Airplane wheel nut self-locking force detection device

Abstract

The utility model relates to the field of aircraft test and maintenance equipment, in particular to an aircraft wheel nut self-locking force detection device which comprises a main body, a placement assembly, a wrench assembly, a driving part and a torque sensor. The placing assembly is arranged on the main body and is used for mounting a stud; the spanner assembly and the placing assembly are correspondingly arranged, the spanner assembly is movably arranged on the main body and can be close to or away from the placing assembly, and the spanner assembly is used for screwing or unscrewing a nut located on the stud; the driving piece is arranged on the main body and is in transmission connection with the wrench assembly; the torque sensor is in transmission connection with the wrench assembly and used for detecting the torque of the wrench assembly. According to the airplane wheel nut self-locking force detection device, the nut can be automatically tested, so that the test efficiency is improved.

Description

Technical Field

[0001] This application relates to the field of aircraft testing and maintenance equipment, and in particular to a device for detecting the self-locking force of aircraft wheel nuts. Background Technology

[0002] Aircraft wheel nuts are used to securely fasten aircraft wheels to the landing gear axles, ensuring a stable connection between the wheels and the landing gear. Abnormal self-locking force in aircraft wheel nuts can cause self-locking failure, leading to wheel bolt breakage and affecting landing gear operation, thus compromising flight safety. Therefore, self-locking force testing of aircraft wheel nuts is necessary.

[0003] In related technologies, maintenance personnel need to tighten the nuts and then test the nut's release torque using a torque gauge. However, this testing method is inefficient, and the labor costs are high when testing a large number of nuts. Utility Model Content

[0004] The purpose of this application is to at least address the problem of low testing efficiency in related technologies. This purpose is achieved through the following means:

[0005] This application discloses a device for detecting the self-locking force of an aircraft wheel nut, comprising a main body, a placement assembly, a wrench assembly, a drive component, and a torque sensor. The placement assembly is disposed on the main body and is used to install a stud. The wrench assembly is correspondingly disposed on the placement assembly and is movably disposed on the main body, capable of approaching or moving away from the placement assembly. The wrench assembly is used to tighten or loosen the nut located on the stud. The drive component is disposed on the main body and is pulsatorically connected to the wrench assembly. The torque sensor is pulsatorically connected to the wrench assembly and is used to detect the torque of the wrench assembly.

[0006] The self-locking force testing device for aircraft wheel nuts disclosed in this application can perform automated testing of nuts, thereby improving testing efficiency.

[0007] In some embodiments, the placement assembly includes a turntable and a first motor. The main body includes a base, the turntable is rotatably disposed on the base and is drively connected to the first motor, and the turntable is provided with a plurality of mounting holes for mounting the studs, the plurality of mounting holes being arranged sequentially along the circumference of the turntable.

[0008] In some embodiments, the wrench assembly includes a second motor and a torque wrench, one end of the torque sensor is drivenly connected to the second motor, the other end of the torque sensor is drivenly connected to the torque wrench, and the torque wrench is correspondingly disposed with one of the plurality of mounting holes and is used to tighten or loosen the nut located on the stud.

[0009] In some embodiments, the main body further includes a mounting bracket, the wrench assembly includes a lifting platform, the lifting platform is movably disposed relative to the mounting bracket and can move closer to or further away from the mounting bracket, the driving component is a telescopic cylinder, one end of the telescopic cylinder is connected to the mounting bracket, the other end of the telescopic cylinder is connected to the lifting platform and can drive the mounting bracket to move, and the second motor is disposed on the lifting platform.

[0010] In some embodiments, the main body further includes a guide rod connected to the mounting bracket, and the lifting platform is movably connected to the guide rod along its extension direction.

[0011] In some embodiments, the main body further includes a housing connected to the base, the housing defining a mounting cavity forming an opening, the guide rod, the lifting platform, the first motor and the torque sensor being located within the mounting cavity, the mounting bracket being connected to the housing and covering the mounting cavity, the torque wrench being inserted through the mounting bracket, and at least a portion of the torque wrench being located outside the mounting cavity.

