolation module is connected to the PLC controller, the PLC controller is electrically connected to the forward relay and the reverse relay, respectively, the forward relay and the reverse relay respectively control the extension and retraction of the throttle motor, and the throttle motor is connected to the fuel adjustment rocker arm of the aircraft engine to increase or decrease the throttle.

[0017] Preferably, the sensor includes a displacement sensor, a pressure sensor and a liquid level sensor; the displacement sensor is fixed on the throttle motor, and the pull rope head of the displacement sensor moves synchronously with the push rod head of the throttle motor; there are two pressure sensors, and the two pressure sensors are respectively installed in front of the fuel nozzle and after the lubricating oil filter of the aircraft engine; the liquid level sensor is installed on the fuel tank.

[0018] Preferably, the starting module includes an ignition relay, an engine ignition accessory, a hydraulic oil tank, a hydraulic pump, a hydraulic pipeline, a hydraulic solenoid valve and a hydraulic motor. The ignition relay is respectively connected to the power supply module and the PLC controller, the output end of the ignition relay is connected to the engine ignition accessory, the engine ignition accessory is connected to the ignition nozzle of the aircraft engine, the output end of the hydraulic oil tank is connected to the hydraulic pump through a hydraulic pipeline, the output end of the hydraulic pump is connected to the hydraulic solenoid valve through a hydraulic pipeline, the hydraulic solenoid valve is respectively connected to the hydraulic motor and the hydraulic oil tank, and the hydraulic motor is connected to the high-pressure rotor of the aircraft engine.

[0019] Preferably, a human-machine interface touch screen, a fire button, an oil pump button, a pipeline solenoid valve button and a throttle joystick are installed on the console, and the human-machine interface touch screen, the fire button, the oil pump button and the pipeline solenoid valve button are electrically connected to the PLC controller respectively.

[0020] Preferably, the human-machine interface touch screen displays high-speed rotor speed, low-pressure rotor speed, exhaust temperature, fuel pressure, lubricating oil pressure, vibration, lubricating oil temperature, signal light, start mode and throttle position.

[0021] Compared with the prior art, the advantages of the utility model are:

[0022] (1) The utility model discloses an electrical control system suitable for ground modification of aircraft engines, comprising a power supply module, a control module, a human-machine interface, a control console, a throttle control module and a starting module. The power supply module supplies power to each module. The control module is used to control the human-machine interface, the throttle control module and the starting module. The human-machine interface is installed on the control console. The throttle control module comprises a fuel supply component and a throttle opening control component. The fuel supply component is connected to the aircraft engine. The throttle opening control component is connected to the fuel adjustment rocker arm of the aircraft engine. The throttle joystick of the throttle opening control component is also installed on the control console. Both the fuel supply component and the throttle opening control component can be controlled by the human-machine interface. The throttle opening control component can also be controlled by the throttle joystick alone. The components are simply connected and have high control efficiency.

[0023] (2) The utility model uses a PLC controller to replace the starter box control method, which greatly simplifies the complex structure and reduces the failure rate; the use of electronic control can ensure accurate and rapid control, and faults can be detected automatically in a timely manner; the throttle motor used has greatly reduced price, weight and power, and has higher energy economy; the use of a hydraulic motor to replace the original air starter of the engine greatly reduces the size of the starter and reduces costs; the use of a reliable PLC controller is suitable for relatively harsh environments and can make corresponding control adjustments in a very short time. Compared with manual mechanical throttle operation, it has higher timeliness and is more conducive to ensuring engine safety;

[0024] (3) The control system of the utility model can automatically detect the prohibition of starting, suspension of starting, major faults, etc. through the PLC controller, detect various parameters of the aircraft engine before starting, during the starting process and under normal operating conditions, respond to fault information, and display various operating parameters and alarm information of the aircraft engine in real time on the human-machine interface;

[0025] (4) The control system of the utility model has undergone a series of simplifications, making the electrical control easy to operate and achieving one-button control and over-control protection. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 , a schematic diagram of an electrical control system suitable for ground modification of aircraft engines according to the utility model;

[0027] Figure 2 , a schematic diagram of a control module of an electrical control system suitable for ground modification of an aircraft engine according to the utility model;

[0028] Figure 3 , a schematic diagram of a human-machine interface of an electrical control system suitable for ground modification of aircraft engines according to the utility model;

[0029] Figure 4, a schematic diagram of a control console of an electrical control system suitable for ground modification of an aircraft engine according to the utility model;

[0030] Figure 5 , a schematic diagram of a fuel supply assembly of an electrical control system suitable for ground modification of an aircraft engine according to the utility model;

[0031] Figure 6 , a schematic diagram of a throttle opening control component of an electrical control system suitable for ground modification of an aircraft engine according to the utility model;

[0032] Figure 7 , a schematic diagram of a start-up module of an electrical control system suitable for ground modification of an aircraft engine according to the utility model;

[0033] Figure 8 , a schematic diagram of a starting module of an electrical control system suitable for ground modification of an aircraft engine according to the utility model.

