One-key stop method and device for aircraft fatigue test

Abstract

The invention belongs to the technical field of aircraft test measurement and control, and particularly relates to a one-key stop method and device for an aircraft fatigue test. The method comprises the following steps: S1, identifying all fatigue testing machines which are connected with an upper computer and are controlled by an instruction of the upper computer; s2, on the stop control interface, corresponding controls are generated for the fatigue testing machines in sequence, each control is provided with a stop option and a timed stop option after flight takeoff and landing are completed, the timed stop option is associated with a stop time setting assembly, and meanwhile, an emergency all-stop control for immediately stopping all the fatigue testing machines is generated; s3, receiving setting of the user for each optional item or all emergency stop controls; and S4, sending a set result to a lower computer PLC (Programmable Logic Controller), analyzing the set result by the lower computer PLC, issuing a control instruction to a control system of each fatigue testing machine, and performing pressure relief operation on the fatigue testing machines by the control system. The fatigue period is shortened, and the working efficiency is improved.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft test measurement and control, and particularly relates to a one-key stop method and device for aircraft fatigue tests. Background Art

[0002] When conducting aircraft model tests, multiple fatigue tests are often run simultaneously in the test laboratory, and there are often situations where they all stop at the same time. Generally, after a flight landing, the operations for the test usually include single-step stop, single-step forward, advancing the buckle in multiple bands, pressure relief, etc. If four, five, or even more than ten tests require these operations simultaneously, it places high demands on the ability of the on-duty personnel. Inevitably, the tests will be stopped prematurely at the wrong time, wasting more than one or even two hours of effective operation time. Summary of the Invention

[0003] To solve the above problems, this application provides a one-key stop method and device for aircraft fatigue tests, which realizes the one-key stop of fatigue tests through the combination of a host computer and a slave computer.

[0004] The first aspect of this application provides a one-key stop method for aircraft fatigue tests, mainly including

[0005] Step S1: Identify all fatigue testing machines connected to the host computer and controlled by the host computer's instructions.

[0006] Step S2: On the stop control interface, generate corresponding controls for the fatigue testing machines in sequence. Each control has an option to stop after a flight landing and an option to stop at a scheduled time. The option to stop at a scheduled time is associated with a stop time setting component, and at the same time, an emergency all-stop control for immediately stopping all fatigue testing machines is generated.

[0007] Step S3: Receive the settings of the user for each option or the emergency all-stop control.

[0008] Step S4: Send the setting result to the slave computer PLC. After the slave computer PLC analyzes the setting result, it issues control instructions to the control systems of each fatigue testing machine, and the control system performs a pressure relief operation on the fatigue testing machine.

[0009] Preferably, the slave computer PLC is connected to a remote module set at each control system through a local area network, and the remote module is configured to be connected to the control system for input and output of digital quantity signals.

[0010] Preferably, further included after step S4:

[0011] When the control system completes the pressure relief operation on the fatigue testing machine, it gives an operation completion prompt signal.

[0012] Preferably, the prompt signal is an audio signal, and / or a signal that is fed back to the host computer and used by the host computer to update the system status.

[0013] Preferably, step S2 further includes:

[0014] Step S21: Provide a monitoring interface for real-time data acquisition and display of the fatigue test. A stop setting control is provided on the monitoring interface.

[0015] Step S22: Respond to the user's stop setting request and switch to the stop control interface.

[0016] The second aspect of the present application provides a one-key stop device for aircraft fatigue tests, mainly including:

[0017] A fatigue testing machine identification module, configured to identify all fatigue testing machines connected to the host computer and controlled by the host computer's instructions.

[0018] A stop control interface generation module, configured to generate corresponding controls for the fatigue testing machines in sequence on the stop control interface. Each control has options for stopping after the completion of flight takeoffs and landings and options for timed stops. The timed stop options are associated with stop time setting components. At the same time, an emergency all-stop control for immediately stopping all fatigue testing machines is generated.

[0019] A stop setting instruction receiving module, configured to receive the settings of the user for each option or the emergency all-stop control.

[0020] A fatigue testing machine stop instruction execution module, configured to send the setting result to the lower-level PLC. After the lower-level PLC analyzes the setting result, control instructions are issued to the control systems of the respective fatigue testing machines, and the control systems perform pressure relief operations on the fatigue testing machines.

