Constant amplitude vibration measuring device for aircraft hydraulic lines and method for locating abnormal vibration points

Abstract

The present application relates to the technical field of aircraft hydraulic pipeline vibration testing, and particularly relates to a constant steady vibration measuring device for an aircraft hydraulic pipeline, comprising: a fastening module, which is used for mounting the constant steady vibration measuring device on a hydraulic pipeline system support or an aircraft body structure; a universal stabilizer, which is mounted on the fastening module; a laser vibration sensor, which is mounted on the universal stabilizer, is used for non-contact collection of real-time vibration data of an aircraft hydraulic pipeline vibration measuring point, and measures a relative position of the laser vibration sensor and the aircraft hydraulic pipeline vibration measuring point; and a space tracking positioner, which is mounted on the universal stabilizer, is used for measuring a position of the laser vibration sensor. The device of the present application can accurately collect aircraft hydraulic pipeline vibration data without directly contacting the pipeline vibration measuring point.

Description

Technical Field

[0001] This invention relates to the field of vibration testing technology for aircraft hydraulic lines, and in particular to a constant vibration measuring device for aircraft hydraulic lines and a method for locating abnormal vibration points. Background Technology

[0002] The hydraulic piping system, acting as the "blood vessels" of an aircraft, transmits hydraulic energy to hydraulic actuators, ensuring the safe and stable operation of all hydraulically actuated components. Excessive vibration in the piping can cause hydraulic line rupture, and current technology struggles to efficiently, accurately, and visually locate abnormal vibration points.

[0003] Current methods for acquiring vibration data require the testing device to be in direct contact with the vibration measurement point on the hydraulic pipeline. However, installing the testing device on the pipeline presents numerous challenges. For example, a typical approach involves installing strain gauges onto the pipeline. In practical applications, some hydraulic pipelines have complex designs, making the installation of strain gauges cumbersome and complicated. Even after installation, the strain gauges are prone to detaching from the pipeline. Furthermore, relative movement between the testing device and the hydraulic pipeline inevitably negatively impacts the accuracy of the acquired data. Therefore, acquiring vibration data is inherently difficult.

[0004] Furthermore, the current process of locating abnormal vibration points in aircraft hydraulic lines based on vibration information requires solid professional background knowledge. However, in actual aircraft maintenance work, not all operators possess such in-depth professional knowledge, thus slowing down the troubleshooting process. To solve this problem, there is an urgent need for a method for visually locating abnormal vibration points. This method needs to be able to intuitively and clearly present the location of abnormal vibration points, helping operators lacking professional background knowledge to quickly and accurately troubleshoot aircraft faults and improve work efficiency. Summary of the Invention

[0005] To solve the above-mentioned technical problems, the present invention provides a constant vibration measurement device that can accurately collect vibration data of aircraft hydraulic lines without direct contact with the vibration measurement points of hydraulic lines, and uses this device to locate abnormal vibration points of aircraft hydraulic lines.

[0006] On one hand, the present invention provides a constant-stability vibration measuring device for aircraft hydraulic lines, comprising:

[0007] Fastening modules are used to mount constant vibration measurement devices onto hydraulic piping system supports or aircraft airframe structures.

[0008] A universal stabilizer is mounted on the fastening module;

[0009] A laser vibration sensor, mounted on a gimbal stabilizer, is used for non-contact collection of real-time vibration data from vibration measurement points on the aircraft's hydraulic lines, and to measure the relative position of the laser vibration sensor to the vibration measurement points on the aircraft's hydraulic lines; and

[0010] A spatial tracking locator, mounted on a gimbal stabilizer, is used to measure the position of a laser vibration sensor.

[0011] On the other hand, the present invention also provides a method for locating abnormal vibration points, comprising the following steps:

[0012] Multiple constant vibration measuring devices are fixed to the aircraft body structure or hydraulic pipeline system support by fastening modules, and multiple vibration measuring points corresponding to the constant vibration measuring devices are set on the hydraulic pipeline.

[0013] Before the aircraft engine is started, the direction of the gimbal stabilizer is adjusted so that the laser vibration sensor is facing the vibration measurement point. The relative position of the laser vibration sensor and the vibration measurement point is transmitted to the system integrated controller. The space tracking positioner transmits the position information of the laser vibration sensor to the system integrated controller, and the system integrated controller calculates the coordinates of the vibration measurement point.