[0034] Description of reference numerals:

[0035] 1. Power supply module, 2. Control module, 3. Human-machine interface, 4. Control console, 5. Throttle control module, 6. Start module, 7. Aircraft engine;

[0036] 2-1, PLC controller, 2-2, sensor, 2-3, transmitter, 2-4, isolation module, 2-5, actuator;

[0037] 2-2-1, displacement sensor;

[0038] 4-1, fire button, 4-2, oil pump button, 4-3, pipeline solenoid valve button;

[0039] 5-1, fuel tank, 5-2, fuel pump, 5-3, fuel pipeline, 5-4, pipeline solenoid valve, 5-5, manual master valve, 5-6, fuel pressure transmitter, 5-7, throttle lever, 5-8, forward relay, 5-9, reverse relay, 5-10, throttle motor;

[0040] 6-1. Ignition relay, 6-2. Engine ignition accessories, 6-3. Hydraulic oil tank, 6-4. Hydraulic pump, 6-5. Hydraulic pipeline, 6-6. Hydraulic solenoid valve, 6-7. Hydraulic motor. DETAILED DESCRIPTION

[0041] The following describes the specific implementation of the utility model in conjunction with embodiments:

[0042] It should be noted that the structures, proportions, sizes, etc. shown in this specification are only used to match the contents disclosed in the specification so that people familiar with this technology can understand and read them, and are not used to limit the conditions under which the present invention can be implemented. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical content disclosed in the present invention without affecting the effects and purposes that can be achieved by the present invention.

[0043] Example 1

[0044] like Figure 1 As shown, the utility model discloses an electrical control system suitable for ground modification application of aircraft engines, including a power supply module 1, a control module 2, a human-machine interface 3, a control console 4, a throttle control module 5 and a starting module 6, wherein the power supply module 1 is respectively connected to the control module 2, the human-machine interface 3 and the starting module 6, the throttle control module 5 includes a fuel supply component and a throttle opening control component, the control module 2 is respectively electrically connected to the human-machine interface 3, the starting module 6, the fuel supply component and the throttle opening control component, the fuel supply component is connected to the aircraft engine 7, the throttle opening control component is connected to the fuel adjustment rocker arm of the aircraft engine 7, and the human-machine interface 3 is installed on the control console 4.

[0045] Example 2

[0046] like Figure 1 As shown, preferably, the power supply module 1 is composed of a main power system and a redundant power supply, the main power system is 24V, and the main power system and the redundant power supply are electrically connected to the control module 2, the human-machine interface 3 and the starting module 6 respectively.

[0047] The power supply module 1 includes a 24V main power supply and a redundant power supply, which can supply the entire system with power for dozens of hours of continuous operation. The redundant power supply is mainly used to supply the system with power for a period of time when the main power supply fails, so that the engine can still shut down normally when the main power supply fails, avoiding damage to the engine caused by direct shutdown in a large state.

[0048] The entire electronic control system has only one voltage level of DC 24V, which avoids the original multi-voltage level power supply of aircraft engines and makes the entire system simple and clear.

[0049] like Figure 2 As shown, preferably, the control module 2 includes a PLC controller 2-1, a sensor 2-2, a transmitter 2-3, an isolation module 2-4 and an actuator 2-5, the output ends of the sensor 2-2 and the transmitter 2-3 are respectively connected to the isolation module 2-4, the output end of the isolation module 2-4 is connected to the PLC controller 2-1, the output end of the PLC controller 2-1 is connected to the actuator 2-5, and the PLC controller 2-1 is electrically connected to the human-machine interface 3, the throttle control module 5 and the starting module 6.

[0050] The control module 2 is the core of the entire electrical control system. All signal reading, analysis, judgment and execution are completed by the control module, and the operation time of the PLC controller is in milliseconds, which can control the engine operation status in a timely and accurate manner.

