Aircraft front wheel steering measuring device

Abstract

The utility model discloses an aircraft front wheel steering measuring device, and relates to the technical field of aircrafts. One end of the angle measuring mechanism sleeves the outer wall of the upper section of the undercarriage; the first laser emission equipment is rotationally connected to one side, far away from the upper section of the undercarriage, of the angle measurement mechanism; the upper section of the undercarriage is fixedly connected to the aircraft, and the lower section of the undercarriage is rotationally connected to the upper section of the undercarriage; one end of the undercarriage lower section away from the undercarriage upper section is connected to front wheels of the aircraft; the centering mechanism sleeves the lower section of the undercarriage; the second laser emission equipment is rotationally connected to one side, facing the angle measurement mechanism, of the centering mechanism; one side, deviating from the first laser emission equipment, of the angle measurement mechanism is provided with angle scale lines; the first laser emitting device corresponds to the middle of the angle scale line, and the second laser emitting device corresponds to the angle scale line. According to the method, the accuracy is remarkably improved, the operation is simple, and the working efficiency is improved.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to an aircraft front wheel steering measurement device. Background Technology

[0002] In the aviation industry, landing gear plays a crucial role. It is the core support component of an aircraft during takeoff, landing, and taxiing, ensuring that the aircraft can move safely and stably on the ground. The design of landing gear is a comprehensive consideration, requiring not only strong support capacity and excellent stability, but also taking into account its impact on the overall performance of the aircraft, especially the accuracy and reliability of the steering system.

[0003] As a key component of aircraft ground control, the steering system directly determines the aircraft's agility and safety during taxiing. However, current methods for measuring the nose wheel steering are still relatively traditional, primarily relying on manual angle measurements using measuring instruments. This method is not only time-consuming and labor-intensive, increasing the workload of personnel, but its accuracy and efficiency are also limited by the operator's skills and experience. Utility Model Content

[0004] This application provides an aircraft nose wheel steering measurement device, which solves the problem that the measurement of aircraft nose wheel steering in the prior art relies on manual labor and measuring instruments, resulting in time and labor costs.

[0005] In a first aspect, embodiments of this application provide a nose wheel steering measurement device for an aircraft, including an angle measuring mechanism, a centering mechanism, a first laser emitting device, and a second laser emitting device; one end of the angle measuring mechanism is sleeved on the outer wall of the upper section of the landing gear; the first laser emitting device is rotatably connected to the side of the angle measuring mechanism away from the upper section of the landing gear and is configured to be aligned with the centerline of the aircraft; the upper section of the landing gear is fixedly connected to the aircraft, the lower section of the landing gear is rotatably connected to the upper section of the landing gear, and the end of the lower section of the landing gear away from the upper section of the landing gear is connected to the nose wheel of the aircraft; the centering mechanism is sleeved on the lower section of the landing gear; the second laser emitting device is rotatably connected to the side of the centering mechanism facing the angle measuring mechanism and is configured to be aligned with the center of the nose wheel; an angle scale line is provided on the side of the angle measuring mechanism away from the first laser emitting device; the first laser emitting device corresponds to the center of the angle scale line, and the second laser emitting device corresponds to the angle scale line.

[0006] In one possible implementation, the aircraft nose wheel steering measuring device further includes a first elastic pad and a second elastic pad; the first elastic pad is disposed between the outer wall of the upper section of the landing gear and the angle measuring mechanism; the second elastic pad is disposed between the outer wall of the lower section of the landing gear and the centering mechanism.

[0007] In one possible implementation, the angle measuring mechanism includes a clamping assembly, an arc-shaped frame, and multiple corner frames; the clamping assembly is sleeved on the outer wall of the upper section of the landing gear; the multiple corner frames are spaced apart along the width direction of the clamping assembly; the arc-shaped frame is located on the side of the corner frame away from the clamping assembly, and the angle scale line is provided on the side facing the centering mechanism; the first laser emitting device is rotatably connected to the side of the corner frame away from the arc-shaped frame.

[0008] In one possible implementation, the angle measuring mechanism further includes a fixing frame; the fixing frame is disposed among the plurality of corner frames and is located on the side of the corner frames away from the arc-shaped frame; the first laser emitting device is rotatably connected to the fixing frame on the side away from the corner frames.