[0012] In some embodiments, the mounting cavity is provided with a mounting plate, which is connected to the housing. The aircraft wheel nut self-locking force detection device further includes a controller, which is mounted on the mounting plate. The guide rod, the lifting platform, the first motor, and the torque sensor are all located on the side of the mounting plate away from the controller. The first motor, the second motor, and the torque sensor are all electrically connected to the controller.

[0013] In some embodiments, multiple second motors, torque wrenches, and torque sensors are provided. The multiple second motors are evenly spaced along the circumferential direction of the turntable, and the multiple torque sensors are arranged in a one-to-one correspondence with the multiple second motors. The multiple torque wrenches are arranged in a one-to-one correspondence with the multiple torque sensors.

[0014] In some embodiments, the turntable includes a turntable body and a plurality of mounting seats, with a plurality of mounting holes corresponding one-to-one with the mounting seats. A portion of each mounting seat is mounted in the turntable body, and another portion of each mounting seat extends out of the turntable body and is located on the side of the turntable body closer to the wrench assembly.

[0015] In some embodiments, the turntable further includes a rotating shaft rotatably disposed on the base, the first motor is installed inside the base, the turntable body is disposed outside the base, a portion of the rotating shaft is located inside the base and is connected to the first motor for transmission, and another portion of the rotating shaft is located outside the base and is connected to the turntable body. Attached Figure Description

[0016] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. Wherein:

[0017] Figure 1 This is a schematic diagram of the aircraft wheel nut self-locking force detection device according to an embodiment of this application;

[0018] Figure 2 This is a front view of a portion of the structure of the aircraft wheel nut self-locking force detection device according to an embodiment of this application;

[0019] Figure 3 This is a side view of a portion of the structure of the aircraft wheel nut self-locking force detection device according to an embodiment of this application.

[0020] The labels in the attached diagram are as follows:

[0021] 100. Aircraft wheel nut self-locking force testing device;

[0022] 1. Main body; 11. Base; 12. Mounting bracket; 13. Guide rod; 14. Outer shell; 141. Mounting cavity; 142. Mounting plate;

[0023] 2. Component placement; 21. Turntable; 211. Turntable body; 212. Mounting base; 22. First motor;

[0024] 3. Wrench assembly; 31. Second motor; 32. Torque wrench; 33. Lifting platform; 34. Intermediate connecting piece;

[0025] 4. Driving components; 41. Telescopic cylinder;

[0026] 5. Torque sensor;

[0027] 6. Controller. Detailed Implementation

[0028] Exemplary embodiments of this application will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of this application are shown in the drawings, it should be understood that this application may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of this application and to fully convey the scope of this application to those skilled in the art.

[0029] It should be understood that the terminology used herein is for the purpose of describing particular exemplary embodiments only and is not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “described” as used herein may also include the plural forms. The terms “comprising,” “including,” “containing,” and “having” are inclusive and therefore indicate the presence of the stated features, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, elements, components, and / or combinations thereof. The method steps, processes, and operations described herein are not construed as requiring them to be performed in a particular order described or illustrated unless the order of performance is explicitly indicated. It should also be understood that additional or alternative steps may be used.

[0030] Although terms such as first, second, third, etc., may be used in this document to describe multiple elements, components, regions, layers, and / or segments, these elements, components, regions, layers, and / or segments should not be limited by these terms. These terms may be used only to distinguish one element, component, region, layer, or segment from another. Unless the context clearly indicates otherwise, terms such as "first," "second," and other numerical terms used herein do not imply order or sequence. Therefore, the first element, component, region, layer, or segment discussed below may be referred to as the second element, component, region, layer, or segment without departing from the teachings of the exemplary embodiments. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0031] For ease of description, spatial relative terms may be used in the text to describe the relationship of one element or feature relative to another element or feature, as shown in the figure. These relative terms include, for example, "inside," "outside," "middle," "outer," "below," "below," "above," "over," etc. Such spatial relative terms are intended to include different orientations of the device in use or operation, other than those depicted in the figure. For example, if the device in the figure rotates, then an element described as "below other elements or features" or "below other elements or features" will subsequently be oriented as "above other elements or features" or "above other elements or features." Therefore, the example term "below" can include both upper and lower orientations. The device may be otherwise oriented (rotated 90 degrees or in other directions), and the spatial relative descriptors used in the text will be interpreted accordingly.