[0014] When the aircraft engine is started, the laser vibration sensor collects real-time vibration data from the aircraft's hydraulic lines and transmits it to the system's integrated controller.

[0015] The system integrated controller identifies abnormal vibration points in the aircraft's hydraulic lines based on real-time vibration data. These abnormal vibration points are vibration measurement points where the vibration data exceeds a preset threshold. The abnormal vibration points are located based on the coordinates of the corresponding vibration measurement points.

[0016] The beneficial effects of this invention are:

[0017] 1. The constant vibration measurement device only needs to be fixed on the aircraft body structure or hydraulic pipeline system bracket to collect data. It does not need to directly contact the vibration measurement point of the hydraulic pipeline, thus overcoming the inconvenience of having to directly contact the test device with the hydraulic pipeline in the past.

[0018] 2. The universal stabilizer in the constant-stability vibration measurement device can ensure that the laser vibration sensor and hydraulic pipeline remain relatively stable under high-frequency vibration of the aircraft engine ground start-up piping system, so as to smoothly collect vibration data and improve the accuracy and reliability of vibration data acquisition.

[0019] 3. By using a constant vibration measurement device, it is possible to accurately locate abnormal vibration points in aircraft hydraulic lines. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of the constant vibration measuring device according to an embodiment of the present invention.

[0021] Figure 2 This is a schematic diagram showing the relationship between the constant vibration measurement device, the system integrated controller, and the display in an embodiment of the present invention.

[0022] In the diagram: 1. Fastening bracket; 2. Static fixed plate; 3. Dynamic fixed plate; 4. Strong magnetic material; 5. Universal stabilizer; 6. Elastic claw; 7. 3D laser scanning probe; 8. Laser vibration sensor; 9. Spatial tracking locator; 10. Display; 11. Remote wireless communication module; 12. Wireless communication and data processing module; 13. System integrated controller. Detailed Implementation

[0023] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. Any specific values ​​in all examples shown and discussed herein should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. Example 1

[0025] like Figure 1 As shown, this embodiment proposes a constant-stability vibration measurement device for aircraft hydraulic lines, comprising:

[0026] The fastening module includes a fastening bracket 1, a static fixed plate 2, and a dynamic fixed plate 3. The fastening bracket 1 has cross-shaped through holes at both ends, through which the constant vibration measuring device is installed on the hydraulic pipeline system bracket or the aircraft body structure. The fastening bracket 1 can also be configured as a rectangular structure with both ends horizontal, an I-shaped concave structure with both ends vertical, or an irregular structure with one end horizontal and one end vertical, depending on the test conditions.

[0027] The universal stabilizer 5 is installed on the bottom of the moving fixed plate 3 of the fastening module;

[0028] A laser vibration sensor 8, mounted on a gimbal stabilizer 5 via elastic claws 6, is used for non-contact measurement of real-time vibration data at vibration measurement points on the aircraft's hydraulic lines. Specifically, this includes vibration stress and acceleration, and the relative position of the laser vibration sensor 8 to the vibration measurement points on the aircraft's hydraulic lines is measured.

[0029] The spatial tracking locator 9 is mounted on the universal stabilizer 5 via the elastic claw 6 and is used to measure the position of the laser vibration sensor 8.

[0030] In some implementations, the gimbal stabilizer 5 is also equipped with a three-dimensional laser scanning probe 7 via an elastic claw 6 for scanning the aircraft's hydraulic lines.

[0031] In some embodiments, the conical pin connection mounts the constant vibration measuring device onto the hydraulic pipeline system bracket or aircraft fuselage structure, achieving a detachable connection; the fastening bracket 1 of the fastening module has a circular through hole in the middle, and the top center of the static fixed plate 2 has a threaded hole, allowing the fastening bracket 1 to rotate on the static fixed plate 2. After adjusting the position, the fastening bracket 1 and the static fixed plate 2 are fixed together by bolts passing through the circular through hole and the threaded hole, achieving a detachable connection; the connecting surfaces of the static fixed plate 2 and the moving fixed plate 3 are respectively provided with strong magnetic material 4, and the static fixed plate 2 and the moving fixed plate 3 are magnetically attracted together, achieving a detachable connection and relative rotation between the fastening module and the universal stabilizer 5.

