System, method and equipment for controlling electronic throttle lever in full-automatic test run of aero-engine

Abstract

The invention relates to an aero-engine full-automatic test run electronic throttle lever control system, method and equipment, and relates to the field of aero-engines. According to the full-automatic test run scheme, the electronic handle box, the pump adjusting execution motor and the electric box are integrated, and full-process automatic control from program starting to data feedback is achieved. After the automatic button is pressed down, the main control module enters a full-automatic test run mode, actions of the handle driving motor and the pump adjusting execution motor are accurately adjusted and controlled through a PI loop, it is ensured that the handle driving motor and the pump adjusting execution motor synchronously run according to preset instructions, and the operation precision and efficiency are improved. In the process, the system not only can obtain and adjust the matching degree between the accelerator instruction and the handle position in real time, but also can synchronously monitor the oil needle position of the pump adjusting execution motor, so that the consistency and the stability of the test run process are ensured. Besides, the scheme supports automatic recording and backtracking of test run data, subsequent analysis and optimization are facilitated, digital management of test run is realized, and safety is guaranteed through a band-type brake locking mechanism when a fault occurs.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to a control system, method and equipment for a fully automatic test run electronic throttle lever of an aero-engine. Background Art

[0002] Engine testing is a key link in the development and production of aircraft engines. It not only determines whether the engine can achieve the designed performance indicators, but also directly affects the safety and reliability of the aircraft. The traditional method of manually operating the throttle lever to test has many limitations, which are specifically manifested in the following aspects: First, manual operation requires the collaboration of multiple personnel. For example, in a typical test run scenario, Person A issues specific throttle commands based on a predetermined test run map, while Person B actually operates the throttle lever to adjust the fuel supply based on these commands. This approach not only increases human resource costs, but also, because it involves communication and coordination between different positions, it is easy to cause misunderstandings or delays, which in turn affects the test run efficiency.

[0003] Secondly, for some operations that have strict requirements on the dynamic response of fuel regulation, such as rapid propulsion (fast push), different operators may have different execution results due to their respective experience differences. This reliance on individual skill levels makes it difficult to ensure data consistency for each test, thereby reducing the validity and repeatability of the test results. Especially in the development of modern high-performance aircraft engines, precise control of fuel flow has become particularly important, and any slight change may have a significant impact on the performance of the final product.

[0004] Furthermore, some important test data are still manually recorded on paper documents. This method is not only inefficient, but also very inconvenient for long-term storage and subsequent query. With the development of information technology, digital management has become one of the important means for all walks of life to improve management level and service quality. However, in the traditional engine test field, due to the lack of effective technical support, many valuable historical data have not been fully utilized, which has brought obstacles to future analysis and research.

[0005] In view of the above problems, in order to improve the degree of automation of test run work and the accuracy of test data, it is necessary to develop an electronic throttle control system and method that supports fully automatic test run function. Summary of the invention

[0006] The purpose of the present invention is to provide an aero-engine fully automatic test electronic throttle lever control system, method and equipment to solve the problems existing in the above-mentioned prior art.

[0007] To achieve the above object, the technical solution adopted by the present invention is: In a first aspect, the present invention provides an aero-engine fully automatic test run electronic throttle lever control system, the system comprising: An electronic handle box connected to the intelligent hub via a communication cable; an electrical box connected to the electronic handle box via an interconnecting cable; and A pump adjustment execution motor, which is connected to the electronic handle box via a resolver cable, and is connected to the electrical box via a motor cable; Among them, the electronic handle box receives the test throttle command from the intelligent center, drives the handle to the command position according to the test throttle command to adjust the fuel supply of the engine fuel pump, and sends the test data of the electronic handle box to the intelligent center to record data and trace back data.

[0008] In a possible implementation, the power output end of the pump regulation actuator motor is connected to the engine fuel pump through a connecting rod; when the pump regulation actuator motor is running, the opening of the engine fuel pump will change accordingly to control the fuel supply.

[0009] In a possible implementation, a first position sensor is further provided on the power output end of the pump adjustment actuator motor, and the first position sensor is connected to the electronic handle box to provide the electronic handle box with a position signal of the pump adjustment actuator motor.

[0010] In a possible implementation, the pump regulation actuator motor has a built-in brake, and the pump regulation actuator motor and the brake are connected to the electrical box.

