Aircraft landing gear wheel assembly shaft space angle detection device and detection method

Abstract

The invention discloses an aircraft landing gear wheel assembly shaft space angle detection device and method. The aircraft landing gear wheel assembly shaft space angle detection device is provided with a first supporting seat, a second supporting seat, an angle scale, an angle scale fixing unit, a sleeve, a pointer unit and a pointer positioning seat unit. The first supporting seat is used for supporting two ends of a pin shaft of a workpiece, and the second supporting seat is used for positioning the height of the angle scale fixing unit; the angle scale fixing unit is clamped outside a piston rod of a workpiece, and the angle scale is installed on the end face of one side of the angle scale fixing unit. The sleeve is clamped outside an airplane wheel assembling shaft of a workpiece, and a positioning groove is formed in the bottom of the sleeve; the pointer unit is assembled with a piston rod of a workpiece through the pointer positioning seat unit, one end of the pointer unit points to the angle scale, and the other end of the pointer unit penetrates through a positioning groove in the bottom of the sleeve. According to the invention, the detection workpiece is accurately positioned, so that the reliability of the space angle detection result of the aircraft wheel assembly shaft of the aircraft landing gear is ensured.

Description

Technical Field

[0001] This invention relates to the field of testing and measurement technology, specifically to a device and method for detecting the spatial angle of an aircraft landing gear wheel assembly shaft. Background Technology

[0002] As attached Figure 1 , Figure 2 , Figure 3 As shown, in the landing gear damper strut actuator assembly of a certain type of aircraft, one end of the outer cylinder 1 of the damper strut actuator is assembled to the Y-shaped trunnion connecting rod of the landing gear via a pin 2. The end of the piston rod 3 of the damper strut actuator is connected to the wheel assembly shaft 4. According to the landing gear assembly technical requirements, after the damper strut actuator assembly is assembled to the Y-shaped trunnion connecting rod of the landing gear, it is necessary to ensure that the spatial angle between the plane of the wheel assembly shaft 4 and the plane of the Y-shaped trunnion connecting rod of the landing gear (hereinafter referred to as the wheel assembly shaft spatial angle) is a set value, i.e., as shown in the attached figure. Figure 3 The angle θ between the center axis of the central gear assembly shaft 4 and the center axis of the pin shaft 2 is a set value.

[0003] In aircraft repair companies, which lack the production conditions of aircraft manufacturers, the detection of the spatial angle of the wheel assembly shaft after the shock absorber strut actuator assembly is assembled during maintenance is generally completed using conventional measuring instruments and equipment. However, due to the difficulty in accurately positioning and fixing the workpiece, the reliability of the detection results cannot be guaranteed. Therefore, it is necessary to design an innovative device and method for detecting the spatial angle of the wheel assembly shaft in the aircraft landing gear shock absorber strut actuator assembly. Summary of the Invention

[0004] This invention provides a device and method for detecting the spatial angle of the landing gear wheel assembly axle, aiming to ensure the reliability of the detection results of the spatial angle of the landing gear wheel assembly axle during aircraft repair by accurately positioning and fixing the workpiece.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: A spatial angle detection device for the assembly shaft of an aircraft landing gear wheel is provided, comprising a first support base, a second support base, an angle disc, an angle disc fixing unit, a sleeve, a pointer unit, and a pointer positioning base unit; The first support base and the second support base are both fixed on the test table surface. The first support base includes two parts arranged symmetrically on the left and right sides, and the two parts of the first support base support the two ends of the pin shaft of the workpiece. The second support base is a height-adjustable structure, and the height of the unit is fixed by the positioning angle plate of the second support base; The angle plate fixing unit is clamped outside the piston rod of the workpiece, and the angle plate is installed on one end face of the angle plate fixing unit; The sleeve is clamped outside the machine wheel assembly shaft of the workpiece, and a positioning groove that cooperates with the pointer unit is provided at the bottom of the sleeve; The pointer unit is assembled with the piston rod of the workpiece through the pointer positioning seat unit. One end of the pointer unit points to the angle plate, and the other end of the pointer unit passes through the positioning groove at the bottom of the sleeve.