[0032] In the description of the application, the technical terms "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "circumferential", "height direction", "first direction", "second direction", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed, operated or used in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of this application.

[0033] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between components; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0034] Aircraft wheel nuts are used to securely fasten aircraft wheels to the landing gear axles, ensuring a stable connection between the wheels and the landing gear. Abnormal self-locking force in aircraft wheel nuts can cause self-locking failure, leading to wheel bolt breakage and affecting landing gear operation, thus compromising flight safety. Therefore, self-locking force testing of aircraft wheel nuts is necessary.

[0035] In related technologies, maintenance personnel need to tighten the nuts and then test the nut's release torque using a torque gauge. However, this testing method is inefficient, and the labor costs are high when testing a large number of nuts.

[0036] To address at least the issue of low testing efficiency in related technologies, embodiments of this application propose an aircraft wheel nut self-locking force testing device 100, which can automate the testing of nuts, thereby improving testing efficiency.

[0037] The self-locking force detection device 100 for aircraft wheel nuts according to an embodiment of this application is described below with reference to the accompanying drawings.

[0038] Combination Figure 1 and Figure 2As shown, this application proposes an aircraft wheel nut self-locking force detection device 100, including a main body 1, a placement assembly 2, a wrench assembly 3, a drive component 4, and a torque sensor 5. The placement assembly 2 is disposed on the main body 1 and is used to install studs; the wrench assembly 3 is correspondingly disposed to the placement assembly 2, and is movably disposed on the main body 1, and can move closer to or away from the placement assembly 2, and is used to tighten or loosen the nut located on the stud; the drive component 4 is disposed on the main body 1 and is drively connected to the wrench assembly 3; the torque sensor 5 is drively connected to the wrench assembly 3 and is used to detect the torque of the wrench assembly 3.

[0039] When performing a self-test on the aircraft wheel nut self-locking force detection device 100 of this embodiment, the stud is installed on the placement assembly 2, and the nut is pre-installed on the stud. The drive wrench assembly 3 is brought close to the placement assembly 2, and the wrench assembly 3 is tightened on the stud. The drive wrench assembly 3 is moved away from the placement assembly 2 to avoid obstructing the view of the nut, and the nut is observed to see if it is tightened properly. The drive wrench assembly 3 is brought close to the placement assembly 2, and the nut is loosened. If the nut is not tightened properly, the number of turns of the wrench assembly 3 is adjusted, and the self-test steps are repeated until the wrench assembly 3 can tighten the nut properly.

[0040] In this embodiment, the aircraft wheel nut self-locking force detection device 100 detects the self-locking force of the nut by installing the stud in the placement assembly 2 and pre-installing the nut on the stud. The drive wrench assembly 3 is brought close to the placement assembly 2 and tightens the nut on the stud. The torque of tightening the nut is obtained by the torque sensor 5, and the self-locking force of the nut is determined based on the torque. Therefore, the aircraft wheel nut self-locking force detection device 100 enables automated testing of nuts, thereby improving testing efficiency.

[0041] Combination Figure 2 and Figure 3 As shown, in some embodiments, the placement component 2 includes a turntable 21 and a first motor 22, the main body 1 includes a base 11, the turntable 21 is rotatably disposed on the base 11 and is connected to the first motor 22 in a transmission manner, the turntable 21 is provided with a plurality of mounting holes for mounting studs, and the plurality of mounting holes are arranged sequentially along the circumference of the turntable 21.