[0011] In a possible implementation, the electrical box includes a pump adjustment driver, which is connected to the electronic handle box and is used to receive a control signal from the electronic handle box to the pump adjustment execution motor and a control signal of the brake; The pump regulation driver is also connected to the pump regulation execution motor and the brake, and is used to drive the pump regulation execution motor to operate, so as to achieve the pump regulation execution motor tracking control of the handle position of the electronic handle box, and at the same time, the pump regulation execution motor can be brake controlled in the event of a fault.

[0012] In a possible implementation, the electrical box further includes an air switch, a filter, a switch button, and a 24V switching power supply; Among them, the 220V mains power is connected to the 24V switching power supply after passing through the air switch, filter, and switch button. The 24V switching power supply is connected to the electronic handle box. The switch button is used to control the power on and off of the entire system.

[0013] In a possible implementation, the electronic handle box includes: A handle transmission assembly, comprising a handle sleeved on the handle spindle, a second position sensor and a spindle gear, wherein the handle drive motor is connected to the spindle gear through a transmission gear; A human-machine interaction module, which includes function buttons for realizing various functions, and a digital tube for displaying the oil needle position of the pump adjustment execution motor, the handle position of the electronic handle box, and a system fault code; A main control module, which is connected to the human-computer interaction module through an internal connector, and is used to obtain the level status of the function button from the human-computer interaction module and perform software function flow; it is connected to the first position sensor, and is used to obtain the oil needle position of the pump adjustment execution motor; it is connected to the second position sensor, and is used to obtain the handle position; and The driving module is connected to the main control module through an internal connector to obtain the handle position; it is connected to the intelligent center to obtain the test throttle command.

[0014] In a second aspect, the present invention provides a method for controlling an electronic throttle lever for fully automatic test of an aircraft engine. The method is applicable to any of the above-described electronic throttle lever control systems for fully automatic test of an aircraft engine, and the method comprises: S1. Press the automatic button of the human-machine interaction module in the electronic handle box, and the main control module in the electronic handle box enters the full-automatic test program; S2, receiving the test throttle command from the intelligent center through the driving module in the electronic handle box, and receiving the actual handle position from the main control module; the test throttle command is the control signal of the handle drive motor, and the handle position is the feedback signal of the handle drive motor, and the tracking control of the handle drive motor is realized through PI loop calculation; S3, at the same time as step S2, the oil needle position of the pump-adjusting actuator motor and the actual handle position are obtained through the main control module in the electronic handle box; the handle position is the control signal of the pump-adjusting actuator motor, and the oil needle position is the feedback signal of the pump-adjusting actuator motor. Through PI loop calculation, the main control module outputs the control signal to the pump-adjusting driver in the electrical box to realize tracking control of the pump-adjusting actuator motor; S4, driving the pump adjustment execution motor through the pump adjustment driver in the electrical box to operate according to the test throttle command of the intelligent center to realize test automation; S5, sending the test data to the intelligent center through the driving module in the electronic handle box for data recording and backtracking to realize the digitalization of the test; S6. The oil needle position and handle position of the pump-adjusting actuator motor are displayed in real time through the human-machine interaction module in the electronic handle box; when a system failure occurs, the electronic handle box outputs a brake control signal to the electrical box, and the electrical box performs brake control through the pump-adjusting driver, and displays the system fault code on the human-machine interaction module.

[0015] In a third aspect, the present invention provides a computer device, comprising a processor and a memory, wherein the memory stores at least one instruction, at least one program, a code set or an instruction set, and the processor can load and execute at least one instruction, at least one program, a code set or an instruction set to implement the electronic throttle lever control method for fully automatic test of an aircraft engine as provided above.

[0016] In a fourth aspect, the present invention provides a computer-readable storage medium, in which at least one instruction, at least one program, code set or instruction set is stored. A processor can load and execute at least one instruction, at least one program, code set or instruction set to implement the electronic throttle lever control method for fully automatic test of an aircraft engine as provided above.

[0017] In a fifth aspect, the present invention provides a computer program product or a computer program, the computer program product or the computer program comprising computer program instructions, the computer program instructions being stored in a computer-readable storage medium. A processor reads the computer instructions from the computer-readable storage medium and executes the computer instructions, so that the computer device executes the method for controlling the electronic throttle lever of the fully automatic test run of an aircraft engine as provided above.