[0009] In one possible implementation, the first laser emitting device is rotatably connected in a vertical plane to the side of the angle measuring mechanism away from the upper section of the landing gear; the second laser emitting device is rotatably connected in a vertical plane to the side of the centering mechanism facing the angle measuring mechanism.

[0010] In one possible implementation, the angle measuring mechanism further includes multiple diagonal braces; the two ends of the multiple diagonal braces are respectively connected to the two sides of the corresponding corner frame, and form a triangular structure with the two sides of the corner frame.

[0011] In one possible implementation, the card assembly includes a first bracket, a second bracket, a first pad, and a second pad; the first bracket, the first pad, the second bracket, and the second pad are sequentially connected to form a first closed structure; wherein the middle portion of the first bracket and the middle portion of the second bracket are both first semi-circular arc-shaped structures, and the inner wall of the first semi-circular arc-shaped structure is configured to fit against the outer wall of the upper section of the landing gear; there are two corner brackets; the ends of the two corner brackets away from the arc-shaped frame are respectively connected to the outer walls of the corresponding first semi-circular arc-shaped structures.

[0012] In one possible implementation, the centering mechanism includes a third support, a fourth support, a third pad, and a fourth pad; the third support, the third pad, the fourth support, and the fourth pad are sequentially connected to form a second closed structure; wherein the middle portions of the third support and the fourth support are both second semi-circular arc-shaped structures, and the inner wall of the second semi-circular arc-shaped structure is configured to fit against the outer wall of the lower section of the landing gear; the second laser emitting device is rotatably connected to the side of the third pad away from the fourth pad.

[0013] In one possible implementation, the aircraft nose wheel steering measuring device further includes a first fixed bracket; the first fixed bracket is rotatably connected to the side of the third pad away from the fourth pad; the second laser emitting device is disposed on the side of the first fixed bracket opposite to the third pad; and / or further includes a second fixed bracket; the second fixed bracket is rotatably connected to the end of the angle measuring mechanism away from the upper section of the landing gear; the first laser emitting device is disposed on the side of the second fixed bracket opposite to the angle measuring mechanism.

[0014] In one possible implementation, the corner bracket is an L-shaped structure.

[0015] One or more technical solutions provided in the embodiments of this application have at least the following technical effects:

[0016] The aircraft nose wheel steering measurement device provided in this application includes an angle measuring mechanism, a centering mechanism, a first laser emitting device, and a second laser emitting device. During installation, the angle measuring mechanism is first installed on the upper section of the landing gear, and the direction of the first laser emitting device is adjusted so that its emitted laser beam is aligned with the centerline of the aircraft. This can typically be referenced to the center position of the tail fin or fuselage (heading) at the lower part of the aircraft. Next, the centering mechanism is securely installed on the lower section of the landing gear, and the second laser emitting device is adjusted so that its emitted laser is accurately aligned with the center of the nose wheel. After the centering mechanism is installed, the second laser emitting device is aligned with the angle scale line on the same horizontal plane, and the aircraft's control system outputs a steering command to the nose wheel steering servo. Upon receiving the control signal, the steering servo drives the lower section of the landing gear and the centering mechanism to rotate until they are completely aligned with the 0° position on the angle scale line, thereby achieving precise calibration of the nose wheel's neutral position. Furthermore, when the aircraft's control system outputs a steering command to the front wheel steering servo again, the steering servo will drive the lower landing gear section, the front wheel, and the centering mechanism to deflect. During this process, the second laser emitting device continuously emits a laser beam, which illuminates the angle scale line. By reading the corresponding value on the angle scale line, the deflection angle of the front wheel can be accurately determined. Therefore, compared with the previous manual measurement method, the aircraft front wheel steering measurement device of this application has significantly improved accuracy, is simple to operate, can greatly improve work efficiency, and shorten the measurement and calibration cycle. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments of this application will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 A schematic diagram of the structure of the aircraft front wheel steering measurement device provided in the embodiments of this application;

[0019] Figure 2 A schematic diagram of the structure of the aircraft nose wheel steering measurement device installed on the landing gear, as provided in the embodiments of this application.

