Digital control system and method for air intake and exhaust air door of aero-engine ground test

Abstract

The invention relates to the technical field of aero-engine tests, and discloses an aero-engine ground test intake and exhaust air door digital control system and method, and the system comprises an operation panel which is used for transmitting an opening or closing instruction of an intake and exhaust air door to an intake and exhaust air door digital simulator; an input interface of the intake and exhaust air door digital simulator receives an instruction and a feedback signal of the aero-engine controller; the simulator CPU analyzes the instruction and controls the timer to generate a delay signal; the output interface outputs a control signal to an aero-engine controller; a controller CPU of the aero-engine controller analyzes the signal and generates a feedback signal; the signal output module returns a feedback signal to an input interface of the simulator to form closed-loop control; the upper computer displays the simulation state and the operation state of the intake and exhaust air door in real time, and judges whether to pass or display fault information according to a feedback result of the controller CPU, so that efficient and accurate simulation control under the condition of no actual air door device is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine testing, and in particular to a digital control system and method for intake and exhaust dampers in aero-engine ground testing. Background Art

[0002] As core components of an aircraft's aerodynamic system, intake and exhaust dampers are primarily responsible for precisely regulating the flow and pressure of the engine's intake and exhaust air, making them a key component in ensuring the stable operation of aircraft engines. In actual flight, the control signals for the intake and exhaust dampers are directly issued by the aircraft engine controller and drive the actuators to dynamically adjust the damper openings. However, in aircraft engine ground test scenarios, actual intake and exhaust damper devices are often not installed in order to focus on evaluating engine performance. While this approach simplifies the test process, it also presents a technical challenge that urgently needs to be addressed: how to simulate the actual movement of the dampers and accurately transmit the corresponding feedback signals to the engine controller.

[0003] Currently, common solutions can be divided into two categories: one is to use the fault signal shielding method, which manually cuts off or shields the fault alarm signal related to the damper to circumvent the problem caused by the missing damper. Although this solution is easy to operate, it conceals the abnormal conditions that may occur in actual operation and cannot truly reflect the actual state of the engine and damper when working together, which greatly reduces the reliability of the test results. The other is to use physical simulation, that is, to install a real damper device for testing in ground tests. Although this method can provide more accurate test data, the installation, debugging and disassembly process of the actual damper is extremely complicated, which is not only time-consuming and labor-intensive, but also has problems such as mechanical wear and frequent failures during operation, which greatly reduces the test efficiency. At the same time, it also increases the test cost and uncertainty, making it difficult to meet the needs of rapid iteration and efficient testing of modern aircraft engines. Summary of the Invention

[0004] In view of this, in order to solve the problem of efficient and accurate simulation control in the absence of actual damper devices, an embodiment of the present invention proposes a digital control system and method for the intake and exhaust dampers of aircraft engine ground tests. Without the need for actual damper hardware, all functions of the intake and exhaust dampers are effectively simulated through high-precision digital control, fully meeting the strict requirements of ground tests.

[0005] In a first aspect, the present invention provides a digital control system for intake and exhaust dampers of an aircraft engine ground test, comprising:

[0006] Operation panel, intake and exhaust damper digital simulator, aircraft engine controller and host computer, including:

[0007] An operation panel, used for sending an opening or closing instruction of the intake and exhaust dampers to the intake and exhaust damper digital simulator;

[0008] The digital simulator for intake and exhaust dampers includes an input interface, a simulator CPU, a timer, and an output interface; the input interface is used to receive instructions from an operation panel and feedback signals from an aircraft engine controller; the simulator CPU is used to perform logical processing on the instructions and control the timer to generate a delay signal; and the output interface is used to output the control signal processed by the simulator CPU to the aircraft engine controller.

[0009] An aircraft engine controller includes a signal input module, a controller CPU, and a signal output module; the signal input module is used to receive control signals from a digital simulator for intake and exhaust dampers; the controller CPU is used to analyze the signals and generate feedback signals; and the signal output module returns the feedback signals to the input interface of the digital simulator for intake and exhaust dampers, thereby forming a closed-loop control system.

[0010] The host computer is used to display the simulation status and operation status of the intake and exhaust dampers in real time, and judge whether it passes or displays fault information based on the feedback results from the controller CPU.

[0011] The digital control system for intake and exhaust dampers in ground tests of aircraft engines provided by the embodiment of the present invention combines the closed-loop control design of the intake and exhaust damper digital simulator with the aircraft engine controller. Through precise logic processing and delayed signal simulation, it can realistically reproduce the dynamic response of the actual damper under different working conditions, ensuring that the test data can truly reflect the state of the engine and the damper working together, providing a reliable basis for engine performance evaluation. The real-time monitoring and fault information display function of the upper computer can quickly capture system anomalies during the test, helping technicians to locate the fault point in time, and combining the detailed data of the closed-loop control feedback to achieve accurate fault diagnosis, which is convenient for subsequent system optimization and maintenance. This method does not require the installation, debugging and disassembly of the actual damper, effectively avoiding the time consumption and potential failure risks caused by the complex process and uncertainty in the physical test, greatly shortening the test cycle, reducing the test cost, and meeting the urgent need for efficient testing in the rapid iterative research and development of aircraft engines.