[0042] The turntable 21 has multiple mounting holes for installing studs, arranged sequentially along its circumference. This means that multiple studs can be mounted on the turntable 21. After the nut on one stud has been inspected, the first motor 22 rotates the turntable 21, causing the stud to rotate to the position corresponding to the wrench assembly 3, allowing the wrench assembly 3 to inspect the next nut. This increases the speed of nut switching, thereby further improving testing efficiency.

[0043] Combination Figure 2and Figure 3 As shown, in some embodiments, the wrench assembly 3 includes a second motor 31 and a torque wrench 32. One end of the torque sensor 5 is connected to the second motor 31, and the other end of the torque sensor 5 is connected to the torque wrench 32. The torque wrench 32 is correspondingly set with one of a plurality of mounting holes and is used to tighten or loosen the nut located on the stud.

[0044] The second motor 31, acting as a power source, provides stable and continuous power to the torque wrench 32, enabling it to tighten or loosen nuts. One end of the torque sensor 5 is connected to the second motor 31, and the other end is connected to the torque wrench 32, ensuring smooth power transmission from the second motor 31 to the torque wrench 32. This also provides the conditions for the torque sensor 5 to detect torque, allowing it to directly detect the torque of the torque wrench 32. This results in a compact structure and efficient transmission between the torque sensor 5, the second motor 31, and the torque wrench 32.

[0045] The torque sensor 5 can be a strain gauge torque sensor, a magnetoelectric torque sensor, a photoelectric torque sensor, a piezoelectric torque sensor, a Hall effect torque sensor, etc.

[0046] Combination Figure 2 and Figure 3 As shown, in some embodiments, the main body 1 further includes a mounting frame 12, the wrench assembly 3 includes a lifting platform 33, the lifting platform 33 is movably arranged relative to the mounting frame 12 and can move closer to or away from the mounting frame 12, the driving component 4 is a telescopic cylinder 41, one end of the telescopic cylinder 41 is connected to the mounting frame 12, the other end of the telescopic cylinder 41 is connected to the lifting platform 33 and can drive the mounting frame 12 to move, and the second motor 31 is provided on the lifting platform 33.

[0047] The lifting platform 33 is movable relative to the mounting frame 12 and can move closer to or away from the mounting frame 12, so that the second motor 31 provided on the lifting platform 33 can generate movement closer to or away from the turntable 21, thereby enabling the torque wrench 32 to generate movement closer to or away from the turntable 21.

[0048] One end of the telescopic cylinder 41 is connected to the mounting bracket 12, and the other end of the telescopic cylinder 41 is connected to the lifting platform 33, so that a stable connection is formed between the telescopic cylinder 41, the mounting bracket 12 and the lifting platform 33, thereby effectively withstanding the external force during the operation and increasing the stability of the wrench assembly 3.

[0049] As some examples, telescopic cylinder 41 is a pneumatic cylinder.

[0050] As another example, telescopic cylinder 41 is a hydraulic cylinder.

[0051] In other embodiments, the drive unit 4 is a third motor located on the mounting frame 12, the lifting platform 33 is connected to the rack, and the third motor is connected to the rack via a gear set to drive the lifting platform 33 to move closer to or away from the mounting frame 12.

[0052] The continuous and stable meshing of the gears and racks effectively transmits the power of the motor to the lifting platform 33, reducing vibration and impact during movement, thereby improving the stability of the torque wrench 32 during movement.

[0053] Combination Figure 2 and Figure 3 As shown, in some alternative embodiments, the lifting platform 33 is located on the side of the mounting bracket 12 away from the turntable 21.

[0054] The lifting platform 33 is located on the side of the mounting bracket 12 away from the turntable 21, providing ample installation space for the second motor 31, torque sensor 5 and torque wrench 32.

[0055] Combination Figure 2 and Figure 3 As shown, in some alternative embodiments, the lifting platform 33 is located on the side of the mounting frame 12 closer to the turntable 21.