[0020] Icons: 1-Angle measuring mechanism; 11-Angle scale line; 12-Card assembly; 121-First bracket; 122-Second bracket; 123-First pad; 124-Second pad; 13-Arc-shaped frame; 14-Angle frame; 15-Fixed frame; 16-Diagonal brace; 2-Centering mechanism; 21-Third bracket; 22-Fourth bracket; 23-Third pad; 24-Fourth pad; 3-First laser emitting device; 4-Second laser emitting device; 5-Landing gear; 6-Front wheel; 7-First fixed bracket; 8-Second fixed bracket; 9-First semi-circular arc structure; 10-Second semi-circular arc structure. Detailed Implementation

[0021] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0022] In the description of the embodiments of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the embodiments of this application and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.

[0023] This application provides an embodiment of an aircraft front wheel steering measurement device, such as... Figures 1 to 2As shown. The aircraft's nose wheel steering measurement device includes an angle measuring mechanism 1, a centering mechanism 2, a first laser emitting device 3, and a second laser emitting device 4. One end of the angle measuring mechanism 1 is fitted onto the outer wall of the upper section of the landing gear 5. The first laser emitting device 3 is rotatably connected to the side of the angle measuring mechanism 1 away from the upper section of the landing gear 5 and is configured to align with the centerline of the aircraft. The upper section of the landing gear 5 is fixedly connected to the aircraft, and the lower section of the landing gear 5 is rotatably connected to the upper section of the landing gear 5. The end of the lower section of the landing gear 5 away from the upper section of the landing gear 5 is connected to the aircraft's nose wheel 6. Specifically, in this application, the upper section of the landing gear 5 does not rotate, while the lower section of the landing gear 5 rotates. The centering mechanism 2 is fitted onto the lower section of the landing gear 5. The second laser emitting device 4 is rotatably connected to the side of the centering mechanism 2 facing the angle measuring mechanism 1 and is configured to align with the center of the nose wheel 6. An angle scale line 11 is provided on the side of the angle measuring mechanism 1 away from the first laser emitting device 3. The first laser emitting device 3 corresponds to the middle of the angle scale line 11, and the second laser emitting device 4 corresponds to the angle scale line 11.

[0024] Specifically, both the first laser emitting device 3 and the second laser emitting device 4 of this application can emit cross-shaped green lasers, with a laser beam width of 1 mm. Simultaneously, this application sets a reference point with a center of 0° on the angle scale line 11.

[0025] It should be noted that during installation, the angle measuring mechanism 1 is first installed on the upper section of the landing gear 5, and the direction of the first laser emitting device 3 is adjusted so that its emitted laser beam is aligned with the centerline of the aircraft. This can usually be referenced by the center position of the tail fin or fuselage (heading) at the bottom of the aircraft. Next, the centering mechanism 2 is securely installed on the lower section of the landing gear 5, and the second laser emitting device 4 is adjusted so that its emitted laser is accurately aligned with the center of the nose wheel 6. After the centering mechanism 2 is installed, the second laser emitting device 4 and the angle scale line 11 are adjusted to the same horizontal plane, and the aircraft's control system outputs a steering command to the steering servo of the nose wheel 6. After receiving the control signal, the steering servo drives the lower section of the landing gear 5 and the centering mechanism 2 to rotate until they are completely aligned with the 0° position on the angle scale line 11, thereby achieving precise calibration of the neutral position of the nose wheel 6. Furthermore, when the aircraft's control system outputs a steering command to the steering servo of the front wheel 6 again, the steering servo will drive the lower section of the landing gear 5, the front wheel 6, and the centering mechanism 2 to deflect. During this process, the second laser emitting device 4 continuously emits a laser beam, which illuminates the angle scale line 11. By reading the corresponding value on the angle scale line 11, the deflection angle of the front wheel 6 can be accurately determined. Therefore, compared with the previous manual measurement method, the aircraft front wheel steering measurement device of this application has significantly improved accuracy, is simple to operate, can greatly improve work efficiency, and shorten the measurement and calibration cycle.

[0026] In this embodiment, the aircraft nose wheel steering measuring device further includes a first elastic pad and a second elastic pad. The first elastic pad is disposed between the outer wall of the upper section of the landing gear 5 and the angle measuring mechanism 1. The second elastic pad is disposed between the outer wall of the lower section of the landing gear 5 and the centering mechanism 2.