[0006] The aforementioned aircraft landing gear wheel assembly axle space angle detection device includes an angle disc fixing unit comprising a fixing block, a first clamping block, and a locking pin assembly. Both the fixing block and the first clamping block are provided with semi-circular slots, which together enclose and clamp the piston rod of the workpiece. The bottom surface of the fixing block is connected to a second support base. One end of the first clamping block is hinged to one side of the semi-circular slot of the fixing block, and the other end is locked and fixed to the other side of the semi-circular slot of the fixing block through the locking pin assembly.

[0007] The aforementioned aircraft landing gear wheel assembly shaft space angle detection device includes a pointer positioning seat unit comprising a Y-shaped frame and a second clamping block. One end of the Y-shaped frame is provided with a semi-circular groove that matches the outer wall of the piston rod of the workpiece, and the other end is provided with a pointer sleeve. The two sides of the semi-circular groove are respectively assembled with the second clamping block through pins and locking pins. The pointer positioning seat unit is fitted onto the outside of the piston rod of the workpiece by the cooperation between the semi-circular groove of the Y-shaped frame and the second clamping block.

[0008] The aforementioned aircraft landing gear wheel assembly shaft space angle detection device includes a pointer unit with a pointer rod and a pointer; one end of the pointer rod is provided with a pointer mounting hole, and the other end is a square column that mates with the positioning groove at the bottom of the sleeve; one end of the pointer passes through the pointer mounting hole of the pointer rod, and the other end points to the angle dial.

[0009] The aforementioned aircraft landing gear wheel assembly shaft space angle detection device includes a pointer unit further comprising a spring and a lever, and an elongated hole on the side wall of the pointer mounting hole of the pointer lever; the spring is fitted into the pointer mounting hole of the pointer lever and abuts against the pointer insertion end; the lever passes through the elongated hole on the side wall of the pointer mounting hole and is fixedly assembled with the pointer.

[0010] The aforementioned aircraft landing gear wheel assembly shaft space angle detection device has V-grooves on the top of both the left and right parts of the first support base, and the left and right ends of the workpiece pin are respectively placed in the corresponding V-grooves.

[0011] The aforementioned aircraft landing gear wheel assembly axle space angle detection device has a vernier angle gauge installed on the angle dial.

[0012] A method for detecting the spatial angle of the aircraft landing gear wheel assembly shaft, using the aforementioned aircraft landing gear wheel assembly shaft spatial angle detection device to detect the spatial angle of the wheel assembly shaft in the aircraft landing gear shock absorber strut actuator assembly, the specific operation steps are as follows: a. Assembly of the angle plate, angle plate fixing unit and workpiece: First, assemble the angle plate with the fixing block in the angle plate fixing unit. Then, clamp the fixing block and the first clamping block in the angle plate fixing unit outside the piston rod of the shock absorber actuating cylinder assembly, so that the zero line of the upstream scale of the angle plate is in the same plane as the center axis of the piston rod and the center axis of the pin of the shock absorber actuating cylinder assembly. b. Workpiece placement: Place the two ends of the pin of the shock absorber actuator assembly into the V-grooves of the left and right parts of the first support seat respectively, and adjust the height of the second support seat so that the plane containing the piston rod center axis, the pin center axis and the zero line of the angle scale on the angle dial is parallel to the test table surface. c. Assembly of the sleeve, pointer unit, and pointer positioning seat unit with the workpiece: First, fit the sleeve outside the wheel assembly shaft of the shock absorber support actuator cylinder assembly, so that the center axis of the positioning groove at the bottom of the sleeve is located in the plane formed by the center axis of the wheel assembly shaft and the center axis of the piston rod. Then, insert the pointer unit into the pointer sleeve at one end of the Y-shaped frame of the pointer positioning seat unit. The square column end of the pointer unit is embedded in the positioning groove at the bottom of the sleeve. Then, the semi-circular groove of the Y-shaped frame of the pointer positioning seat unit cooperates with the second clamping block to clamp the piston rod outside. d. Aircraft landing gear wheel assembly shaft spatial angle detection: Move the lever of the pointer unit to make the pointer accurately point to the vertex angle scale on the angle dial, read the angle value and compare it with the set value to determine whether the spatial angle of the wheel assembly shaft in the shock absorber strut actuator assembly meets the assembly requirements.