[0021] Preferably, the lower-level PLC is connected to a remote module provided at each control system through a local area network. The remote module is configured to be connected to the control system for input and output of digital quantity signals.

[0022] Preferably, the device further includes:

[0023] A prompt module, configured to give an operation completion prompt signal after the control system completes the pressure relief operation on the fatigue testing machine.

[0024] Preferably, the prompt signal is an audio signal, and / or a signal that is fed back to the host computer and used by the host computer to update the system status.

[0025] Preferably, the stop control interface generation module further includes:

[0026] A monitoring interface presenting unit, configured to present a monitoring interface for real-time data acquisition and display of a fatigue test, wherein a stop setting control is provided on the monitoring interface;

[0027] An interface switching unit, configured to respond to a user's stop setting request and switch to a stop control interface.

[0028] This application shortens the fatigue cycle and improves work efficiency. Description of the Drawings

[0029] Figure 1 is a flowchart of a preferred embodiment of the one-key stop method for aircraft fatigue test in this application.

[0030] Figure 2 is a schematic diagram of the stop control interface. Detailed Description of the Embodiment

[0031] To make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the drawings in the embodiments of this application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements with the same or similar functions from beginning to end. The described embodiments are some but not all of the embodiments of this application. The embodiments described below by referring to the drawings are exemplary and are intended to explain this application and should not be construed as limiting this application. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the drawings.

[0032] The first aspect of this application provides a one-key stop method for aircraft fatigue test, as Figure 1 shown, mainly including:

[0033] Step S1: Identify all fatigue testing machines connected to the host computer and controlled by the host computer instructions;

[0034] Step S2: On the stop control interface, generate corresponding controls for the fatigue testing machines in sequence. Each control has an option to stop after the completion of flight takeoffs and landings and an option to stop at a scheduled time. The option to stop at a scheduled time is associated with a stop time setting component. At the same time, an emergency all-stop control for immediately stopping all fatigue testing machines is generated;

[0035] Step S3: Receive the settings of the user for each option or the emergency all-stop control;

[0036] Step S4: Send the setting result to the lower-level PLC. After the lower-level PLC parses the setting result, it issues control instructions to the control systems of each fatigue testing machine, and the control system performs a pressure relief operation on the fatigue testing machine.

[0037] This application has developed a brand-new one-key stop system for fatigue tests, which can achieve one-key stop of fatigue tests through the combination of the upper computer and the lower computer. The above method is implemented on the upper computer. The upper computer software at the application layer is written in the visual programming language LabView and is closely integrated with the hardware platform. It can perform stop operations for each test, and the execution status is intuitively displayed on the computer interface. The lower computer uses a programmable logic controller, namely PLC, as the control core, and is connected to the digital input and output of the control system through relays, forming the perception layer of the Internet of Things to complete the state acquisition and control functions of the control system. The network layer uses optical fibers, network cables, and switches to form a local area network to complete data upload and download.

[0038] In some alternative embodiments, the lower-level PLC is connected to remote modules provided at each control system through a local area network, and the remote modules are configured to be connected to the control system for input and output signals of switch quantities.

[0039] In this embodiment, the DI and DO of the remote module are connected to the DO and DI of the control system. The remote module is adopted because the test pieces are very discrete inside the laboratory, and the positions of multiple control systems are not fixed. A single remote module only needs to be connected to the switch through a network cable and form a local area network with the main control PLC to achieve communication, which brings convenience to wiring and transplantation.

[0040] Through the above combination design of software and hardware, in step S1, the upper computer can identify all control systems connected thereto, that is, all fatigue testing machines can be identified. Then, in step S2, a stop control interface is generated, and in step S3, the operations of the user on the stop control interface are received.

[0041] As Figure 2 shown, there are three control methods for setting the stop for each fatigue test in the stop control interface.

[0042] The first is to check "Stop after this landing is completed". This test will automatically stop after the current landing is completed. This is the most widely used method because during the operation of the aircraft strength test, the load will be continuously switched. The first row of each landing has the smallest load or zero load. At this time, unloading and pressure relief cause the least impact on the aircraft or the loading mechanism. After checking all the test options, click the "Send Stop Instruction" button, and the system will automatically stop the corresponding test according to the instruction. The tests that are not checked will not stop automatically.