[0012] In an optional implementation, the input interface, output interface, input module, and output module each include multiple ports, which respectively input or output different command signals.

[0013] The embodiment of the present invention receives or sends different types of instructions through independent ports. Each port focuses on a specific function, which can ensure that each signal remains independent during the transmission process, reduce signal interference, and make the system's recognition and processing of instructions clearer and more orderly, thereby improving the accuracy and stability of signal processing. When a fault occurs, based on the clear division of labor of each input interface, technicians can quickly locate the source of the problem.

[0014] In a second aspect, the present invention provides a digital control method for intake and exhaust dampers in a ground test of an aircraft engine, comprising: an intake and exhaust damper opening control method and an intake and exhaust damper closing control method, wherein the intake and exhaust damper opening control method comprises:

[0015] Step S11: the operation panel sends a power-on command to the input interface of the intake and exhaust damper digital simulator;

[0016] Step S12: The simulator CPU parses the power-on instruction and sends it to the signal input module of the aircraft engine controller through the output interface;

[0017] Step S13: The controller CPU receives and analyzes the signal from the intake and exhaust damper digital simulator, generates an intake and exhaust damper opening enable signal, and feeds it back to the input interface of the intake and exhaust damper digital simulator;

[0018] Step S14: The simulator CPU processes the intake and exhaust damper opening enable signal according to the first preset control logic: confirming that the intake and exhaust damper opening enable signal is valid, initially setting the door opening action signal to invalid and the door closing action signal to valid, and activating the door actuator signal at the same time. After a preset delay time, the door opening action signal is set to valid and the door closing action signal is set to invalid, and the door actuator signal is turned off at the same time.

[0019] Step S15: The intake and exhaust damper digital simulator transmits the updated door opening motion signal, door closing motion signal, and door actuator signal to the signal input module of the aircraft engine controller via the output interface. The controller CPU processes the received signals and transmits the results to the host computer via the signal output module.

[0020] Step S16: The host computer displays the received processing result and terminates the process if the status is normal according to the processing result; otherwise, it returns to step S11 if the status is faulty.

[0021] The intake and exhaust damper closing control method comprises the following steps:

[0022] Step S21: The control panel sends a stop or emergency stop command to the input interface of the intake and exhaust damper digital simulator;

[0023] Step S22: The simulator CPU parses the received stop or emergency stop command and transmits it to the signal input module of the aircraft engine controller through the output interface;

[0024] Step S23: The controller CPU receives and analyzes the signal from the intake and exhaust damper digital simulator, generates an intake and exhaust damper closing enable signal, and feeds it back to the input interface of the intake and exhaust damper digital simulator;

[0025] Step S24: The simulator CPU processes the exhaust damper closing enable signal according to the second preset control logic: confirming that the intake and exhaust damper closing enable signal is valid, immediately sets the door opening action signal to invalid, while keeping the door actuator signal valid. After a preset delay, the door closing action signal is set to valid, and the door actuator signal is turned off.

[0026] Step S25: The intake and exhaust damper digital simulator outputs the updated door opening action signal, door closing action signal, and door actuator signal to the signal input module of the aircraft engine controller through its output interface. The controller CPU processes the received signals and transmits them to the host computer through the signal output module.

[0027] Step S26: The host computer displays the received processing result and ends the process if it is normal based on the processing result. Otherwise, it returns to step S21 if it is in a fault state.

[0028] In the process of opening and closing the intake and exhaust dampers, the embodiment of the present invention can highly restore the dynamic response process of the intake and exhaust dampers in actual flight by setting a delay signal to simulate the mechanical response time of the dampers. This enables ground tests to more accurately reflect the actual state of the engine and dampers working together, avoids deviations in test results caused by ignoring the mechanical characteristics of the dampers, and provides a reliable basis for engine performance evaluation. A closed-loop control mechanism is adopted, and signal feedback and processing are continuously carried out between the aircraft engine controller and the intake and exhaust damper digital simulator. This cyclic interaction ensures the accuracy and stability of the control signal and effectively improves the control accuracy of the entire control system; the upper computer monitors and displays the processing results in real time. Once a fault is detected, it automatically returns to the initial step to resend instructions for fault detection and repair. This timely feedback and processing mechanism can quickly locate and solve potential problems, avoid further deterioration of the fault, and ensure reliability and stability during the test process.

[0029] In an optional embodiment, the delay preset time is 3 seconds to simulate the delayed response of the damper mechanical action to ensure that the control logic is consistent with the physical action timing.