[0013] In the above-mentioned method for detecting the spatial angle of the aircraft landing gear wheel assembly shaft, in step b, a dial indicator is used to measure the distance between two points on the axial parallel line of the piston rod outer wall of the shock absorber strut actuator assembly and the test table surface, in order to verify whether the plane containing the piston rod center axis, the pin shaft center axis, and the zero line of the angle scale on the angle dial of the shock absorber strut actuator assembly is parallel to the test table surface.

[0014] In the above-mentioned method for detecting the spatial angle of the aircraft landing gear wheel assembly shaft, in step c, a vertical projection surface is set on the test table. The distance from two points on the axial parallel line of the outer wall of the pointer sleeve in the pointer positioning seat unit to the vertical projection surface is measured by a dial indicator. This verifies that the central axis of the piston rod of the shock absorber strut actuator assembly, the central axis of the wheel assembly shaft, and the central axis of the pointer unit are located in the same plane.

[0015] This invention provides a device and method for detecting the spatial angle of the wheel assembly shaft in an aircraft landing gear strut. It is suitable for detecting the spatial angle of the wheel assembly shaft in the aircraft landing gear shock absorber strut actuator assembly. The device ensures, through the cooperation of a first support base, a second support base, and an angle dial fixing unit, that the zero line of the upward-pointing angle scale on the angle dial, the central axis of the piston rod of the shock absorber strut actuator assembly, and the central axis of the pin shaft are all in the same plane parallel to the test table surface. Furthermore, it ensures, through the cooperation of a sleeve, a pointer unit, and a pointer positioning unit, that the central axis of the piston rod of the shock absorber strut actuator assembly, the central axis of the wheel assembly shaft, and the central axis of the pointer unit are all located in the same plane. After the device is assembled with the aircraft landing gear wheel assembly shaft spatial angle detection device, the value indicated by the pointer on the angle dial is the spatial angle of the wheel assembly shaft in the aircraft landing gear shock absorber strut actuator assembly. Therefore, it can be seen that the present invention converts the wheel assembly shaft space angle θ required for the assembly of the shock absorber strut actuator cylinder into an angle value indicated by a pointer, which not only enables accurate positioning of the workpiece, but also facilitates intuitive acquisition of test data, thereby ensuring the reliability of the test results. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the aircraft landing gear shock absorber strut actuator assembly involved in the present invention. Figure 2 Figure 1 View from direction A; Figure 3 Figure 1 View from direction B; Figure 4 This is a schematic diagram of the space angle detection device for the aircraft landing gear wheel assembly shaft and its mating structure with the workpiece described in this invention; Figure 5 yes Figure 4 Schematic diagram of the cross-sectional structure of the middle CC section; Figure 6 yes Figure 4 The D-direction view; Figure 7 This is a schematic diagram of the fixing block structure in the angle plate fixing unit; Figure 8 This is a schematic diagram of the clamping block structure; Figure 9 This is a schematic diagram of the Y-shaped frame structure in the pointer positioning unit; Figure 10 This is a schematic diagram of the pointer unit structure; Figure 11 This is a schematic diagram of the cross-sectional structure of the casing; Figure 12 yes Figure 11 The K-direction view.

[0017] Explanation of each label in the diagram: 1 represents the outer cylinder; 2 represents the pin; 3 represents the piston rod; 4 is the axle for assembling the wheel; 5 is the first support base, and 5-1 is the V-groove; 6 represents the angle dial, and 6-1 represents the vernier angle scale; 7 is the angle plate fixing unit, 7-1 is the fixing block, 7-1-1 is the first clamping block hinge end clearance groove, 7-1-2 is the hinge shaft hole, 7-1-3 is the first clamping block locking hole, 7-1-4 is the first clamping block locking groove, 7-1-5 is the angle plate connecting lug, 7-2 is the first clamping block, 7-2-1 is the hinge shaft through hole, 7-2-2 is the locking pin through groove, and 7-3 is the locking pin assembly; 8 is the second support seat; 9 is the pointer positioning seat unit, 9-1 is the Y-shaped frame, 9-1-1 is the semi-circular groove, 9-1-2 is the pointer sleeve, 9-2 is the second clamping block, and 9-3 is the pin. 10 is the pointer unit, 10-1 is the pointer rod, 10-2 is the pointer, 10-3 is the spring, 10-4 is the lever, 10-5 is the square prism, and 10-6 is the elongated hole; 11 is the sleeve, and 11-1 is the positioning groove; 12 represents the testing table surface. Detailed Implementation