[0018] The beneficial effects brought about by the technical solution provided by the present invention include at least: The fully automatic test run solution integrates the electronic handle box, pump adjustment execution motor and electrical box to realize the full process automation control from the start-up procedure to data feedback. After pressing the automatic button, the main control module enters the fully automatic test run mode, and uses the PI loop to accurately control the action of the handle drive motor and the pump adjustment execution motor to ensure that the two run synchronously according to the preset instructions, thereby improving the operation accuracy and efficiency. During this process, the system can not only obtain and adjust the matching degree between the throttle command and the handle position in real time, but also synchronously monitor the oil needle position of the pump adjustment execution motor to ensure the consistency and stability of the test run process. In addition, the solution supports the automatic recording and backtracking of test run data, which is convenient for subsequent analysis and optimization, and realizes the digital management of test runs. More importantly, when encountering a fault, the system can respond quickly, ensure safety through the brake locking mechanism, and immediately display the fault information on the human-computer interaction module to help quickly diagnose the problem, thereby improving the reliability of the system and user experience. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings are used to provide further understanding of the present invention and constitute a part of the specification. They are used to explain the present invention together with the embodiments of the present invention and do not constitute a limitation of the present invention.

[0020] Figure 1 A structural block diagram of an electronic throttle lever control system for fully automatic test running of an aircraft engine provided by an exemplary embodiment of the present invention is shown.

[0021] Figure 2 A schematic diagram of the structure of a pump adjustment actuator motor of an electronic throttle lever control system for fully automatic test running of an aircraft engine provided by an exemplary embodiment of the present invention is shown.

[0022] Figure 3 A schematic structural diagram of an electrical box of an aero-engine fully automatic test electronic throttle lever control system provided by an exemplary embodiment of the present invention is shown.

[0023] Figure 4 A schematic structural diagram of an electronic handle box of an electronic throttle lever control system for fully automatic test running of an aircraft engine provided by an exemplary embodiment of the present invention is shown.

[0024] Figure 5 A schematic structural diagram of a human-machine interaction module of an electronic handle box of an electronic throttle lever control system for fully automatic test running of an aircraft engine provided by an exemplary embodiment of the present invention is shown.

[0025] Figure 6 A flow chart of an electronic throttle lever control method for fully automatic test run of an aircraft engine provided by an exemplary embodiment of the present invention is shown.

[0026] Figure 7 A schematic diagram of the structure of a computer device for executing an electronic throttle lever control method for fully automatic test run of an aircraft engine provided by an exemplary embodiment of the present invention is shown. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0029] Figure 1A structural block diagram of an aircraft engine fully automatic test electronic throttle lever control system provided by an exemplary embodiment of the present invention is shown, and the aircraft engine fully automatic test electronic throttle lever control system includes: an electronic handle box 2, an electrical box 3, and a pump adjustment execution motor 4, the electronic handle box 2 is connected to the intelligent center 1 through a communication cable; the electrical box 3 is connected to the electronic handle box 2 through an interconnecting cable; the pump adjustment execution motor 4 is connected to the electronic handle box 2 through a rotary transformer cable, and is connected to the electrical box 3 through a motor cable; wherein the electronic handle box 2 receives a test throttle command from the intelligent center 1, drives the handle to the command position according to the test throttle command to adjust the fuel supply of the engine fuel pump, and sends the test data of the electronic handle box 2 to the intelligent center 1 to record data and trace back data.

[0030] In detail, Figure 2 The schematic diagram of the structure of a pump-adjusting actuator motor of an aero-engine fully automatic test electronic throttle lever control system provided by an exemplary embodiment of the present invention is shown. The power output end of the pump-adjusting actuator motor 4 is connected to the engine fuel pump through a connecting rod 41; when the pump-adjusting actuator motor 4 is running, the opening of the engine fuel pump will change accordingly to control the fuel supply. A first position sensor 42 is also provided on the power output end of the pump-adjusting actuator motor 4, and the first position sensor 42 is connected to the electronic handle box 2, and is used to provide the electronic handle box 2 with a position signal of the pump-adjusting actuator motor 4. The pump-adjusting actuator motor 4 is equipped with a brake, and the pump-adjusting actuator motor 4 and the brake are connected to the electrical box 3.