[0027] It should be noted that, on the one hand, both the first and second elastic pads of this application can effectively prevent scratches on the upper and lower sections of the landing gear 5 when they come into contact with the angle measuring mechanism 1 and the centering mechanism 2. On the other hand, the first and second elastic pads can also provide greater friction, enabling the angle measuring mechanism 1 and the centering mechanism 2 to be securely clamped to the upper and lower sections of the landing gear 5, thereby enhancing the stability and reliability of the entire measuring device.

[0028] Specifically, the angle measuring mechanism 1 and the centering mechanism 2 of this application have gaps with the upper section of the landing gear 5 and the lower section of the landing gear 5, respectively, and the first elastic pad and the second elastic pad are disposed in the gaps.

[0029] In this embodiment, the angle measuring mechanism 1 includes a clamping assembly 12, an arc-shaped frame 13, and multiple corner frames 14. The clamping assembly 12 is sleeved on the outer wall of the upper section of the landing gear 5. The multiple corner frames 14 are spaced apart along the width direction of the clamping assembly 12. The arc-shaped frame 13 is located on the side of the corner frame 14 away from the clamping assembly 12, and has an angle scale line 11 on the side facing the centering mechanism 2. The first laser emitting device 3 is rotatably connected to the side of the corner frame 14 away from the arc-shaped frame 13.

[0030] It should be noted that the arc-shaped frame 13 is located on the side of the corner frame 14 away from the clamping assembly 12, and an angle scale line 11 is provided on the side facing the centering mechanism 2 for reading the deflection angle of the front wheel 6. At the same time, multiple corner frames 14 are evenly spaced along the width direction of the clamping assembly 12, providing a solid mounting base for the arc-shaped frame 13 and the first laser emitting device 3.

[0031] In this embodiment, the angle measuring mechanism 1 further includes a fixing frame 15. The fixing frame 15 is disposed among a plurality of corner frames 14 and is located on the side of the corner frame 14 away from the arc-shaped frame 13. The first laser emitting device 3 is rotatably connected to the side of the fixing frame 15 away from the corner frame 14.

[0032] Specifically, the first laser emitting device 3 can be hinged to the side of the fixed frame 15 away from the corner bracket 14.

[0033] In this embodiment, the first laser emitting device 3 is rotatably connected in the vertical plane to the side of the angle measuring mechanism 1 away from the upper section of the landing gear 5, allowing the first laser emitting device 3 to adjust its emission direction as needed to ensure that the emitted laser beam is accurately aligned with the centerline of the aircraft. The second laser emitting device 4 is rotatably connected in the vertical plane to the side of the centering mechanism 2 facing the angle measuring mechanism 1, allowing the second laser emitting device 4 to adjust its emission direction as needed to ensure that the laser beam is accurately aligned with the center of the front wheel 6.

[0034] Specifically, the first laser emitting device 3 and the second laser emitting device 4 can rotate 180° in the vertical plane.

[0035] In this embodiment, the angle measuring mechanism 1 further includes a plurality of diagonal braces 16. The two ends of the plurality of diagonal braces 16 are respectively connected to the two sides of the corresponding corner bracket 14, forming a triangular structure with the two sides of the corner bracket 14, thereby improving the overall structural strength.

[0036] Specifically, the corner frame 14 of this application has an L-shaped structure.

[0037] In this embodiment, the locking assembly 12 includes a first bracket 121, a second bracket 122, a first pad 123, and a second pad 124. The first bracket 121, the first pad 123, the second bracket 122, and the second pad 124 are sequentially connected to form a first closed structure. Specifically, the first bracket 121, the first pad 123, the second bracket 122, and the second pad 124 are sequentially and detachably connected. The middle portion of the first bracket 121 and the middle portion of the second bracket 122 are both first semi-circular arc-shaped structures 9, and the inner wall of the first semi-circular arc-shaped structure 9 is configured to fit against the outer wall of the upper section of the landing gear 5. There are two corner brackets 14. The ends of the two corner brackets 14 away from the arc-shaped frame 13 are respectively connected to the outer walls of the corresponding first semi-circular arc-shaped structures 9.