[0018] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0019] See Figure 1. Figure 2 , Figure 3 A landing gear damper strut actuator assembly is disclosed. One end of the outer cylinder 1 of the damper strut actuator is assembled to the Y-shaped trunnion connecting rod of the landing gear via a pin 2. The end of the piston rod 3 of the damper strut actuator is connected to the wheel assembly shaft 4. According to landing gear assembly technical requirements, after the damper strut actuator is assembled to the Y-shaped trunnion connecting rod of the landing gear, the spatial angle between the plane of the wheel assembly shaft 4 and the plane of the Y-shaped trunnion connecting rod of the landing gear must be a set value, i.e., [the following is missing from the original text]. Figure 3 The angle θ between the center axis of the central gear assembly shaft 4 and the center axis of the pin shaft 2 is a set value.

[0020] See Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 11 , Figure 12To accurately measure the spatial angle of the wheel assembly shaft in the aircraft landing gear shock absorber strut actuator assembly, this invention provides an aircraft landing gear wheel assembly shaft spatial angle detection device. It comprises a first support base 5, a second support base 8, an angle disc 6, an angle disc fixing unit 7, a sleeve 11, a pointer unit 10, and a pointer positioning unit 9. Both the first support base 5 and the second support base 8 are fixed on the testing table surface 12. The first support base 5 includes two symmetrically arranged parts, each with a V-groove 5-1 at its top. The pins 2 of the workpiece (the aircraft landing gear shock absorber strut actuator assembly) are respectively placed in the corresponding V-grooves 5-1. The second support base 8 is height-adjustable, and the height of the angle disc fixing unit 7 is positioned by the second support base 8. The angle disc... The fixing unit 7 is clamped outside the piston rod 3 of the workpiece. An angle disk 6 is installed on one end face of the angle disk fixing unit 7. A vernier angle gauge 6-1 is provided on the angle disk 6. The angle disk fixing unit 7 and the second support seat 8 cooperate to ensure that the workpiece pin shaft and the central axis of the piston rod are located in the same plane as the parallel detection table surface 12. The sleeve 11 is clamped outside the wheel assembly shaft 4 of the workpiece. A positioning groove 11-1 that cooperates with the pointer unit is provided at the bottom of the sleeve 11. The pointer unit 10 is assembled with the piston rod 3 of the workpiece through the pointer positioning seat unit 9. One end of the pointer unit 10 points to the angle disk 6, and the other end passes through the positioning groove 11-1 at the bottom of the sleeve 11. The positioning groove 11-1 ensures that the central axis of the workpiece piston rod, the central axis of the wheel assembly shaft, and the central axis of the pointer unit are located in the same plane.