[0031] In the embodiment of the present application, the pump adjustment execution motor 4 is directly connected to the engine fuel pump through the connecting rod 41, so as to realize the precise control of the fuel pump opening, so as to dynamically adjust the fuel supply to adapt to different test requirements and working conditions. This direct drive mode not only improves the response speed of the system, but also reduces the error that may be introduced by the intermediate transmission link, and ensures the accuracy and consistency of the fuel supply. In order to ensure the closed-loop control performance of the system, the power output end of the pump adjustment execution motor 4 is equipped with a first position sensor 42, which monitors and feeds back the position information of the motor to the electronic handle box 2 in real time. These position signals are essential for maintaining the precise control of the fuel pump opening, because they enable the electronic handle box 2 to adjust the control instructions in time according to the actual fuel pump state to ensure that the fuel flow meets the expected setting. This not only improves the consistency and repeatability of the test process, but also provides a reliable basis for subsequent data analysis. In addition, the built-in brake design of the pump adjustment execution motor 4 further enhances the safety and reliability of the system. The brake can quickly lock the motor shaft in the event of power failure or emergency, prevent unexpected movement caused by inertia or other external forces, and protect the safety of equipment and personnel. At the same time, when a set point needs to be maintained for a long time, the brake can help fix the motor position, reduce the motor load and extend its service life. The connection between the brake and the electrical box 3 ensures that the control system can activate the brake function in a timely manner as needed, thereby enhancing the automation level and safety of the system.

[0032] Specifically, Figure 3 The schematic diagram of the structure of the electrical box of an aero-engine fully automatic test electronic throttle lever control system provided by an exemplary embodiment of the present invention is shown. The electrical box 3 includes a pump adjustment driver 31, which is connected to the electronic handle box 2 and is used to receive the control signal of the electronic handle box 2 to the pump adjustment execution motor 4 and the control signal of the brake; the pump adjustment driver 31 is also connected to the pump adjustment execution motor 4 and the brake, and is used to drive the pump adjustment execution motor 4 to operate, so as to realize the pump adjustment execution motor 4 tracking control of the handle position of the electronic handle box 2, and at the same time, the pump adjustment execution motor 4 can be brake controlled in case of a fault. The electrical box 3 also includes an air switch 32, a filter 33, a switch button 34, and a 24V switch power supply 35; wherein, the 220V mains power is connected to the 24V switch power supply 35 after passing through the air switch 32, the filter 33, and the switch button 34, and the 24V switch power supply 35 is connected to the electronic handle box 2, and the switch button 34 is used to control the power on and off of the entire system.

[0033] In the embodiment of the present application, the electrical box 3 contains a pump adjustment driver 31, which serves as a key bridge connecting the electronic handle box 2 and the pump adjustment execution motor 4, and is responsible for receiving control signals from the electronic handle box 2, including operating instructions for the pump adjustment execution motor 4 and its built-in brake. Through these signals, the pump adjustment driver 31 can effectively drive the pump adjustment execution motor 4 to operate, ensuring that it accurately tracks the handle position set by the electronic handle box 2. The design of this closed-loop control system allows the fuel pump opening to be dynamically adjusted according to actual needs, ensuring the consistency and stability of the engine performance during the test run. In addition, the 24V DC power supply provided by the 24V switching power supply supplies power to low-voltage equipment such as the electronic handle box 2, ensuring that all subsystems can obtain continuous and pure power supply. The switch button 34 is not only used to control the power on and off of the system, but also provides the ability to quickly cut off the power in an emergency, increasing the safety of operation.

[0034] Further, Figure 4 A schematic diagram of the structure of an electronic handle box of an aero-engine fully automatic test electronic throttle lever control system provided by an exemplary embodiment of the present invention is shown. Figure 5 The structure diagram of the human-machine interaction module of an electronic handle box of an aircraft engine full-automatic test electronic throttle control system provided by an exemplary embodiment of the present invention is shown. The electronic handle box 2 includes: a handle transmission assembly 21, a handle drive motor 22, a human-machine interaction module 23, a main control module 24, and a drive module 25. The handle transmission assembly 21 includes a handle sleeved on the handle main shaft, a second position sensor and a main shaft gear. The handle drive motor 22 is connected to the main shaft gear through a transmission gear; the human-machine interaction module 23 includes a function button 231 for realizing various functions, and a function button 232 for displaying the oil level of the pump adjustment execution motor 4. The main control module 24 is connected to the human-computer interaction module 23 through an internal connector, and is used to obtain the level status of the function button 211 from the human-computer interaction module 21 and perform software function flow; the main control module 24 is connected to the first position sensor 42, and is used to obtain the oil needle position of the pump adjustment execution motor 4; the main control module 24 is connected to the second position sensor, and is used to obtain the handle position; the drive module 25 is connected to the main control module 24 through an internal connector, and is used to obtain the handle position; the drive module 25 is connected to the intelligent hub 1, and is used to obtain the test throttle command.