[0051] The PLC controller 2-1 reads various parameter signals of the throttle control module 5, the starting module 6, and the aircraft engine 7 through the analog / switch input channel, obtains corresponding real-time parameters such as engine throttle opening, nozzle oil pressure, lubricating oil pressure, lubricating oil temperature, lubricating oil level, etc. through calculation and processing, and displays them on the human-machine interface.

[0052] Example 3

[0053] like Figure 5 As shown, preferably, the fuel supply assembly includes a fuel tank 5-1, a fuel pump 5-2, a fuel pipeline 5-3, a pipeline solenoid valve 5-4, a manual master valve 5-5 and a fuel pressure transmitter 5-6. The fuel tank 5-1 is connected to the fuel pump 5-2 through the fuel pipeline 5-3. A manual master valve 5-5 is provided on the fuel pipeline 5-3 between the fuel tank 5-1 and the fuel pump 5-2. The fuel pump 5-2 is connected to the aircraft engine 7 through the fuel pipeline 5-3. A pipeline solenoid valve 5-4 and a fuel pressure transmitter 5-6 are provided on the fuel pipeline 5-3 between the oil pump 5-2 and the aircraft engine 7. The pipeline solenoid valve 5-4 and the fuel pressure transmitter 5-6 are electrically connected to the PLC controller 2-1, respectively.

[0054] like Figure 6 As shown, preferably, the throttle opening control component includes a throttle lever 5-7, a forward relay 5-8, a reverse relay 5-9 and a throttle motor 5-10, the throttle lever 5-7 is installed on the console 4, the throttle lever 5-7 is connected to the isolation module 2-4, the isolation module 2-4 is connected to the PLC controller 2-1, the PLC controller 2-1 is electrically connected to the forward relay 5-8 and the reverse relay 5-9 respectively, the forward relay 5-8 and the reverse relay 5-9 respectively control the extension and retraction of the throttle motor 5-10, the throttle motor 5-10 is connected to the fuel adjustment rocker arm of the aircraft engine 7 to increase or decrease the throttle.

[0055] The throttle control module 5 includes two parts, a fuel supply component and a throttle opening control component. The fuel supply component includes a fuel tank 5-1, an oil pump 5-2, a fuel pipeline 5-3, a pipeline solenoid valve 5-4, a manual main valve 5-5 and a fuel pressure transmitter 5-6. During the startup process, the PLC controller 2-1 automatically starts the oil pump 5-2, opens the pipeline solenoid valve 5-4, and supplies fuel to the combustion chamber of the aircraft engine 7.

[0056] The throttle opening control component is controlled in two ways. One is a human-machine interface control. There are various state buttons of the engine throttle opening on the human-machine interface. When the corresponding button is clicked, the throttle motor 5-10 automatically pushes the fuel adjustment rocker arm of the aircraft engine 7 to the corresponding position. The other is a manual throttle joystick 5-7 installed on the operating table. When the throttle joystick 5-7 is pushed forward, the throttle of the aircraft engine 7 is increased. When the throttle joystick 5-7 is pulled back, the throttle of the aircraft engine 7 is reduced.

[0057] Example 4

[0058] like Figure 6 As shown, preferably, the sensor 2-2 includes a displacement sensor 2-2-1, a pressure sensor and a liquid level sensor; the displacement sensor 2-2-1 is fixed on the throttle motor 5-10, and the pull rope head of the displacement sensor 2-2-1 moves synchronously with the push rod head of the throttle motor 5-10; there are two pressure sensors, and the two pressure sensors are respectively installed in front of the fuel nozzle and after the lubricating oil filter of the aircraft engine 7; the liquid level sensor is installed on the fuel tank 5-1.

[0059] like Figure 7 , 8 As shown, preferably, the starting module 6 includes an ignition relay 6-1, an engine ignition accessory 6-2, a hydraulic oil tank 6-3, a hydraulic pump 6-4, a hydraulic pipeline 6-5, a hydraulic solenoid valve 6-6 and a hydraulic motor 6-7, the ignition relay 6-1 is respectively connected to the power supply module 1 and the PLC controller 2-1, the output end of the ignition relay 6-1 is connected to the engine ignition accessory 6-2, the engine ignition accessory 6-2 is connected to the ignition nozzle of the aircraft engine 7, the output end of the hydraulic oil tank 6-3 is connected to the hydraulic pump 6-4 through the hydraulic pipeline 6-5, the output end of the hydraulic pump 6-4 is connected to the hydraulic solenoid valve 6-6 through the hydraulic pipeline 6-5, the hydraulic solenoid valve 6-6 is respectively connected to the hydraulic motor 6-7 and the hydraulic oil tank 6-3, and the hydraulic motor 6-7 is connected to the high-pressure rotor of the aircraft engine 7.