[0056] The lifting platform 33 is located on the side of the mounting bracket 12 closer to the turntable 21, bringing the torque wrench 32 mounted on the lifting platform 33 closer to the turntable 21. This reduces the travel distance of the torque wrench 32 when tightening or loosening nuts on studs, improving testing efficiency. Furthermore, the location of the lifting platform 33 on the side of the mounting bracket 12 closer to the turntable 21 makes the overall structure of the aircraft wheel nut self-locking force testing device 100 of this embodiment more compact.

[0057] Combination Figure 2 and Figure 3 As shown, in some embodiments, the main body 1 further includes a guide rod 13, which is connected to the mounting frame 12. Along the extension direction of the guide rod 13, the lifting platform 33 is movably connected to the guide rod 13.

[0058] The guide rod 13 is used to guide the movement of the lifting platform 33. The guide rod 13 can reduce the probability of lateral deviation or wobbling of the lifting platform 33 during movement, thereby improving the accuracy of tightening or loosening the nut and making the movement of the lifting platform 33 more precise. This makes the movement of the torque wrench 32 more precise, and thus the torque wrench 32 can be accurately aligned with the stud of the placement component 2, thereby improving the accuracy and consistency of the torque wrench 32 in detecting the nut.

[0059] The guide rod 13 provides partial constraint to the lifting platform 33, which reduces the probability of deformation of the lifting platform 33 under stress. This helps the lifting platform 33 maintain its shape and dimensional accuracy, ensures the matching accuracy of the lifting platform 33 with other components, and thus guarantees the normal operation of the equipment.

[0060] Combination Figure 2 and Figure 3 As shown, in some optional embodiments, there are multiple guide rods 13, which are spaced apart circumferentially along the lifting platform 33.

[0061] Multiple guide rods 13 are distributed circumferentially along the lifting platform 33, which can more evenly distribute the external forces on the lifting platform 33 during movement, thereby reducing the force on each guide rod 13 and increasing the structural stability of the aircraft wheel nut self-locking force detection device 100 of this embodiment. When the lifting platform 33 is subjected to eccentric load, the multiple guide rods 13 are distributed circumferentially along the lifting platform 33, thereby reducing the load on each guide rod 13 and further increasing the structural stability of the aircraft wheel nut self-locking force detection device 100 of this embodiment.

[0062] Even if one of the multiple guide rods 13 is damaged, the other guide rods 13 can still guide the lifting platform 33, thereby improving the reliability of the aircraft wheel nut self-locking force detection device 100 in this embodiment.

[0063] Combination Figure 2 and Figure 3 As shown, in some optional embodiments, the wrench assembly 3 further includes an intermediate connector 34, which is movably sleeved on the guide rod 13 and embedded in the lifting platform 33.

[0064] The intermediate connector 34 is movably sleeved on the guide rod 13, and can fit tightly against the guide rod 13 to provide precise guidance for the movement of the lifting platform 33.

[0065] The intermediate connector 34 is embedded in the lifting platform 33 and can fit tightly against the lifting platform 33, thereby transmitting the external force received by the lifting platform 33 to the lifting platform 33 in a timely manner.

[0066] Combination Figure 2 and Figure 3 As shown, in some embodiments, the main body 1 further includes a housing 14, which is connected to the base 11. The housing 14 defines a mounting cavity 141 forming an opening. The guide rod 13, the lifting platform 33, the first motor 22, and the torque sensor 5 are all located inside the mounting cavity 141. The mounting bracket 12 is connected to the housing 14 and covers the mounting cavity 141. The torque wrench 32 is inserted through the mounting bracket 12, and at least a portion of the torque wrench 32 is located outside the mounting cavity 141.