[0035] In the embodiment of the present application, the function button 231 of the human-computer interaction module 23 can realize the calibration function of the electronic throttle lever system, the electronic brake and drive control function of the pump adjustment execution motor, and the automatic test run function; the human-computer interaction module 23 also includes a status indicator light for feedback on the current system operation status; the main control module 24 controls the human-computer interaction module status indicator light and the display area of ​​the digital tube 232 through the SPI interface.

[0036] In the embodiment of the present application, the handle, the second position sensor and the main shaft gear in the handle transmission assembly 21 work together to ensure the accuracy and stability of the handle movement; and the handle drive motor 22 is connected to the main shaft gear through the transmission gear, and can accurately adjust the handle position according to the instructions issued by the main control module 24; this design ensures that even in a complex test environment, the fuel pump opening can be highly accurately controlled, thereby maintaining stable engine performance. The drive module 25 plays the role of a bridge. It is not only connected to the main control module 24 through an internal connector to obtain handle position information, but also directly communicates with the intelligent hub 1 to receive test throttle instructions; such a setting ensures that all operations are completed under the unified dispatch of the intelligent hub 1, realizing global coordinated control and further enhancing the stability and controllability of the system.

[0037] In one example, the driving module 25 uses TMS320F2812 as its core digital signal processor (DSP) and DRV8711 as the motor driving chip. The main control module 24 uses the TMS320F2812 digital signal processor (DSP) of Texas Instruments (TI).

[0038] Figure 6 A flowchart of an aircraft engine full-automatic test electronic throttle lever control method provided by an exemplary embodiment of the present invention is shown. The aircraft engine full-automatic test electronic throttle lever control method is applicable to the aircraft engine full-automatic test electronic throttle lever control system as described above. The method comprises the following steps: Step S1, press the automatic button of the human-machine interaction module in the electronic handle box, and the main control module in the electronic handle box enters the full-automatic test program.

[0039] In the embodiment of the present application, the operator presses the automatic button on the human-machine interaction module in the electronic handle box. This action marks the official start of the test run process. After the main control module receives the button trigger signal, it will start the preset initialization process, check whether the status of each part of the system is normal, and enter the fully automatic test run program. At this time, the main control module will perform a series of self-test operations to ensure that all connected sensors and actuators are in good condition and prepare for the subsequent precise control.

[0040] Step S2: Receive the test throttle command from the intelligent center through the drive module in the electronic handle box, and receive the actual handle position from the main control module; the test throttle command is the control signal of the handle drive motor, and the handle position is the feedback signal of the handle drive motor. Through PI loop calculation, tracking control of the handle drive motor is realized.

[0041] In the embodiment of the present application, step S2 involves the exchange of information between the intelligent center and the electronic handle box. First, the drive module in the electronic handle box receives the test throttle command from the intelligent center, which serves as a control signal for the handle drive motor and indicates the expected handle position. At the same time, the main control module continuously monitors the actual handle position, which is a feedback signal provided by the second position sensor. By comparing these two signals, the expected value and the actual value, the main control module uses the PI (proportional-integral) controller algorithm to adjust the action of the handle drive motor so that the actual position of the handle can closely follow the set target position. This closed-loop control system ensures that the handle position can maintain a high degree of consistency and accuracy even in the face of external interference or internal parameter changes.

[0042] Step S3, at the same time as step S2, obtain the oil needle position of the pump-adjusting actuator motor and the actual handle position through the main control module in the electronic handle box; the handle position is the control signal of the pump-adjusting actuator motor, and the oil needle position is the feedback signal of the pump-adjusting actuator motor. Through PI loop calculation, the main control module outputs the control signal to the pump-adjusting driver in the electrical box to realize tracking control of the pump-adjusting actuator motor.

[0043] In the embodiment of the present application, when step S2 is in progress, the main control module simultaneously obtains the oil needle position of the pump adjustment actuator motor and the actual handle position from the first position sensor. Here, the handle position again plays the role of the control signal, and the oil needle position is used as a feedback signal to verify the working state of the pump adjustment actuator motor. Similarly, the main control module adopts the PI loop calculation method to adjust the control signal output to the pump adjustment driver in the electrical box according to the difference between the two, to ensure that the pump adjustment actuator motor can operate in the expected manner and maintain the consistency of the fuel supply.