[0030] In actual flight, intake and exhaust dampers, as mechanical components, have inherent delays in opening and closing due to their structural characteristics. By setting a 3-second delay, we can accurately replicate the damper's response rhythm in real-world conditions, making the ground test environment infinitely closer to actual flight conditions and providing more realistic reference data. This also ensures that control logic aligns with physical action timing, preventing control confusion caused by asynchrony between signal transmission and mechanical response.

[0031] In an optional embodiment, the judgment logic of the host computer based on the processing result of the controller CPU includes:

[0032] If the controller CPU feedback signal is consistent with the preset control logic, it will be displayed as passed;

[0033] If there is a signal conflict, timing error, or no response after timeout, a fault message will be displayed and a process reset will be triggered.

[0034] The embodiment of the present invention can accurately determine whether the system is operating as expected by comparing the controller CPU feedback signal with the preset control logic. If the feedback signal is consistent with the preset logic, it will be displayed as passed, indicating that the system control logic is correct and the test results are credible. This provides a reliable basis for engine performance evaluation and ensures that the decisions and optimizations made based on the test data are accurate and effective. When signal conflicts, timing errors, or timeouts occur, the host computer can display fault information in a timely manner. These abnormal conditions may indicate hardware failures, software logic errors, or communication problems in the system. Discovering these potential problems in a timely manner can avoid the test from continuing in an erroneous state and prevent incorrect test results from being obtained, thereby ensuring the accuracy of the test results.

[0035] In an optional embodiment, the door actuator signal is activated during the damper action to simulate the power drive state of the actual actuator, and is turned off to cut off the power supply after the action is completed.

[0036] The embodiment of the present invention combines the mechanical movement of the damper with electrical control by simulating the electric drive state of the actuator, and completely reproduces the entire process of the damper from startup to completion of movement in the actual system, which helps to more comprehensively verify the collaborative working ability between the aircraft engine controller and the intake and exhaust damper digital simulator, and ensure that the simulation effect of the entire control system is real and effective.

[0037] In an optional implementation, after returning to step S11 or S21 in the fault state, the fault is repaired and the process is re-executed to verify the fault elimination result.

[0038] The embodiments of the present invention are based on accurate fault location, and technicians can repair the faulty parts in a targeted manner. Whether it is a hardware fault or a software fault, the corresponding components or logic can be adjusted and repaired based on the clear starting point of the fault, thereby improving the efficiency and accuracy of fault repair. Re-executing the process can not only verify the results of the current fault troubleshooting, but also timely discover potential problems and hidden dangers during the operation of the system, take preventive measures in advance, and effectively prevent the recurrence of the fault. When re-executing the process, each link of the system is monitored and analyzed in real time. If abnormal changes are found in certain parameters or signals, they can be adjusted and optimized in time to ensure the long-term stable operation of the system.

[0039] In a third aspect, an embodiment of the present invention provides a computer device, including:

[0040] A memory and a processor, wherein the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the digital control method for intake and exhaust dampers of an aircraft engine ground test of any optional embodiment of the second aspect by executing the computer instructions.

[0041] In a fourth aspect, an embodiment of the present invention provides a computer-readable storage medium having computer instructions stored thereon, wherein the computer instructions are used to enable a computer to execute the digital control method for intake and exhaust dampers of an aircraft engine ground test according to any optional embodiment of the second aspect.

[0042] In a fifth aspect, an embodiment of the present invention provides a computer program product comprising computer instructions, wherein the computer instructions are used to enable a computer to execute the digital control method for intake and exhaust dampers of an aircraft engine ground test according to any optional embodiment of the second aspect. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0044] Figure 1 2. It is a schematic diagram of the module structure of the digital control system for intake and exhaust dampers of an aircraft engine ground test according to an embodiment of the present invention;

[0045] Figure 2 is a flow chart of an intake and exhaust damper opening control method according to an embodiment of the present invention;

[0046] Figure 34 is a flow chart of an intake and exhaust damper closing control method according to an embodiment of the present invention.

[0047] Figure 4 Schematic diagram of the hardware structure of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0048] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are 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 those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0049] As a key component of an aircraft, the intake and exhaust dampers are responsible for regulating the inflow and outflow of air, and their control signals are directly derived from the aircraft engine controller. However, in ground tests, in order to focus on engine performance evaluation, the installation of the actual dampers is usually omitted. This leads to a key problem: how to accurately transmit the damper's action signal to the controller? Existing solutions simplify the problem by shielding fault signals (but sacrificing the authenticity of the test), or rely on physical testing (although accurate, inefficient and prone to failure). Although the shielding method is simple and easy to implement, it cannot reflect the actual state of the engine; the physical method seriously restricts the efficiency and accuracy of the test due to the complexity of installation, debugging and disassembly, as well as the uncertainty in operation.