[0043] The second control method is to check "Stop at Set Time", then set the stop time, and click the "Send Stop Command" button. In this way, the system will automatically send a stop command to the control system and the hydraulic system when the time arrives, and automatically complete the stop operation. This mode is designed for situations where, in certain special cases, several tests need to be stopped simultaneously, and the duty personnel are unable to operate several control systems at the same time. This device uses a combination of software and hardware techniques to achieve functions that cannot be completed manually, improving work efficiency.

[0044] The third control method is to directly click the "Emergency All Stop" button. The system will pop up a prompt box to confirm that all fatigue tests need to be stopped. After confirmation, it will immediately send a stop command to the control systems of all fatigue tests and automatically stop the corresponding hydraulic oil pumps. The system will complete all operations within a few seconds. This method is to quickly stop all tests in the event of major emergencies such as oil spraying or fire at the site to protect the safety of the test pieces and the loading mechanism. If there are multiple fatigue tests running, when the duty personnel encounter such a situation, they cannot react quickly enough to stop the tests correctly, which will cause serious consequences.

[0045] After that, in step S4, a command is sent, and the lower computer controls the fatigue testing machine.

[0046] After setting and executing the stop command through the software, the monitoring software will send corresponding stop commands according to different tests. After the PLC receives the command, it completes the digital quantity command output operation. The digital quantity input channel of the control system completes the corresponding operation after detecting the stop command. After pressure relief, the PLC sends a pump stop and pressure relief command to the corresponding hydraulic system to complete the stop operation of the entire fatigue test.

[0047] In some alternative embodiments, after step S4, it further includes:

[0048] When the control system completes the pressure relief operation of the fatigue testing machine, it gives an operation completion prompt signal.

[0049] In some alternative embodiments, the prompt signal is a sound signal, and / or a signal that is fed back to the upper computer and the upper computer updates the system status.

[0050] In some alternative embodiments, step S2 further includes:

[0051] Step S21: Present a monitoring interface for real-time data acquisition and display of the fatigue test, and a stop setting control is provided on the monitoring interface;

[0052] Step S22: Respond to the user's stop setting request and switch to the stop control interface.

[0053] In this embodiment, the stop control interface is a secondary interface of the monitoring interface. In the monitoring interface, the upper computer fatigue test monitoring software can monitor the fatigue test status of the laboratory operation in real time. Specifically, it can monitor the operation status of 6 fatigue tests, charging status, oil source pressure, gas source pressure, temperature and humidity, etc. on site in real time. If it is necessary to stop the test, click the "Stop Setting" button in the upper left corner, and the system will pop up Figure 2 the stop setting interface shown as follows.

[0054] This application constructs a one-key stop system for fatigue tests through a combination of software and hardware technologies, laying a foundation for building a large-scale laboratory digital management system, improving work efficiency, shortening the fatigue cycle, saving operation costs, having a low input cost, being able to be replicated in large quantities, and adopting the Internet of Things development method, which is convenient for debugging and uploading test data. In addition, if you want to expand the functions of the entire system in the future, it can be completed simply through the data connection between modules.

[0055] The second aspect of this application provides a one-key stop device for aircraft fatigue tests corresponding to the above method, mainly including:

[0056] A fatigue testing machine identification module, used to identify all fatigue testing machines connected to the upper computer and receiving control instructions from the upper computer;

[0057] A stop control interface generation module, used to generate corresponding controls for the fatigue testing machines in sequence on the stop control interface. Each control has options for stopping after the flight landing is completed and options for timed stop. The timed stop option is associated with a stop time setting component, and at the same time, an emergency all-stop control for immediately stopping all fatigue testing machines is generated;

[0058] A stop setting instruction receiving module, used to receive the settings of the user for each option or the emergency all-stop control;

[0059] A fatigue testing machine stop instruction execution module, used to send the setting result to the lower computer PLC. After the lower computer PLC analyzes the setting result, control instructions are sent to the control systems of each fatigue testing machine, and the control system performs a pressure relief operation on the fatigue testing machine.

[0060] In some alternative embodiments, the lower computer PLC is connected to a remote module set at each control system through a local area network, and the remote module is configured to be connected to the control system for input and output signals of switch quantities.