[0038] Specifically, the radius of the first semi-circular structure 9 in this application is 2 mm larger than the radius of the upper section of the landing gear 5. A first elastic pad with a thickness of 2 mm is laid between the outer wall of the upper section of the landing gear 5 and the angle measuring mechanism 1.

[0039] In this embodiment, the centering mechanism 2 includes a third support 21, a fourth support 22, a third pad 23, and a fourth pad 24. The third support 21, third pad 23, fourth support 22, and fourth pad 24 are sequentially connected to form a second closed structure. The third support 21, third pad 23, fourth support 22, and fourth pad 24 are sequentially detachably connected. The middle portions of the third support 21 and the fourth support 22 are both second semi-circular arc-shaped structures 10, and the inner walls of the second semi-circular arc-shaped structures 10 are configured to fit against the outer wall of the lower section of the landing gear 5. The second laser emitting device 4 is rotatably connected to the side of the third pad 23 away from the fourth pad 24.

[0040] The radius of the second semi-circular arc structure 10 in this application is 2mm larger than the radius of the upper section of the landing gear 5. A second elastic pad with a thickness of 2mm is laid between the outer wall of the lower section of the landing gear 5 and the centering mechanism 2. This not only ensures that the centering mechanism 2 can be easily fitted onto the lower section of the landing gear 5, but also provides convenience for subsequent measurement and adjustment through the reserved small gap.

[0041] Once the laser beam emitted by the second laser emitting device 4 is aligned with the center of the front wheel 6, the centering mechanism 2 is tightened to the lower section of the landing gear 5 to prevent movement.

[0042] Specifically, both the first elastic pad and the second elastic pad in this application are rubber blocks.

[0043] In this embodiment, the aircraft front wheel steering measuring device further includes a first fixed bracket 7. The first fixed bracket 7 is rotatably connected to the side of the third pad 23 away from the fourth pad 24. The second laser emitting device 4 is disposed on the side of the first fixed bracket 7 opposite to the third pad 23, and the first fixed bracket 7 provides a flexible adjustment platform for the second laser emitting device 4.

[0044] Specifically, the first fixed bracket 7 is provided with a third rotating hole, and the third pad 23 is provided with a fourth rotating hole corresponding to the third rotating hole.

[0045] And / or may also include a second fixed bracket 8, which is rotatably connected to one end of the upper section of the angle measuring mechanism 1 away from the landing gear 5. The first laser emitting device 3 is disposed on the side of the second fixed bracket 8 opposite to the angle measuring mechanism 1. The second fixed bracket 8 provides a flexible adjustment platform for the first laser emitting device 3.

[0046] Specifically, the second fixed bracket 8 is provided with a first rotating hole, and the angle measuring mechanism 1 is provided with a second rotating hole corresponding to the first rotating hole.

[0047] Furthermore, the aircraft front wheel steering measurement device of this application is a steering measurement tool with a simple design and convenient operation. It is not only suitable for the testing phase of aircraft and fixed-wing UAVs, but can also be widely used in the debugging process of steering control systems of vehicles (especially unmanned vehicles).

[0048] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0049] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.

Claims

1. A device for measuring the steering of an aircraft's nose wheel, characterized in that, It includes an angle measuring mechanism (1), a centering mechanism (2), a first laser emitting device (3), and a second laser emitting device (4); One end of the angle measuring mechanism (1) is sleeved on the outer wall of the upper section of the landing gear (5); The first laser emitting device (3) is rotatably connected to the side of the upper section of the angle measuring mechanism (1) away from the landing gear (5) and is configured to align with the centerline of the aircraft body; The upper section of the landing gear (5) is fixedly connected to the aircraft, the lower section of the landing gear (5) is rotatably connected to the upper section of the landing gear (5), and the end of the lower section of the landing gear (5) away from the upper section of the landing gear (5) is connected to the nose wheel (6) of the aircraft. The centering mechanism (2) is fitted onto the lower section of the landing gear (5); The second laser emitting device (4) is rotatably connected to the centering mechanism (2) on the side facing the angle measuring mechanism (1), and the second laser emitting device (4) is configured to be aligned with the center of the front wheel (6); An angle measuring mechanism (1) has an angle scale line (11) on the side opposite to the first laser emitting device (3); The first laser emitting device (3) corresponds to the middle of the angle scale line (11), and the second laser emitting device (4) corresponds to the angle scale line (11).