[0050] In order to overcome the shortcomings of the prior art, the present invention provides an embodiment of a digital control system for intake and exhaust dampers of an aircraft engine ground test, such as Figure 1 As shown, it includes: an operation panel, a digital simulator for intake and exhaust dampers, an aircraft engine controller and a host computer, among which:

[0051] The operation panel is used to send opening or closing instructions for the intake and exhaust dampers to the intake and exhaust damper digital simulator; specifically, the operation panel serves as the central console of the user interaction interface and is equipped with a series of intuitive buttons and display screens, which are used for the operator sitting in front of the operating panel to send corresponding control instructions, thereby reducing the difficulty of operation and improving the convenience of operation.

[0052] The digital simulator for intake and exhaust dampers includes an input interface, a simulator CPU, a timer, and an output interface; the input interface is used to receive instructions from an operation panel and feedback signals from an aircraft engine controller; the simulator CPU is used to perform logical processing on the instructions and control the timer to generate a delay signal; and the output interface is used to output the control signal processed by the simulator CPU to the aircraft engine controller.

[0053] The simulator CPU in this embodiment of the present invention processes and analyzes commands from the control panel and feedback signals from the aircraft engine controller, providing a reliable basis for engine performance evaluation. The timer can adjust delay parameters as needed to accommodate different engine models or diverse test scenarios, enhancing the system's versatility and adaptability. For example, the timer is configured to generate a 3-second delay signal when the damper is actuated, simulating the damper's mechanical response time. This allows the ground test environment to more closely resemble actual flight conditions, ensuring that test results more accurately reflect the performance of the engine and damper working together.

[0054] An aircraft engine controller includes a signal input module, a controller CPU, and a signal output module; the signal input module is used to receive control signals from a digital simulator for intake and exhaust dampers; the controller CPU is used to analyze the signals and generate feedback signals; and the signal output module returns the feedback signals to the input interface of the digital simulator for intake and exhaust dampers, forming a closed-loop control.

[0055] The controller CPU of an embodiment of the present invention parses the received signal, determines the current state of the intake and exhaust dampers, generates a corresponding feedback signal, and sends it in real time to the input interface of the intake and exhaust damper digital simulator. It then dynamically compares the signal with the preset logic of the intake and exhaust damper digital simulator to ensure signal synchronization. For example, upon receiving a control signal to open the intake and exhaust dampers, the controller CPU analyzes the signal and, through the signal output module, feeds back the intake and exhaust damper opening enable signal to the input interface of the intake and exhaust damper digital simulator, forming a tight closed-loop control circuit. This ensures accurate signal transmission and processing within the system, thereby improving the control accuracy of the intake and exhaust dampers, ensuring that the engine's intake and exhaust volumes more closely meet design requirements, and enhancing the engine's overall performance.

[0056] The host computer is used to display the simulated status and operating status of the intake and exhaust dampers in real time, and judge whether it has passed or displayed fault information based on the feedback results of the controller CPU. The host computer in the embodiment of the present invention is like the monitoring center of the entire system, equipped with a high-definition display screen, which displays the simulated status of the intake and exhaust dampers and the operating status of the system in real time in the form of charts and data during the test. The operator can intuitively see key information such as the opening degree and action time of the damper. At the same time, the host computer also has an intelligent judgment function, and makes strict judgments based on the feedback results of the controller CPU. If everything is normal, the screen will clearly display "pass"; if a fault such as signal conflict, timing error or timeout is detected, the host computer will immediately display detailed fault information to remind the operator to deal with it in time.

[0057] Furthermore, the input interface and output interface of the intake and exhaust damper digital simulator, as well as the signal input module and signal output module of the aircraft engine controller, respectively input or output different command signals.

[0058] The embodiment of the present invention uses independent input and output port designs to isolate different types of signals from each other during transmission, reducing interference between signals. For example, the command signal of the operation panel and the enable signal of the controller CPU enter the simulator through different input interfaces, avoiding erroneous identification and processing that may be caused by signal cross-interference. Similarly, different output ports also ensure the independence and stability of various control signals when they are transmitted to the controller CPU, reducing the probability of system failure due to signal interference. When a system failure occurs, since each port has a clear function, technicians can quickly locate the location where the failure may occur, greatly shortening the troubleshooting time and improving the maintainability and reliability of the system.

[0059] The embodiment of the present invention also provides a digital control method for intake and exhaust dampers in a ground test of an aircraft engine, including: an intake and exhaust damper opening control method and an intake and exhaust damper closing control method, such as Figure 2 As shown, the method flow includes the following steps:

[0060] Step S11: The operation panel sends a power-on instruction to the input interface of the intake and exhaust damper digital simulator.