[0060] The start module 6 is mainly used in the engine start process. After pressing the start button through the human-machine interface 3, the hydraulic pump 6-4 starts to rotate, and the high-pressure rotor of the aircraft engine 7 is driven to rotate through the hydraulic motor 6-7. At the same time, the PLC controller 2-1 controls the ignition of the ignition nozzle of the aircraft engine 7 through the ignition relay 6-1. When the aircraft engine 7 is ignited successfully and reaches a certain speed, the hydraulic pump 6-4 automatically stops working. The human-machine interface 3 will display the relevant data of the hydraulic system in real time, including hydraulic temperature, hydraulic torque, hydraulic speed, etc., for the operator to observe.

[0061] Example 5

[0062] like Figure 4As shown, preferably, the console 4 is installed with a human-machine interface touch screen 3, a fire button 4-1, an oil pump button 4-2, a pipeline solenoid valve button 4-3 and a throttle joystick 5-7, and the human-machine interface touch screen, the fire button 4-1, the oil pump button 4-2 and the pipeline solenoid valve button 4-3 are electrically connected to the PLC controller 2-1 respectively.

[0063] like Figure 3 As shown, preferably, the human-machine interface touch screen displays high-speed rotor speed, low-pressure rotor speed, exhaust temperature, fuel pressure, lubricating oil pressure, vibration, lubricating oil temperature, signal light, start mode and throttle position.

[0064] The console 4 is also provided with an emergency module. The human-machine interface 3 and the throttle joysticks 5-7 are all installed on the console 4. The human-machine interface 3 can display various parameters of the engine in real time. The operator can control and detect the engine on the console 4.

[0065] The operation of the aircraft engine 7 by the electronic control system of the utility model is all carried out in the human-machine interface 3. The screen is clear and concise, and the operation process is simple. It can be started and stopped with one button. When misoperation is handled in the program and a fault occurs, the PLC controller will automatically take countermeasures. It has a high degree of automation and a low degree of dependence on operators. General technicians can operate it after simple training.

[0066] The human-machine interface 3 is provided with a button that can control the throttle opening. Clicking the button controls the throttle to a predetermined position. Various sensors such as displacement sensors (fixed on the throttle motor, the sensor pull rope head moves synchronously with the motor push rod head), pressure sensors (one each before the fuel nozzle and after the lubricating oil filter), and liquid level sensors (installed on the fuel tank) enter the PLC controller 2-1 through the PLC controller input terminal, and display various parameters of the aircraft engine 7 on the industrial touch human-machine interface. Before the aircraft engine 7 is started, the PLC controller 2-1 automatically performs a self-check, and the self-check result is displayed on the human-machine interface. If it can be started, it will display "self-check completed, can be started"; if the self-check fails, it cannot be started, and it will display "self-check completed, cannot be started".

[0067] A start button is provided on the human-machine interface 3. After the self-test is completed and the engine can be started, click the start button and the internal program of the PLC controller 2-1 will control the aircraft engine 7 to start according to the predetermined start sequence. This program is an existing program and will not be described in detail in this application.

[0068] The human-machine interface 3 is connected to the PLC controller 2-1, which is used to control the actuator and display the engine parameters, and can detect various parameters of the engine. When the startup conditions are not met or a fault occurs during the operation of the engine, a warning box pops up. This human-machine interface adopts a mature and reliable industrial touch human-machine interface with a large interface size and high resolution, which can adapt to harsh industrial scenarios. Compared with traditional physical buttons, the design is more user-friendly, the interface is more convenient to change, the degree of customization is higher, and it is more convenient to detect and monitor the engine status and parameters, as well as to set engine parameters and control the engine's actuators.

[0069] During the starting process of aircraft engine 7, if a parameter failure occurs, such as excessive exhaust temperature, excessive engine vibration, or it is manually determined that the starting conditions are not met and the start must be terminated, the start termination button is pressed, and the start sequence will be immediately terminated, and the corresponding electromagnetic valve and throttle opening of aircraft engine 7 will return to the initial state.

[0070] After the aircraft engine 7 starts normally and enters the high state, when a parameter failure occurs, such as excessive exhaust temperature, low lubricating oil pressure, excessive vibration, etc., the PLC controller 2-1 immediately makes a judgment to pull the throttle to the slow or parking position to reduce the engine operating state to avoid expanding the impact and causing greater damage to the engine.