[0044] Step S4, the pump adjustment driver in the electrical box drives the pump adjustment execution motor to operate according to the test throttle command of the intelligent center to realize test automation.

[0045] In the embodiment of the present application, based on the data flow and control logic established in the previous steps, the pump adjustment driver in the electrical box drives the pump adjustment execution motor according to the control signal sent by the main control module, so that it can operate accurately according to the test throttle command issued by the intelligent center. In this process, the pump adjustment execution motor is responsible for adjusting the opening of the fuel pump to meet the needs of the test run at different stages, thereby realizing a high degree of automation of the entire test run process.

[0046] Step S5: Send the test data to the intelligent center through the drive module in the electronic handle box for data recording and backtracking to realize the digitization of the test.

[0047] In the embodiment of the present application, the driver module in the electronic handle box is not only responsible for receiving commands from the intelligent center, but also bears the task of transmitting various data generated during the test run to the intelligent center. These data include but are not limited to the handle position, oil needle position and other key performance indicators, which are recorded for future reference or further analysis, which helps to evaluate the performance of the engine and optimize future test run plans.

[0048] Step S6, display the oil needle position and handle position of the pump adjustment actuator motor in real time through the human-machine interaction module in the electronic handle box; when a system failure occurs, the electronic handle box outputs the brake control signal to the electrical box, and the electrical box executes the brake control through the pump adjustment driver and displays the system fault code on the human-machine interaction module.

[0049] In the embodiment of the present application, the digital tube on the human-machine interaction module updates and displays the oil needle position and handle position of the pump-adjusting actuator motor in real time, so that the operator can intuitively understand the current operating status of the system. More importantly, if the system detects any abnormality, the electronic handle box will immediately send a brake control signal to the electrical box, prompting the pump-adjusting driver to activate the brake function to prevent potential safety risks. At the same time, the fault code will also appear on the human-machine interaction module to help technicians quickly diagnose the problem.

[0050] In summary, the above six steps constitute a complete workflow of the electronic throttle lever control system for fully automatic test of aircraft engines. From initial settings to final data recording, and then to necessary safety measures, each link is to ensure the safety, efficiency and accuracy of the test process. This is not only a major improvement on the traditional test method, but also provides strong technical support for the future research and development of aircraft engines.

[0051] Figure 7 A schematic diagram of the structure of a computer device for executing an electronic throttle lever control method for fully automatic test of an aircraft engine provided by an exemplary embodiment of the present invention is shown, and the computer device includes: The processor 701 includes one or more processing cores. The processor 701 executes various functional applications and data processing by running software programs and modules.

[0052] The receiver 702 and the transmitter 703 can be implemented as a communication component, and the communication component can be a communication chip. Optionally, the communication component can be implemented to include a signal transmission function. That is, the transmitter 703 can be used to transmit a control signal to the image acquisition device and the scanning device, and the receiver 702 can be used to receive the corresponding feedback instruction.

[0053] The memory 704 is connected to the processor 701 via a bus 705 .

[0054] The memory 704 may be used to store at least one instruction, and the processor 701 may be used to execute the at least one instruction to implement each step in the above method embodiment.

[0055] An embodiment of the present invention also provides a computer-readable storage medium, which stores at least one instruction, at least one program, code set or instruction set, which is loaded and executed by a processor to implement the above-mentioned aircraft engine fully automatic test electronic throttle lever control method.

[0056] The present invention also provides a computer program product or a computer program, which includes a computer instruction stored in a computer-readable storage medium. A processor of a computer device reads the computer instruction from the computer-readable storage medium, and the processor executes the computer instruction, so that the computer device executes the method for controlling the electronic throttle lever of the fully automatic test run of an aircraft engine described in any of the above embodiments.

[0057] Optionally, the computer readable storage medium may include: a read-only memory (ROM), a random access memory (RAM), a solid state drive (SSD), or an optical disk. Among them, the random access memory may include a resistance random access memory (ReRAM) and a dynamic random access memory (DRAM). The serial numbers of the above embodiments of the present invention are only for description and do not represent the advantages and disadvantages of the embodiments.

[0058] It should be understood that the specific examples herein are only intended to help those skilled in the art to better understand the present disclosure, rather than to limit the scope of the present invention.

[0059] It is understood that in the various implementations of this specification, the size of the sequence number of each process does not mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the present disclosure.

[0060] It can be understood that the various implementation modes described in this specification can be implemented individually or in combination, and the present disclosure is not limited to this.