[0061] Specifically, in the actual scenario of aircraft engine ground testing, the operator sits in the test control room. After completing all equipment inspections and preparations, he presses the "Power On" button on the operation panel to trigger the power-on command. The power-on command is transmitted in the form of an electrical signal through a specific communication line to the 1# input interface of the intake and exhaust damper digital simulator.

[0062] Step S12: The simulator CPU parses the power-on instruction and sends it to the signal input module of the aircraft engine controller through the output interface.

[0063] Specifically, after the simulator receives the instruction, its internal simulator CPU quickly starts the parsing program to convert the original power-on instruction into a format that the system can understand. The parsing process needs to be combined with preset logic to eliminate illegal instructions or noise interference and verify the validity of the signal (such as check bits, timing matching, etc.). After the parsing is completed, the simulator sends the processed signal to the 1# input terminal of the aircraft engine controller through the 1# output interface. The invalid or abnormal signals are eliminated through the parsing logic, thereby improving the reliability of the control system and ensuring that the signal format transmitted to the controller is unified for easy subsequent processing.

[0064] Step S13: The controller CPU receives and analyzes the signal from the intake and exhaust damper digital simulator, generates an intake and exhaust damper opening enable signal, and feeds it back to the input interface of the intake and exhaust damper digital simulator.

[0065] Specifically, after receiving the signal, the controller CPU conducts in-depth parsing and analysis. Based on pre-set control logic and algorithms (such as state machine logic), it determines the current test requirements and system status, ultimately generating an intake and exhaust damper opening enable signal (such as an active-high signal). This signal is fed back through output port 1 to input port 2 of the intake and exhaust damper digital simulator, forming a closed-loop control link. A real-time feedback mechanism ensures consistency between the control signal and the execution status, achieving dynamic data synchronization between the controller and simulator.

[0066] Step S14: The simulator CPU processes the intake and exhaust damper opening enable signal according to the first preset control logic: confirms that the intake and exhaust damper opening enable signal is valid. In the initial state, the door opening action signal is set to invalid, the door closing action signal is set to valid, and the door actuator signal is activated at the same time. After a preset delay time, the door opening action signal is set to valid and the door closing action signal is set to invalid, and the door actuator signal is closed at the same time.

[0067] Specifically, after the 2# input interface of the simulator CPU receives the enable signal, the first preset control logic is activated:

[0068] 1. Set the door opening action signal to invalid (low level) and the door closing action signal to valid (high level) to simulate the initial closed state of the damper;

[0069] 2. Output door actuator activation signal (such as pulse signal) to simulate the electric drive of the actual actuator;

[0070] 3. Start the timer for a 3-second delay to simulate the physical response time of the damper mechanical action;

[0071] 4. After the delay ends, the door opening action is switched to valid and the closing action is switched to invalid, and the door actuator signal is turned off.

[0072] The delay characteristics of the throttle mechanical action are accurately reproduced through delay logic to improve the authenticity of ground tests. The sequential control of action signals is achieved through preset logic to avoid signal conflicts (such as opening and closing at the same time). The delay preset time is determined to be 3 seconds through experiments to simulate the delayed response of the throttle mechanical action, making the ground test environment infinitely close to the actual flight state, ensuring that the control logic is consistent with the physical action timing, and avoiding control confusion caused by the lack of synchronization between signal transmission and mechanical response.

[0073] Step S15: The intake and exhaust damper digital simulator sends the updated door opening action signal, door closing action signal, and door actuator signal to the signal input end of the controller CPU through the output interface. The controller CPU processes the received signal and uploads the result to the host computer.

[0074] Specifically, the simulator transmits updated action signals to the corresponding inputs of the controller via multiple output interfaces (e.g., output interfaces 3#, 4#, and 5#). The controller CPU performs secondary analysis on the received signals (e.g., verifying the logical consistency of the action signal with the enable signal) and uploads the processing results (e.g., "action completed" or "abnormal") to the host computer via a communication interface (e.g., Ethernet). Transmitting different action signals via independent output interfaces avoids signal crosstalk. Real-time communication between the controller and the host computer provides operators with dynamic status visualization support.

[0075] Step S16: The host computer displays the received processing result and ends the process if it is normal based on the processing result. Otherwise, it returns to step S11 if it is in a fault state.

[0076] Specifically, the host computer displays the damper opening status (such as "closing completed" or "fault code") in real time, and intuitively displays the damper status through a graphical interface, reducing the complexity of manual inspections, and quickly locating the fault type through preset judgment logic, shortening the troubleshooting time.

[0077] The intake and exhaust damper closing control method in the embodiment of the present invention is as follows: Figure 3 As shown, the following steps are included:

[0078] Step S21: The control panel sends a stop or emergency stop command to the input interface of the intake and exhaust damper digital simulator.