[0021] See Figure 5 , Figure 6 , Figure 7 , Figure 8The aircraft landing gear wheel assembly axle space angle detection device of the present invention includes an angle disc fixing unit 7 comprising a fixing block 7-1, a first clamping block 7-2, and a locking pin assembly 7-3; semi-circular slots are respectively provided on the fixing block 7-1 and the first clamping block 7-2, the upper semi-circular slot of the fixing block 7-1 and the upper semi-circular slot of the first clamping block 7-2 are symmetrically arranged, the lower ends of the fixing block 7-1 and the first clamping block 7-2 are hinged together, and the first clamping block is hinged on the lower side of the semi-circular slot of the fixing block 7-1. The end clearance groove 7-1-1 and the hinge shaft hole 7-1-2 are provided. The lower side of the semi-circular groove of the first clamping block 7-2 is provided with a hinge shaft through hole 7-2-1. The fixing block 7-1 and the first clamping block 7-2 are clamped around the piston rod 3 of the workpiece and locked by the locking pin assembly 7-3. For this purpose, the first clamping block locking groove 7-1-4 and the first clamping block locking hole 7-1-3 are provided on the upper side of the semi-circular groove of the fixing block 7-1, and the locking pin through groove 7-2-2 is provided on the upper side of the semi-circular groove of the first clamping block. The fixing block 7-1 is also provided with a set of angle plate connecting ears 7-1-5. Several sets of angle plate connecting ears 7-1-5 are arranged around the semi-circular groove of the fixing block 7-1. The fixing block 7-1 is fixedly assembled with the angle plate 6 through the angle plate connecting ears 7-1-5. This assembly structure can not only reliably fix the angle plate, but also reduce the weight of the fixing block 7-1, which is beneficial to the balance of weight on the left and right sides of the angle plate fixing unit 7. The bottom surface of the fixing block 7-1 is connected to the second support base 8, and the height of the fixing block 7-1 and the angle plate 6 can be controlled by adjusting the second support base 8. One end of the first clamping block is hinged to one side of the semi-circular groove of the fixing block, and the other end is locked and fixed to the other side of the semi-circular groove of the fixing block through the locking pin assembly.

[0022] See Figure 4 , Figure 9 The aircraft landing gear wheel assembly shaft space angle detection device of the present invention includes a pointer positioning seat unit 9 comprising a Y-shaped frame 9-1 and a second clamping block 9-2. One end of the Y-shaped frame 9-1 is provided with a semi-circular groove 9-1-1 that matches the outer wall of the piston rod of the workpiece, and the other end is provided with a pointer sleeve 9-1-2. The two sides of the semi-circular groove 9-1-1 are respectively assembled with the second clamping block 9-2 through a pin and a locking pin. The structure of the second clamping block 9-2 is the same as that of the first clamping block 7-2 in the angle plate fixing unit 7 (this structure will not be described in detail). The pointer positioning seat unit 9 can be fitted onto the outside of the piston rod 3 of the workpiece by the cooperation of the semi-circular groove 9-1-1 of the Y-shaped frame and the second clamping block 9-2.

[0023] See Figure 4 , Figure 6 , Figure 10The aircraft landing gear wheel assembly shaft space angle detection device of the present invention includes a pointer unit 10 comprising a pointer rod 10-1, a pointer 10-2, a spring 10-3, and a lever 4. One end of the pointer rod 10-1 has a pointer mounting hole, and the other end is a square column 10-5 that mates with the positioning groove 11-1 at the bottom of the sleeve 11. An elongated hole 10-6 is provided on the side wall of the pointer mounting hole of the pointer rod 10-1. One end of the pointer 10-2 passes through the pointer mounting hole of the pointer rod 10-1, and the other end points to the angle disc 6. The spring 10-3 is fitted into the pointer mounting hole of the pointer rod 10-1, abutting against the end of the pointer 10-2 that passes through it. The lever 4 passes through the elongated hole 10-6 on the side wall of the pointer mounting hole and is fixedly assembled with the pointer 10-2.