[0032] In some embodiments, multiple sets of omnidirectional stabilizers 5 are provided. The bottom end of the omnidirectional stabilizer 5 is provided with an elastic claw 6. The elastic claw 6 is U-shaped. When in use, it holds the clamped item. After use, it pulls out the clamped item, so that the omnidirectional stabilizer 5 can be detachably connected to the laser vibration sensor 8, the spatial tracking locator 9, and the three-dimensional laser scanning probe 7.

[0033] Multiple detachable connections enable convenient maintenance, improve system disassembly and assembly efficiency, and facilitate adaptation to various complex hydraulic pipeline system operating conditions. Example 2

[0034] This embodiment proposes a method for locating abnormal vibration points in aircraft hydraulic lines, using the constant vibration measurement device described in Embodiment 1, and includes the following steps:

[0035] Multiple constant vibration measuring devices are fixed to the aircraft body structure or hydraulic pipeline system support by fastening modules, and multiple vibration measuring points corresponding to the constant vibration measuring devices are set on the hydraulic pipeline.

[0036] Before the aircraft engine is started, the direction of the gimbal stabilizer 5 is adjusted so that the laser vibration sensor 8 is facing the vibration measurement point. The relative position of the laser vibration sensor 8 and the vibration measurement point is transmitted to the system integrated controller 13. The space tracking locator 9 transmits the position information of the laser vibration sensor 8 to the system integrated controller 13. The system integrated controller 13 calculates the coordinates of the vibration measurement point.

[0037] When the aircraft engine is started and driven, during the entire process from idle to afterburner, the laser vibration sensor 8 collects real-time vibration data of the aircraft hydraulic lines, namely vibration stress and vibration acceleration, and transmits it to the system integrated controller 13.

[0038] The system integrated controller 13 determines the abnormal vibration points of the aircraft hydraulic lines based on real-time vibration data. The abnormal vibration points are vibration measurement points where the vibration data exceeds a preset threshold. The abnormal vibration points are located based on the coordinates of the corresponding vibration measurement points. The preset threshold is set as an empirical value.

[0039] The system integrated controller 13 is preferably a PLC controller.

[0040] In some implementations, before the vibration test begins, the display 10 and the system integrated controller 13 are placed on one side of the aircraft to be tested, about (3-5) meters away from the fuselage, and the display 10 and the system integrated controller 13 are connected together by a dedicated cable.

[0041] The constant vibration measurement device is also equipped with a three-dimensional laser scanning probe 7. Before adjusting the laser vibration sensor 8 toward the vibration measurement point, the universal stabilizer is adjusted so that the three-dimensional laser scanning probe 7 scans the aircraft hydraulic pipeline to be tested for vibration and transmits the scan data to the system integrated controller 13. The system integrated controller 13 performs three-dimensional modeling of the aircraft hydraulic pipeline to obtain a three-dimensional model of the aircraft hydraulic pipeline.

[0042] The system integrated controller 13 maps the vibration measurement points onto the three-dimensional model of the aircraft hydraulic lines and performs high-brightness calibration; it distributes the real-time measured vibration values ​​on the aircraft hydraulic lines in the form of cloud map distribution, generates vibration curves of vibration values ​​at different time points and measurement point position coordinates, and displays them on the display 10 in real time.

[0043] Based on the distribution cloud map of vibration values ​​on the hydraulic pipeline and the vibration curve of vibration value-measuring point position coordinates at different time points, the system integrated controller 13 calculates the abnormal vibration points of the hydraulic pipeline of the test aircraft and the direction of the abnormal vibration. The system integrated controller 13 quickly highlights the coordinates of the measuring point corresponding to the abnormal vibration point and the direction of the abnormal vibration on the three-dimensional model and displays it on the display 10 in real time.

[0044] The coordinates of abnormal vibration points are visualized on a 3D model, enabling staff without a professional background to intuitively understand the vibration of the pipeline system and quickly troubleshoot abnormal vibration faults.

[0045] After the vibration test is completed, shut down the aircraft engine and all power switches. Remove the constant vibration measurement device from the aircraft body structure or hydraulic pipeline system support. Remove the three-dimensional laser scanning probe 7, laser vibration sensor 8 and space tracking locator 9 fixed by the elastic claw 6, and restore all components to their original positions.