[0071] When an emergency occurs, such as fire or exhaust temperature exceeding the maximum limit, the operator can press the emergency stop button on the console 4. At this time, the PLC controller 2-1 will make a judgment and control the output at the same time, stop the machine and cut off the oil circuit until the engine stops.

[0072] The working principle of the utility model is as follows:

[0073] like Figures 1 to 8As shown, the utility model discloses an electrical control system suitable for ground modification of aircraft engines, including a power supply module 1, a control module 2, a human-machine interface 3, a control console 4, a throttle control module 5 and a starting module 6. The power supply module 1 supplies power to each module, the control module 2 is used to control the human-machine interface 3, the throttle control module 5 and the starting module 6, the human-machine interface 3 is installed on the control console 4, the throttle control module 5 includes a fuel supply component and a throttle opening control component, the fuel supply component is connected to the aircraft engine 7, the throttle opening control component is connected to the fuel adjustment rocker arm of the aircraft engine 7, and the throttle control of the throttle opening control component Rods 5-7 are also installed on the console 4. The fuel supply component and the throttle opening control component can be controlled by the human-machine interface 3. The throttle opening control component can also be controlled by the throttle joystick 5-7 alone. The components are electrically connected to start the aircraft engine. The connection of the components is simple, which reduces the difficulty of installation and processing. The fuel supply component is controlled by the PLC controller to supply fuel to the aircraft engine 7, the throttle opening control component is controlled to control the size of the throttle, the starting module 6 is controlled to start the high-pressure rotor of the aircraft engine 7 through the hydraulic motor 6-7, and the ignition nozzle of the aircraft engine 7 is controlled to ignite. The control efficiency is high and the degree of automation is high.

[0074] The utility model uses a PLC controller to replace the control mode of the starter box, which greatly simplifies the complex structure and reduces the failure rate; the electronic control mode can ensure accurate and rapid control, and the failure can be automatically detected in time; the throttle motor used has greatly reduced price, weight and power, and has higher energy economy; the hydraulic motor is used to replace the original air starter of the engine, which greatly reduces the size of the starter and reduces the cost; the reliable PLC controller is used, which is suitable for relatively harsh environments, such as industrial occasions with strong interference and complex control, and the operation time of the PLC is millisecond level. When an engine parameter failure is detected, the corresponding control adjustment can be made in a very short time, which has higher timeliness than manual mechanical throttle operation by personnel and is more conducive to ensuring engine safety.

[0075] The control system of the utility model can automatically detect the prohibition of starting, suspension of starting, major state faults, etc. through the PLC controller, detect various parameters of the aircraft engine before starting, during the starting process and under normal operating conditions, respond to fault information, and display various operating parameters and alarm information of the aircraft engine in real time on the human-machine interface.

[0076] The control system of the utility model has carried out a series of simplifications, so that the electrical control becomes easy to operate and realizes one-key control and over-control protection.

[0077] The preferred embodiments of the present invention are described in detail above, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of ordinary technicians in this field without departing from the purpose of the present invention.

[0078] Many other changes and modifications can be made without departing from the concept and scope of the utility model. It should be understood that the utility model is not limited to a specific embodiment, and the scope of the utility model is defined by the appended claims.

Claims

1. An electrical control system suitable for ground modification of aircraft engines, characterized in that: The invention comprises a power supply module (1), a control module (2), a human-machine interface (3), a control console (4), a throttle control module (5) and a starting module (6); the power supply module (1) is respectively connected to the control module (2), the human-machine interface (3) and the starting module (6); the throttle control module (5) comprises a fuel supply component and a throttle opening control component; the control module (2) is respectively electrically connected to the human-machine interface (3), the starting module (6), the fuel supply component and the throttle opening control component; the fuel supply component is connected to an aircraft engine (7); the throttle opening control component is connected to a fuel adjustment rocker arm of the aircraft engine (7); and the human-machine interface (3) is mounted on the control console (4).

2. An electrical control system suitable for ground modification of aircraft engines according to claim 1, characterized in that: The power supply module (1) is composed of a main power supply system and a redundant power supply. The main power supply system is 24V. The main power supply system and the redundant power supply are electrically connected to the control module (2), the human-machine interface (3) and the start-up module (6) respectively.

3. An electrical control system suitable for ground modification of aircraft engines according to claim 2, characterized in that: The control module (2) comprises a PLC controller (2-1), a sensor (2-2), a transmitter (2-3), an isolation module (2-4) and an actuator (2-5); the output ends of the sensor (2-2) and the transmitter (2-3) are respectively connected to the isolation module (2-4); the output end of the isolation module (2-4) is connected to the PLC controller (2-1); the output end of the PLC controller (2-1) is connected to the actuator (2-5); and the PLC controller (2-1) is respectively electrically connected to the human-machine interface (3), the throttle control module (5) and the starting module (6).