[0061] Unless otherwise stated, all technical and scientific terms used in this disclosure have the same meaning as those generally understood by those skilled in the art of the technical field of this specification. The terms used in this specification are only for the purpose of describing specific embodiments and are not intended to limit the scope of this specification. The term "and / or" used in this specification includes any and all combinations of one or more related listed items. The singular forms of "a", "above", and "the" used in this disclosure and the appended claims are also intended to include plural forms, unless the context clearly indicates other meanings.

[0062] It can be understood that the processor of the present disclosure can be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method implementation method can be completed by the hardware integrated logic circuit or software instructions in the processor. The above processor can be a general processor, a digital signal processor (DigitalSignalProcessor, DSP), an application-specific integrated circuit (Application Specific Integrated Circuit, ASIC), a field programmable gate array (Field Programmable Gate Array, FPGA) or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. The methods, steps and logic block diagrams disclosed in the present disclosure can be implemented or executed. The general processor can be a microprocessor or the processor can also be any conventional processor, etc. The steps of the method disclosed in the present disclosure can be directly embodied as a hardware decoding processor to perform, or the hardware and software modules in the decoding processor can be combined to perform. The software module can be located in a mature storage medium in the field such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory or an electrically erasable programmable memory, a register, etc. The storage medium is located in the memory, and the processor reads the information in the memory and completes the steps of the above method in combination with its hardware.

[0063] It is understood that the memory in the present disclosure may be a volatile memory or a non-volatile memory, or may include both volatile and non-volatile memory. Among them, the non-volatile memory may be a read-only memory (ROM), a programmable read-only memory (programmable ROM, PROM), an erasable programmable read-only memory (erasable PROM, EPROM), an electrically erasable programmable read-only memory (EEPROM) or a flash memory. The volatile memory may be a random access memory (RAM). It should be noted that the memory of the systems and methods described herein is intended to include, but is not limited to, these and any other suitable types of memory.

[0064] Those skilled in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this specification.

[0065] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working processes of the systems, devices and units described above can refer to the corresponding processes in the aforementioned method implementation methods and will not be repeated here.

[0066] In the several embodiments provided in this specification, it should be understood that the disclosed systems, devices and methods can be implemented in other ways. For example, the device implementation described above is only schematic. For example, the division of the units is only a logical function division. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of devices or units, which can be electrical, mechanical or other forms.

[0067] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the present embodiment.

[0068] In addition, each functional unit in each embodiment of the present specification may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.

[0069] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this specification, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium, including several instructions for a computer device (which can be a personal computer, server, or network device, etc.) to perform all or part of the steps of the method described in each embodiment of this specification. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM), random access memory (RAM), disk or optical disk, etc., various media that can store program codes.

[0070] The above is only a specific implementation of this specification, but the protection scope of the present invention is not limited thereto. Any person skilled in the art who is familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in this specification, which should be included in the protection scope of this specification. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. An electronic throttle lever control system for fully automatic test of an aircraft engine, characterized in that: The system comprises: An electronic handle box (2) connected to the intelligent hub (1) via a communication cable; an electrical box (3) connected to the electronic handle box (2) via an interconnecting cable; and A pump adjustment execution motor (4), which is connected to the electronic handle box (2) via a resolver cable, and is connected to the electrical box (3) via a motor cable; The electronic handle box (2) receives a test throttle command from the intelligent center (1), drives the handle to reach a command position according to the test throttle command to adjust the fuel supply of the engine fuel pump, and sends the test data of the electronic handle box (2) to the intelligent center (1) to record and trace the data.

2. The aircraft engine fully automatic test electronic throttle lever control system according to claim 1, characterized in that: The power output end of the pump regulation execution motor (4) is connected to the engine fuel pump via a connecting rod (41); when the pump regulation execution motor (4) is running, the opening degree of the engine fuel pump will change accordingly to control the fuel supply amount.

3. The aircraft engine fully automatic test run electronic throttle lever control system according to claim 2, characterized in that: A first position sensor (42) is also provided on the power output end of the pump adjustment actuator motor (4), and the first position sensor (42) is connected to the electronic handle box (2) and is used to provide the electronic handle box (2) with a position signal of the pump adjustment actuator motor (4).

4. The aircraft engine fully automatic test run electronic throttle lever control system according to claim 2, characterized in that: The pump regulation execution motor (4) has a built-in brake, and the pump regulation execution motor (4) and the brake are connected to the electrical box (3).