[0067] The outer casing 14 provides protection for the guide rod 13, the lifting platform 33, the first motor 22, and the torque sensor 5. The guide rod 13, the lifting platform 33, the first motor 22, and the torque sensor 5 are all located within the mounting cavity 141. The mounting bracket 12 is connected to the outer casing 14 and seals the mounting cavity 141, isolating solid particles, liquids, or other debris. This reduces the probability of debris affecting the guide rod 13, the lifting platform 33, the first motor 22, and the torque sensor 5, thereby improving the stability and reliability of the aircraft wheel nut self-locking force detection device 100 in this embodiment.

[0068] like Figure 3 As shown, in some embodiments, a mounting plate 142 is provided inside the mounting cavity 141. The mounting plate 142 is connected to the outer shell 14. The aircraft wheel nut self-locking force detection device 100 also includes a controller 6. The controller 6 is mounted on the mounting plate 142. The guide rod 13, the lifting platform 33, the first motor 22 and the torque sensor 5 are all located on the side of the mounting plate 142 away from the controller 6. The first motor 22, the second motor 31 and the torque sensor 5 are all electrically connected to the controller 6.

[0069] By arranging the guide rod 13, lifting platform 33, first motor 22, and torque sensor 5 on the side of mounting plate 142 away from controller 6, a reasonable partitioning of mounting cavity 141 is achieved. This allows for full utilization of the space within mounting cavity 141, increasing its usability, and preventing the guide rod 13, lifting platform 33, first motor 22, and torque sensor 5 from interfering with or colliding with controller 6. Therefore, arranging the guide rod 13, lifting platform 33, first motor 22, and torque sensor 5 on the side of mounting plate 142 away from controller 6 enables the guide rod 13, lifting platform 33, first motor 22, torque sensor 5, and controller 6 to operate efficiently within a limited space.

[0070] Mounting plate 142 is connected to housing 14, providing a stable mounting base for controller 6. Moreover, since mounting plate 142 is connected to housing 14, it can provide a certain degree of support for housing 14, thereby increasing the strength of housing 14.

[0071] like Figure 2 As shown, in some embodiments, multiple second motors 31, torque wrenches 32, and torque sensors 5 are provided. Along the circumferential direction of the turntable 21, multiple second motors 31 are evenly spaced, and multiple torque sensors 5 are arranged in a one-to-one correspondence with the multiple second motors 31. Multiple torque wrenches 32 are also arranged in a one-to-one correspondence with the multiple torque sensors 5. Therefore, it is possible to simultaneously tighten or loosen nuts on multiple studs and detect torque synchronously, thereby improving detection efficiency and shortening detection time.

[0072] Combination Figure 2 and Figure 3 As shown, in some embodiments, the turntable 21 includes a turntable body 211 and a plurality of mounting seats 212, with a plurality of mounting holes corresponding to each mounting seat 212. A portion of each mounting seat 212 is installed inside the turntable body 211, and another portion of each mounting seat 212 extends out of the turntable body 211 and is located on the side of the turntable body 211 near the wrench assembly 3.

[0073] A portion of the mounting base 212 extends out of the turntable body 211 and approaches the wrench assembly 3, making the mounting hole on the mounting base 212 protrude. The mounting hole is not obstructed by the turntable body 211, allowing the operator to see the position of the mounting hole more clearly. When inserting the stud, the line of sight is unobstructed, making it easier to align the mounting hole, thereby improving the accuracy and convenience of stud installation.

[0074] Combination Figure 2 and Figure 3 As shown, in some embodiments, the turntable 21 further includes a rotating shaft rotatably disposed on the base 11, the first motor 22 is installed inside the base 11, the turntable 21 body is disposed outside the base 11, a part of the rotating shaft is located inside the base 11 and is connected to the first motor 22 for transmission, and another part of the rotating shaft is located outside the base 11 and is connected to the turntable 21 body.

[0075] The rotating shaft provides support for the turntable body 211, and the first motor 22 provides support for the rotating shaft. The first motor 22 is mounted on the base 11, and the base 11 provides support for the first motor 22, thereby improving the stability of the first motor 22 and the turntable body 211 during operation.