4. The electrical control system for ground modification of aircraft engines according to claim 3, characterized in that: The fuel supply assembly comprises a fuel tank (5-1), a fuel pump (5-2), a fuel pipeline (5-3), a pipeline solenoid valve (5-4), a manual master valve (5-5) and a fuel pressure transmitter (5-6); the fuel tank (5-1) is connected to the fuel pump (5-2) via the fuel pipeline (5-3); a manual master valve (5-5) is provided on the fuel pipeline (5-3) between the fuel tank (5-1) and the fuel pump (5-2); the fuel pump (5-2) is connected to the aircraft engine (7) via the fuel pipeline (5-3); a pipeline solenoid valve (5-4) and a fuel pressure transmitter (5-6) are provided on the fuel pipeline (5-3) between the fuel pump (5-2) and the aircraft engine (7); and the pipeline solenoid valve (5-4) and the fuel pressure transmitter (5-6) are respectively electrically connected to a PLC controller (2-1).

5. The electrical control system for ground modification of aircraft engines according to claim 4, characterized in that: The throttle opening control component comprises a throttle lever (5-7), a forward relay (5-8), a reverse relay (5-9) and a throttle motor (5-10). The throttle lever (5-7) is mounted on a control console (4). The throttle lever (5-7) is connected to an isolation module (2-4). The isolation module (2-4) is connected to a PLC controller (2-1). The PLC controller (2-1) is electrically connected to the forward relay (5-8) and the reverse relay (5-9) respectively. The forward relay (5-8) and the reverse relay (5-9) respectively control the extension and retraction of the throttle motor (5-10). The throttle motor (5-10) is connected to a fuel adjustment rocker arm of an aircraft engine (7) to increase or decrease the throttle.

6. An electrical control system suitable for ground modification of aircraft engines according to claim 5, characterized in that: The sensor (2-2) comprises a displacement sensor (2-2-1), a pressure sensor and a liquid level sensor; the displacement sensor (2-2-1) is fixed on the throttle motor (5-10), and the pull rope head of the displacement sensor (2-2-1) moves synchronously with the push rod head of the throttle motor (5-10); there are two pressure sensors, which are respectively installed in front of the fuel nozzle and after the lubricating oil filter of the aircraft engine (7); and the liquid level sensor is installed on the fuel tank (5-1).

7. The electrical control system for ground modification of aircraft engines according to claim 2, characterized in that: The starting module (6) comprises an ignition relay (6-1), an engine ignition accessory (6-2), a hydraulic oil tank (6-3), a hydraulic pump (6-4), a hydraulic pipeline (6-5), a hydraulic solenoid valve (6-6) and a hydraulic motor (6-7); the ignition relay (6-1) is respectively connected to the power supply module (1) and the PLC controller (2-1); the output end of the ignition relay (6-1) is connected to the engine ignition accessory (6-2); the engine ignition accessory (6-2) is connected to the ignition nozzle of the aircraft engine (7); the output end of the hydraulic oil tank (6-3) is connected to the hydraulic pump (6-4) through the hydraulic pipeline (6-5); the output end of the hydraulic pump (6-4) is connected to the hydraulic solenoid valve (6-6) through the hydraulic pipeline (6-5); the hydraulic solenoid valve (6-6) is respectively connected to the hydraulic motor (6-7) and the hydraulic oil tank (6-3); and the hydraulic motor (6-7) is connected to the high-pressure rotor of the aircraft engine (7).

8. The electrical control system for ground modification of aircraft engines according to claim 5, characterized in that: The control console (4) is equipped with a human-machine interface touch screen of a human-machine interface (3), a fire button (4-1), an oil pump button (4-2), a pipeline solenoid valve button (4-3) and a throttle joystick (5-7); the human-machine interface touch screen, the fire button (4-1), the oil pump button (4-2) and the pipeline solenoid valve button (4-3) are electrically connected to the PLC controller (2-1) respectively.

9. An electrical control system suitable for ground modification of aircraft engines according to claim 8, characterized in that: The human-machine interface touch screen displays high-speed rotor speed, low-pressure rotor speed, exhaust temperature, fuel pressure, lubricating oil pressure, vibration, lubricating oil temperature, signal light, start mode and throttle position.

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