5. The aircraft engine fully automatic test run electronic throttle lever control system according to claim 4, characterized in that: The electrical box (3) comprises a pump adjustment driver (31), the pump adjustment driver (31) being connected to the electronic handle box (2) and being used for receiving control signals from the electronic handle box (2) for the pump adjustment execution motor (4) and the brake control signal; The pump adjustment driver (31) is also connected to the pump adjustment execution motor (4) and the brake, and is used to drive the pump adjustment execution motor (4) to operate, so as to achieve tracking control of the handle position of the electronic handle box (2) by the pump adjustment execution motor (4), and at the same time, can perform brake control on the pump adjustment execution motor (4) when a fault occurs.

6. The aircraft engine fully automatic test run electronic throttle lever control system according to claim 5, characterized in that: The electrical box (3) further comprises an air switch (32), a filter (33), a switch button (34), and a 24V switching power supply (35); The 220V mains electricity is connected to the 24V switch power supply (35) via the air switch (32), the filter (33), and the switch button (34); the 24V switch power supply (35) is connected to the electronic handle box (2); and the switch button (34) is used to control power on and power off of the entire system.

7. The aircraft engine fully automatic test run electronic throttle lever control system according to claim 3, characterized in that: The electronic handle box (2) comprises: A handle transmission assembly (21), comprising a handle sleeved on a handle main shaft, a second position sensor and a main shaft gear, wherein a handle drive motor (22) is connected to the main shaft gear through a transmission gear; A human-machine interaction module (23), comprising function buttons (231) for realizing various functions, and a digital tube (232) for displaying the oil needle position of the pump adjustment execution motor (4), the handle position of the electronic handle box (2), and a system fault code; a main control module (24), which is connected to the human-machine interaction module (23) via an internal connector, and is used to obtain the level state of the function button (211) from the human-machine interaction module (21) and perform software function flow; it is connected to the first position sensor (42) and is used to obtain the oil needle position of the pump adjustment execution motor (4); it is connected to the second position sensor and is used to obtain the handle position; and A drive module (25) is connected to the main control module (24) via an internal connector and is used to obtain the handle position; it is connected to the intelligent center (1) and is used to obtain a test throttle command.

8. A method for controlling an electronic throttle lever for fully automatic test of an aircraft engine, the method being applicable to the electronic throttle lever control system for fully automatic test of an aircraft engine according to any one of claims 1 to 7, characterized in that: The method comprises: S1. Press the automatic button of the human-machine interaction module in the electronic handle box, and the main control module in the electronic handle box enters the full-automatic test program; S2, receiving the test throttle command from the intelligent center through the driving module in the electronic handle box, and receiving the actual handle position from the main control module; the test throttle command is the control signal of the handle drive motor, and the handle position is the feedback signal of the handle drive motor, and the tracking control of the handle drive motor is realized through PI loop calculation; S3, at the same time as step S2, the oil needle position of the pump-adjusting actuator motor and the actual handle position are obtained through the main control module in the electronic handle box; the handle position is the control signal of the pump-adjusting actuator motor, and the oil needle position is the feedback signal of the pump-adjusting actuator motor. Through PI loop calculation, the main control module outputs the control signal to the pump-adjusting driver in the electrical box to realize tracking control of the pump-adjusting actuator motor; S4, driving the pump adjustment execution motor through the pump adjustment driver in the electrical box to operate according to the test throttle command of the intelligent center to realize test automation; S5, sending the test data to the intelligent center through the driving module in the electronic handle box for data recording and backtracking to realize the digitalization of the test; S6. The oil needle position and handle position of the pump-adjusting actuator motor are displayed in real time through the human-machine interaction module in the electronic handle box; when a system failure occurs, the electronic handle box outputs a brake control signal to the electrical box, and the electrical box performs brake control through the pump-adjusting driver, and displays the system fault code on the human-machine interaction module.

9. A computer device, characterized in that: The computer device includes a processor and a memory, wherein the memory stores at least one instruction, at least one program, code set or instruction set, and the at least one instruction, at least one program, code set or instruction set is loaded and executed by the processor to implement the aircraft engine fully automatic test electronic throttle lever control method as described in claim 8.

10. A computer-readable storage medium, characterized in that: The readable storage medium stores at least one instruction, at least one program, code set or instruction set, and the at least one instruction, at least one program, code set or instruction set is loaded and executed by the processor to implement the aircraft engine fully automatic test electronic throttle lever control method as described in claim 8.

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