[0046] In some implementations, the system integrated controller 13 is wirelessly connected to the constant vibration measurement device. Specifically, the data collected by the three-dimensional laser scanning probe 7, the laser vibration sensor 8, and the spatial tracking locator 9 are transmitted to the remote wireless communication module 11 installed in the display 10 via the wireless communication and data processing module 12. The wireless communication and data processing module 12 and the remote wireless communication module 11 are connected via Bluetooth. The display 10 and the system integrated controller 13 are connected via a cable.

[0047] Multiple constant vibration measurement devices communicate with each other through the wireless communication and data processing module 12 to achieve data interconnection, and each constant vibration measurement device is connected to the remote wireless communication module 11 via Bluetooth to realize rapid, wireless vibration testing of various complex hydraulic pipeline systems on the aircraft.

[0048] Wireless connectivity facilitates data transmission and allows staff to observe the test without having to approach the testing equipment, thus preventing injuries to staff during testing.

Claims

1. A constant-steady vibration measuring device for aircraft hydraulic lines, characterized in that, include: Fastening modules are used to mount constant vibration measurement devices onto hydraulic piping system supports or aircraft airframe structures. A universal stabilizer is mounted on the fastening module; A laser vibration sensor, mounted on a gimbal stabilizer, is used for non-contact collection of real-time vibration data from vibration measurement points on the aircraft's hydraulic lines, and to measure the relative position of the laser vibration sensor to the vibration measurement points on the aircraft's hydraulic lines; and A spatial tracking locator, mounted on a gimbal stabilizer, is used to measure the position of a laser vibration sensor.

2. The constant vibration measuring device for aircraft hydraulic lines as described in claim 1, characterized in that: The gimbal stabilizer is also equipped with a three-dimensional laser scanning probe for scanning the aircraft's hydraulic lines.

3. The constant vibration measuring device for aircraft hydraulic lines as described in claim 1, characterized in that: The fastening module is detachably connected to the aircraft body structure or hydraulic pipeline system bracket, and is detachably connected to the universal stabilizer; the fastening module and the universal stabilizer rotate relative to each other.

4. The constant vibration measuring device for aircraft hydraulic lines as described in claim 2, characterized in that: Multiple sets of omnidirectional stabilizers are provided, and the bottom of each omnidirectional stabilizer is equipped with an elastic claw. The omnidirectional stabilizer is detachably connected to the laser vibration sensor, the spatial tracking locator, and the three-dimensional laser scanning probe through the elastic claw.

5. A method for locating abnormal vibration points using the constant-steady vibration measuring device according to claim 1, characterized in that, Includes the following steps: Multiple constant vibration measuring devices are fixed to the aircraft body structure or hydraulic pipeline system support by fastening modules, and multiple vibration measuring points corresponding to the constant vibration measuring devices are set on the hydraulic pipeline. Before the aircraft engine is started, the direction of the gimbal stabilizer is adjusted so that the laser vibration sensor is facing the vibration measurement point. The relative position of the laser vibration sensor and the vibration measurement point is transmitted to the system integrated controller. The space tracking positioner transmits the position information of the laser vibration sensor to the system integrated controller, and the system integrated controller calculates the coordinates of the vibration measurement point. When the aircraft engine is started, the laser vibration sensor collects real-time vibration data from the aircraft's hydraulic lines and transmits it to the system's integrated controller. The system integrated controller identifies abnormal vibration points in the aircraft's hydraulic lines based on real-time vibration data. These abnormal vibration points are vibration measurement points where the vibration data exceeds a preset threshold. The abnormal vibration points are located based on the coordinates of the corresponding vibration measurement points.

6. The method for locating abnormal vibration points as described in claim 5, characterized in that: The constant vibration measurement device is also equipped with a three-dimensional laser scanning probe. Before adjusting the laser vibration sensor toward the vibration measurement point, the universal stabilizer is adjusted so that the three-dimensional laser scanning probe scans the aircraft hydraulic pipeline to be tested for vibration. The scanned data is transmitted to the system integrated controller, which performs three-dimensional modeling of the aircraft hydraulic pipeline to obtain a three-dimensional model of the aircraft hydraulic pipeline. The system's integrated controller marks the coordinates of the vibration measurement points corresponding to the abnormal vibration points on the three-dimensional model and displays them on the monitor in real time.

7. The method for locating abnormal vibration points in aircraft hydraulic lines as described in claim 5 or 6, characterized in that: The system's integrated controller is wirelessly connected to the constant vibration measurement device.

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