[0076] The above description is merely a preferred embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A device for detecting the self-locking force of aircraft wheel nuts, characterized in that, include: main body; A placement component is provided on the main body, and the placement component is used to install studs; A wrench assembly is provided corresponding to the placement assembly. The wrench assembly is movably disposed on the main body and can move closer to or further away from the placement assembly. The wrench assembly is used to tighten or loosen the nut located on the stud. A driving component is disposed on the main body, and the driving component is connected to the wrench assembly in a transmission manner; A torque sensor is connected to the wrench assembly and is used to detect the torque of the wrench assembly.

2. The aircraft wheel nut self-locking force detection device according to claim 1, characterized in that, The placement assembly includes a turntable and a first motor. The main body includes a base. The turntable is rotatably disposed on the base and is connected to the first motor for transmission. The turntable is provided with a plurality of mounting holes for mounting the studs. The plurality of mounting holes are arranged sequentially along the circumference of the turntable.

3. The aircraft wheel nut self-locking force detection device according to claim 2, characterized in that, The wrench assembly includes a second motor and a torque wrench. One end of the torque sensor is connected to the second motor, and the other end of the torque sensor is connected to the torque wrench. The torque wrench is configured to correspond to one of the plurality of mounting holes and is used to tighten or loosen the nut located on the stud.

4. The aircraft wheel nut self-locking force detection device according to claim 3, characterized in that, The main body also includes a mounting frame, and the wrench assembly includes a lifting platform. The lifting platform is movably arranged relative to the mounting frame and can move closer to or further away from the mounting frame. The driving component is a telescopic cylinder. One end of the telescopic cylinder is connected to the mounting frame, and the other end of the telescopic cylinder is connected to the lifting platform and can drive the mounting frame to move. The second motor is located on the lifting platform.

5. The aircraft wheel nut self-locking force detection device according to claim 4, characterized in that, The main body also includes a guide rod, which is connected to the mounting frame. Along the extension direction of the guide rod, the lifting platform is movably connected to the guide rod.

6. The aircraft wheel nut self-locking force detection device according to claim 5, characterized in that, The main body also includes a housing, which is connected to the base. The housing defines an opening in the mounting cavity. The guide rod, the lifting platform, the first motor, and the torque sensor are all located in the mounting cavity. The mounting bracket is connected to the housing and covers the mounting cavity. The torque wrench is inserted through the mounting bracket, and at least a portion of the torque wrench is located outside the mounting cavity.

7. The aircraft wheel nut self-locking force detection device according to claim 6, characterized in that, The mounting cavity is provided with a mounting plate, which is connected to the outer shell. The aircraft wheel nut self-locking force detection device also includes a controller, which is mounted on the mounting plate. The guide rod, the lifting platform, the first motor and the torque sensor are all located on the side of the mounting plate away from the controller. The first motor, the second motor and the torque sensor are all electrically connected to the controller.

8. The aircraft wheel nut self-locking force detection device according to any one of claims 3 to 7, characterized in that, Multiple second motors, torque wrenches, and torque sensors are provided. Multiple second motors are evenly spaced along the circumferential direction of the turntable, and multiple torque sensors are provided in one-to-one correspondence with multiple second motors. Multiple torque wrenches are provided in one-to-one correspondence with multiple torque sensors.

9. The aircraft wheel nut self-locking force detection device according to any one of claims 2 to 7, characterized in that, The turntable includes a turntable body and multiple mounting seats. Multiple mounting holes are provided one-to-one with each mounting seat. A portion of each mounting seat is installed in the turntable body, and another portion of each mounting seat extends out of the turntable body and is located on the side of the turntable body near the wrench assembly.

10. The aircraft wheel nut self-locking force detection device according to claim 9, characterized in that, The turntable also includes a rotating shaft rotatably disposed on the base. The first motor is installed inside the base, and the turntable body is disposed outside the base. A portion of the rotating shaft is located inside the base and is connected to the first motor for transmission, while another portion of the rotating shaft is located outside the base and is connected to the turntable body.

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