2. The aircraft nose wheel steering measuring device according to claim 1, characterized in that, It also includes a first elastic pad and a second elastic pad; The first elastic pad is disposed between the outer wall of the upper section of the landing gear (5) and the angle measuring mechanism (1); The second elastic pad is disposed between the outer wall of the lower section of the landing gear (5) and the centering mechanism (2).

3. The aircraft nose wheel steering measuring device according to claim 1, characterized in that, The angle measuring mechanism (1) includes a clamp assembly (12), an arc frame (13), and multiple corner frames (14); The card assembly (12) is sleeved on the outer wall of the upper section of the landing gear (5); The plurality of said corner brackets (14) are spaced apart along the width direction of said clamp assembly (12); The arc-shaped frame (13) is located on the side of the corner frame (14) away from the card assembly (12), and the angle scale line (11) is provided on the side facing the centering mechanism (2); The first laser emitting device (3) is rotatably connected to the side of the corner frame (14) away from the arc frame (13).

4. The aircraft nose wheel steering measuring device according to claim 3, characterized in that, The angle measuring mechanism (1) also includes a fixing frame (15); The fixing frame (15) is disposed among the plurality of corner frames (14) and is located on the side of the corner frame (14) away from the arc frame (13); The first laser emitting device (3) is rotatably connected to the side of the fixed frame (15) away from the corner frame (14).

5. The aircraft nose wheel steering measuring device according to claim 1, characterized in that, The first laser emitting device (3) is rotatably connected in the vertical plane to the side of the upper section of the angle measuring mechanism (1) away from the landing gear (5); The second laser emitting device (4) is rotatably connected in the vertical plane to the side of the centering mechanism (2) facing the angle measuring mechanism (1).

6. The aircraft nose wheel steering measuring device according to claim 3, characterized in that, The angle measuring mechanism (1) also includes multiple diagonal braces (16); The two ends of the plurality of diagonal braces (16) are respectively connected to the two sides of the corresponding corner bracket (14), and form a triangular structure with the two sides of the corner bracket (14).

7. The aircraft nose wheel steering measuring device according to claim 3, characterized in that, The card assembly (12) includes a first bracket (121), a second bracket (122), a first pad (123), and a second pad (124); The first bracket (121), the first pad (123), the second bracket (122), and the second pad (124) are connected in sequence to form a first closed structure; The middle part of the first support (121) and the middle part of the second support (122) are both first semi-circular arc-shaped structures (9), and the inner wall of the first semi-circular arc-shaped structure (9) is configured to fit against the outer wall of the upper section of the landing gear (5). There are two corner brackets (14); The ends of the two corner brackets (14) away from the arc-shaped bracket (13) are respectively connected to the outer wall of the corresponding first semi-circular arc-shaped structure (9).

8. The aircraft nose wheel steering measuring device according to claim 1, characterized in that, The centering mechanism (2) includes a third support (21), a fourth support (22), a third pad (23), and a fourth pad (24); The third bracket (21), the third pad (23), the fourth bracket (22), and the fourth pad (24) are connected in sequence to form a second closed structure; The middle part of the third support (21) and the middle part of the fourth support (22) are both second semi-circular arc-shaped structures (10), and the inner wall of the second semi-circular arc-shaped structure (10) is configured to fit against the outer wall of the lower section of the landing gear (5). The second laser emitting device (4) is rotatably connected to the side of the third pad (23) away from the fourth pad (24).

9. The aircraft nose wheel steering measuring device according to claim 8, characterized in that, It also includes a first fixing bracket (7); The first fixed bracket (7) is rotatably connected to the side of the third pad (23) away from the fourth pad (24); The second laser emitting device (4) is disposed on the side of the first fixed bracket (7) away from the third pad (23); And / or may also include a second fixing bracket (8); The second fixed bracket (8) is rotatably connected to one end of the upper section of the angle measuring mechanism (1) away from the landing gear (5); The first laser emitting device (3) is disposed on the side of the second fixed bracket (8) away from the angle measuring mechanism (1).

10. The aircraft nose wheel steering measuring device according to claim 3, characterized in that, The corner bracket (14) has an L-shaped structure.

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