[0061] In some alternative embodiments, the device further includes:

[0062] A prompt module, used to give an operation completion prompt signal when the control system completes the pressure relief operation on the fatigue testing machine.

[0063] In some alternative embodiments, the prompt signal is a sound signal, and / or a signal fed back to the host computer for the host computer to update the system state.

[0064] In some alternative embodiments, the stop control interface generation module further includes:

[0065] A monitoring interface presentation unit for presenting a monitoring interface for real-time data acquisition and display of the fatigue test, and a stop setting control is provided on the monitoring interface;

[0066] An interface switching unit for switching to the stop control interface in response to a user's stop setting request.

[0067] As described above, the above are only specific embodiments of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered by the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A one-button stop method for aircraft fatigue testing, characterized in that: include: Step S1, identifying all fatigue testing machines connected to the host computer and receiving commands from the host computer; Step S2, in the stop control interface, corresponding controls are generated for the fatigue testers in sequence, each control having a stop option after the flight takeoff and landing is completed and a timed stop option, the timed stop option is associated with a stop time setting component, and an emergency all stop control is generated for immediately stopping all fatigue testers; Step S3, receiving the user's settings for each optional item or emergency stop all controls; Step S4, sending the setting result to the lower computer PLC, the lower computer PLC analyzes the setting result and issues control instructions to the control system of each fatigue testing machine, and the control system performs pressure relief operation on the fatigue testing machine.

2. The one-button stop method for aircraft fatigue testing according to claim 1, characterized in that: The lower computer PLC is connected to a remote module arranged at each control system via a local area network, and the remote module is arranged to be connected to the control system for input and output signals of switch quantities.

3. The one-button stop method for aircraft fatigue testing according to claim 1, characterized in that: Step S4 further includes: When the control system completes the pressure relief operation on the fatigue testing machine, it gives an operation completion prompt signal.

4. The one-button stop method for aircraft fatigue testing according to claim 3, characterized in that: The prompt signal is a sound signal, and / or a signal fed back to the host computer and used by the host computer to update the system status.

5. The one-button stop method for aircraft fatigue testing according to claim 1, characterized in that: Step S2 further comprises: Step S21, providing a monitoring interface for real-time data collection and display of fatigue test, wherein a stop setting control is provided on the monitoring interface; Step S22: respond to the user's stop setting request and switch to the stop control interface.

6. A one-button stop device for aircraft fatigue testing, characterized in that: include: Fatigue testing machine identification module, used to identify all fatigue testing machines connected to the host computer and receiving commands and control from the host computer; A stop control interface generation module is used to generate corresponding controls for fatigue test machines in sequence on the stop control interface. Each control has a stop option after the flight takeoff and landing is completed and a timed stop option. The timed stop option is associated with a stop time setting component. At the same time, an emergency stop control for immediately stopping all fatigue test machines is generated; A stop setting instruction receiving module is used to receive the user's settings for each optional item or emergency all stop controls; The fatigue testing machine stop command execution module is used to send the setting results to the lower computer PLC. After the lower computer PLC analyzes the setting results, it issues control commands to the control systems of each fatigue testing machine, and the control system performs pressure relief operations on the fatigue testing machine.

7. The one-button stop device for aircraft fatigue testing according to claim 6, characterized in that: The lower computer PLC is connected to a remote module arranged at each control system via a local area network, and the remote module is arranged to be connected to the control system for input and output signals of switch quantities.

8. The one-button stop device for aircraft fatigue testing according to claim 6, characterized in that: The device also includes: The prompt module is used to give an operation completion prompt signal after the control system completes the pressure relief operation on the fatigue testing machine.

9. The one-button stop device for aircraft fatigue testing according to claim 8, characterized in that: The prompt signal is a sound signal, and / or a signal fed back to the host computer and used by the host computer to update the system status.

10. The one-button stop device for aircraft fatigue testing according to claim 6, characterized in that: The stop control interface generation module further includes: A monitoring interface presentation unit, used to present a monitoring interface for real-time data collection and presentation of fatigue tests, wherein a stop setting control is provided on the monitoring interface; The interface switching unit is used to respond to the user's stop setting request and switch to the stop control interface.

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