[0079] Specifically, when an emergency stop or damper closure is required, the operating panel sends a stop or emergency stop command to the 2# input interface of the intake and exhaust damper digital simulator. Emergency stop commands are usually high-priority signals and require the use of anti-interference communication protocols (such as CAN bus or hard-wired signals) to ensure the real-time and reliability of signal transmission. The embodiment of the present invention meets the safety requirements of sudden working conditions in aircraft engine tests by supporting the rapid triggering of high-priority commands. The independent input interface design avoids conflicts with other control signals and ensures the independence of emergency actions.

[0080] Step S22: The simulator CPU parses the received stop or emergency stop command and transmits it to the signal input module of the aircraft engine controller through the output interface;

[0081] Specifically, after receiving a stop or emergency stop command, the simulator CPU first verifies the signal's validity (e.g., checksum verification) and transmits a standardized control signal to the controller CPU via an output interface (e.g., output interface 6). The signal format must match the controller's input protocol (e.g., PWM, digital I / O) to ensure compatibility. Parsing logic filters out noise or abnormal signals, improving the reliability of emergency commands. Standardized output ensures seamless interoperability between different controller models, enhancing system adaptability.

[0082] Step S23: The controller CPU receives and analyzes the signal from the intake and exhaust damper digital simulator, generates an intake and exhaust damper closing enable signal, and feeds it back to the input interface of the intake and exhaust damper digital simulator.

[0083] Specifically, for example, the controller CPU executes preset safety logic (such as an emergency stop state machine) based on the received stop command, generating a shutdown enable signal (such as a continuously high level). This signal is fed back to the simulator via an independent output terminal (such as the 2# signal output port), forming a closed-loop control link. The rapid feedback of the enable signal ensures dynamic synchronization of the control link.

[0084] Step S24: The simulator CPU processes the exhaust damper closing enable signal according to the second preset control logic: confirming that the intake and exhaust damper closing enable signal is valid, immediately sets the door opening action signal to invalid, and keeps the door actuator signal in a valid state. After a preset delay time, the door closing action signal is set to valid, and the door actuator signal is closed at the same time.

[0085] Specifically, the simulator CPU performs the following operations according to the second preset control logic:

[0086] 1. Confirm that the intake and exhaust damper closing enable signal is valid;

[0087] 2. Disable the door opening signal to avoid damper action conflicts, maintain the actuator signal valid, and ensure the power supply for the damper closing action;

[0088] 3. Use a timer to delay for 3 seconds to simulate the physical delay of the damper mechanical closing to ensure that the timing is consistent with the actual working conditions;

[0089] 4. After the delay ends, the door closing action is set to valid and the actuator power is cut off to complete the closing process.

[0090] The embodiment of the present invention eliminates the risk of simultaneous opening and closing by forcing the door to open and close. The delay logic reproduces the mechanical inertia of the damper closing, thereby improving the accuracy of the test data. The preset delay time is determined to be 3 seconds through experiments to simulate the delayed response of the damper mechanical action, so that the ground test environment is infinitely close to the actual flight state, ensuring that the control logic is consistent with the physical action timing, and avoiding control confusion caused by the lack of synchronization between signal transmission and mechanical response.

[0091] Step S25: The intake and exhaust damper digital simulator outputs the updated door opening action signal, door closing action signal, and door actuator signal to the signal input module of the aircraft engine controller through its output interface. The controller CPU processes the received signals and sends them to the host computer through the signal output module.

[0092] Specifically, the simulator transmits updated door action signals to the controller (e.g., signal input ports 2, 3, and 4) via multiple output interfaces (e.g., output interfaces 3, 4, and 5). The controller CPU performs a secondary check on the signals (e.g., logical consistency check between the action signal and the enable signal) to ensure there are no timing misalignments or signal loss. This multi-channel, independent signal transmission prevents signal crosstalk and improves fault tolerance.

[0093] Step S26: The host computer displays the received processing result and ends the process if it is normal based on the processing result. Otherwise, it returns to step S21 if it is in a fault state.

[0094] Specifically, the host computer displays the damper closing status (such as "closing completed" or "fault code") in real time, and intuitively displays the damper status through a graphical interface, reducing the complexity of manual inspections, and quickly locating the fault type through preset judgment logic, shortening the troubleshooting time.

[0095] Furthermore, in this embodiment of the present invention, the host computer performs a logical judgment based on the results uploaded by the controller: if the controller CPU feedback signal is consistent with the preset control logic, it displays a pass and ends the process; if there is a signal conflict, timing error, or no response after a timeout, a fault message is displayed and the process is reset. This preset judgment logic allows the fault type to be quickly located, shortening troubleshooting time, and the automatic reset mechanism reduces manual intervention and improves test efficiency.

[0096] After a fault condition, the system returns to step S11 or S21 to repair the fault and re-executes the process to verify the troubleshooting results. This forms a closed-loop verification mechanism, eliminating the need for manual reset or restart, reducing operational complexity and the risk of human error. By re-executing the entire process (such as power-on or emergency stop commands), it is verified that the repaired system meets the preset logic, ensuring that the fault has been completely eliminated.

[0097] An automatic retry mechanism after fault repair prevents test process interruptions and ensures stability during long-term tests. In complex test scenarios (such as multi-cycle endurance tests), the system automatically recovers and continues execution, preventing test data loss or equipment downtime due to a single fault. By dynamically resetting the initial state, residual fault signals (such as conflicting levels or logic latches) are cleared, preventing secondary fault triggering. By repeatedly executing the initial process and combining it with real-time monitoring data from the host computer, the system can quickly locate the root cause of the fault.

[0098] The embodiment of the present invention also provides a computer device having the above Figure 1 The variable cycle wide range engine turbine design system is shown. Figure 4 , Figure 4 is a schematic diagram of the structure of a computer device provided by an optional embodiment of the present invention, such as Figure 4 As shown, the computer device includes: one or more processors 10, memory 20, and interfaces for connecting various components, including high-speed interfaces and low-speed interfaces. Various components utilize different buses to communicate with each other and can be installed on a common mainboard or installed in other ways as needed. The processor can process the instructions executed in the computer device, including instructions stored in the memory or on the memory to display the graphical information of the GUI on an external input / output device (such as, a display device coupled to the interface). In some optional embodiments, if necessary, multiple processors and / or multiple buses can be used together with multiple memories and multiple memories. Equally, multiple computer devices can be connected, and each device provides part of the necessary operations (for example, as a server array, a group of blade servers, or a multi-processor system). Figure 4 A processor 10 is taken as an example.

[0099] The processor 10 may be a central processing unit, a network processor, or a combination thereof. The processor 10 may further include a hardware chip. The hardware chip may be an application-specific integrated circuit, a programmable logic device, or a combination thereof. The programmable logic device may be a complex programmable logic device, a field programmable gate array, a general purpose array logic, or any combination thereof.

[0100] The memory 20 stores instructions that can be executed by at least one processor 10, so as to enable at least one processor 10 to execute the method shown in the above embodiment.

[0101] The memory 20 may include a program storage area and a data storage area, wherein the program storage area may store an operating system and application programs required for at least one function; the data storage area may store data created based on the use of the computer device, etc. In addition, the memory 20 may include a high-speed random access memory, and may also include a non-transient memory, such as at least one disk storage device, a flash memory device, or other non-transient solid-state storage device. In some optional embodiments, the memory 20 may optionally include a memory remotely located relative to the processor 10, and these remote memories may be connected to the computer device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0102] The memory 20 may include a volatile memory, such as a random access memory; the memory may also include a non-volatile memory, such as a flash memory, a hard disk or a solid-state drive; the memory 20 may also include a combination of the above types of memory.

[0103] The computer device further includes a communication interface 30 for the computer device to communicate with other devices or a communication network.

[0104] The embodiment of the present invention also provides a computer-readable storage medium. The above-mentioned method according to the embodiment of the present invention can be implemented in hardware, firmware, or implemented as a computer code that can be recorded in a storage medium, or implemented as a computer code that is originally stored in a remote storage medium or a non-temporary machine-readable storage medium and downloaded through a network and will be stored in a local storage medium, so that the method described herein can be stored in such software processing on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. Among them, the storage medium can be a magnetic disk, an optical disk, a read-only storage memory, a random access memory, a flash memory, a hard disk or a solid-state drive, etc.; further, the storage medium can also include a combination of the above-mentioned types of memory. It can be understood that a computer, a processor, a microprocessor central control system or programmable hardware includes a storage component that can store or receive software or computer code. When the software or computer code is accessed and executed by a computer, a processor or hardware, the method shown in the above embodiment is implemented.

[0105] A portion of the present invention may be applied as a computer program product, such as a computer program instruction, which, when executed by a computer, can call or provide the method and / or technical solution according to the present invention through the operation of the computer. Those skilled in the art should understand that the form in which the computer program instruction exists in a computer-readable medium includes, but is not limited to, a source file, an executable file, an installation package file, etc. Accordingly, the way in which the computer program instruction is executed by the computer includes, but is not limited to: the computer directly executes the instruction, or the computer compiles the instruction and then executes the corresponding compiled program, or the computer reads and executes the instruction, or the computer reads and installs the instruction and then executes the corresponding installed program. Here, the computer-readable medium may be any available computer-readable storage medium or communication medium that can be accessed by the computer.

[0106] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A digital control system for intake and exhaust dampers of aircraft engines for ground testing, characterized in that: include: Operation panel, intake and exhaust damper digital simulator, aircraft engine controller and host computer, including: An operation panel, used for sending an opening or closing instruction of the intake and exhaust dampers to the intake and exhaust damper digital simulator; The digital simulator for intake and exhaust dampers includes an input interface, a simulator CPU, a timer, and an output interface; the input interface is used to receive instructions from an operation panel and feedback signals from an aircraft engine controller; the simulator CPU is used to perform logical processing on the instructions and control the timer to generate a delay signal; and the output interface is used to output the control signal processed by the simulator CPU to the aircraft engine controller. An aircraft engine controller includes a signal input module, a controller CPU, and a signal output module; the signal input module is used to receive control signals from a digital simulator for intake and exhaust dampers; the controller CPU is used to analyze the signals and generate feedback signals; and the signal output module returns the feedback signals to the input interface of the digital simulator for intake and exhaust dampers, thereby forming a closed-loop control system. The host computer is used to display the simulation status and operation status of the intake and exhaust dampers in real time, and judge whether it passes or displays fault information based on the feedback results from the controller CPU.

2. The system according to claim 1, wherein: The input interface, output interface, input module, and output module all include multiple ports, which respectively input or output different command signals.

3. A digital control method for intake and exhaust dampers of an aircraft engine ground test, characterized in that: include: Intake and exhaust damper opening control method and intake and exhaust damper closing control method, wherein the intake and exhaust damper opening control method includes: Step S11: the operation panel sends a power-on command to the input interface of the intake and exhaust damper digital simulator; Step S12: The simulator CPU parses the power-on instruction and sends it to the signal input module of the aircraft engine controller through the output interface; Step S13: The controller CPU receives and analyzes the signal from the intake and exhaust damper digital simulator, generates an intake and exhaust damper opening enable signal, and feeds it back to the input interface of the intake and exhaust damper digital simulator; Step S14: The simulator CPU processes the intake and exhaust damper opening enable signal according to the first preset control logic: confirming that the intake and exhaust damper opening enable signal is valid, initially setting the door opening action signal to invalid and the door closing action signal to valid, and activating the door actuator signal at the same time. After a preset delay time, the door opening action signal is set to valid and the door closing action signal is set to invalid, and the door actuator signal is turned off at the same time. Step S15: The intake and exhaust damper digital simulator transmits the updated door opening motion signal, door closing motion signal, and door actuator signal to the signal input module of the aircraft engine controller via the output interface. The controller CPU processes the received signals and transmits the results to the host computer via the signal output module. Step S16: The host computer displays the received processing result and terminates the process if the status is normal according to the processing result; otherwise, it returns to step S11 if the status is faulty. The intake and exhaust damper closing control method comprises the following steps: Step S21: The control panel sends a stop or emergency stop command to the input interface of the intake and exhaust damper digital simulator; Step S22: The simulator CPU parses the received stop or emergency stop command and transmits it to the signal input module of the aircraft engine controller through the output interface; Step S23: The controller CPU receives and analyzes the signal from the intake and exhaust damper digital simulator, generates an intake and exhaust damper closing enable signal, and feeds it back to the input interface of the intake and exhaust damper digital simulator; Step S24: The simulator CPU processes the exhaust damper closing enable signal according to the second preset control logic: confirming that the intake and exhaust damper closing enable signal is valid, immediately sets the door opening action signal to invalid, while keeping the door actuator signal valid. After a preset delay, the door closing action signal is set to valid, and the door actuator signal is turned off. Step S25: The intake and exhaust damper digital simulator outputs the updated door opening action signal, door closing action signal, and door actuator signal to the signal input module of the aircraft engine controller through its output interface. The controller CPU processes the received signals and transmits them to the host computer through the signal output module. Step S26: The host computer displays the received processing result and ends the process if it is normal based on the processing result. Otherwise, it returns to step S21 if it is in a fault state.

4. The method according to claim 3, characterized in that The delay preset time is 3 seconds, which is used to simulate the delayed response of the damper mechanical action to ensure that the control logic is consistent with the physical action timing.

5. The method according to claim 3, characterized in that The host computer's judgment logic based on the controller CPU processing result includes: If the controller CPU feedback signal is consistent with the preset control logic, it will be displayed as passed; If there is a signal conflict, timing error, or no response after timeout, a fault message will be displayed and a process reset will be triggered.

6. The method according to claim 3, characterized in that The door actuator signal is activated during the damper operation to simulate the power drive state of the actual actuator, and is turned off to cut off the power supply after the operation is completed.

7. The method according to claim 3, characterized in that After returning to step S11 or S21 in the fault state, the fault is repaired and the process is re-executed to verify the fault elimination result.

8. A computer device, characterized in that: include: A memory and a processor, wherein the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the digital control method for intake and exhaust dampers of an aircraft engine ground test according to any one of claims 3 to 7 by executing the computer instructions.

9. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a computer to execute the digital control method for intake and exhaust dampers of an aircraft engine ground test according to any one of claims 3 to 7.

10. A computer program product, characterized in that The method comprises computer instructions for causing a computer to execute the digital control method for intake and exhaust dampers of an aero-engine ground test according to any one of claims 3 to 7.

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