[0024] See Figures 1 to 12 The present invention also provides an angle measurement method, which uses the above-mentioned aircraft landing gear wheel assembly shaft spatial angle detection device to detect the spatial angle of the wheel assembly shaft in the aircraft landing gear shock absorber strut actuator assembly. The specific operation steps are as follows: a. Assembly of the angle plate, angle plate fixing unit and workpiece: First, assemble the angle plate 6 with the fixing block 7-1 in the angle plate fixing unit 7. Then, clamp the fixing block 7-1 and the first clamping block 7-2 in the angle plate fixing unit 7 outside the piston rod 3 of the shock absorber actuating cylinder assembly, so that the zero line of the vertex angle ruler 6-1 on the angle plate 6 is in the same plane as the center axis of the piston rod and the center axis of the pin of the shock absorber actuating cylinder assembly. b. Workpiece placement: Place both ends of the pin 3 of the shock absorber actuator assembly in the V-grooves 5-1 of the left and right parts of the first support 5, respectively. Adjust the height of the second support 8 so that the plane containing the piston rod center axis, the pin center axis, and the zero line of the angle scale on the angle dial is parallel to the test table surface 12. The distance between two points on the axial parallel line of the outer wall of the piston rod 3 of the shock absorber actuator assembly and the test table surface 12 can be measured by a dial indicator to verify whether the plane containing the piston rod center axis, the pin center axis, and the zero line of the angle scale on the angle dial is parallel to the test table surface 12. c. Assembly of the sleeve, pointer unit, and pointer positioning seat unit with the workpiece: First, fit the sleeve 11 outside the wheel assembly shaft 4 of the shock absorber actuating cylinder assembly, so that the center axis of the bottom positioning groove of the sleeve 11 is located in the plane formed by the center axis of the wheel assembly shaft and the center axis of the piston rod. Then, insert the pointer unit 10 into the pointer sleeve at one end of the Y-shaped frame 9-1 of the pointer positioning seat unit 9. The square column end of the pointer unit is embedded in the bottom positioning groove 11-1 of the sleeve 11. A vertical projection surface can be set on the test table 12. The distance from two points on the axial parallel line of the outer wall of the pointer sleeve 9-1-2 in the pointer positioning seat unit 9 to the vertical projection surface is measured by a dial indicator to verify that the center axis of the piston rod of the shock absorber actuating cylinder assembly, the center axis of the wheel assembly shaft, and the center axis of the pointer unit are in the same plane. Then, the semi-circular groove 9-1-1 of the Y-shaped frame 9-1 of the pointer positioning seat unit 9 and the second clamping block 9-2 are fitted together and clamped outside the piston rod 3. d. Aircraft landing gear wheel assembly shaft space angle detection: Move the lever 10-4 of the pointer unit 10 so that the pointer points precisely to the vertex angle scale 6-1 on the angle dial 6, read the angle value and compare it with the set value to determine whether the space angle of the wheel assembly shaft in the shock absorber strut actuator assembly meets the assembly requirements.

Claims

1. A device for detecting the spatial angle of an aircraft landing gear wheel assembly shaft, characterized in that: It is provided with a first support base (5), a second support base (8), an angle plate (6), an angle plate fixing unit (7), a sleeve (11), a pointer unit (10) and a pointer positioning base unit (9); The first support base (5) and the second support base (8) are both fixed on the test table surface (12). The first support base (5) includes two parts arranged symmetrically on the left and right sides. The two parts of the first support base support the two ends of the pin (2) of the workpiece. The second support base (8) is a height-adjustable structure, and the height of the positioning angle plate is fixed by the second support base (8); The angle plate fixing unit (7) is clamped outside the piston rod (3) of the workpiece, and the angle plate (6) is installed on one end face of the angle plate fixing unit (7). The sleeve (11) is clamped outside the wheel assembly shaft (4) of the workpiece, and a positioning groove (11-1) is provided at the bottom of the sleeve (11) to cooperate with the pointer unit. The pointer unit (10) is assembled with the piston rod (3) of the workpiece through the pointer positioning seat unit (9). One end of the pointer unit (10) points to the angle plate (6), and the other end passes through the positioning groove (11-1) at the bottom of the sleeve (11).

2. The aircraft landing gear wheel assembly axle spatial angle detection device according to claim 1, characterized in that: The angle plate fixing unit (7) includes a fixing block (7-1), a first pressing block (7-2), and a locking pin assembly (7-3). The fixing block (7-1) and the first pressing block (7-2) are both provided with semi-circular slots. The two are clamped around the piston rod (3) of the workpiece. The bottom surface of the fixing block (7-1) is connected to the second support seat (8). One end of the first pressing block (7-2) is hinged to one side of the semi-circular slot of the fixing block, and the other end is locked and fixed to the other side of the semi-circular slot of the fixing block through the locking pin assembly (7-3).

3. The aircraft landing gear wheel assembly axle spatial angle detection device according to claim 1 or 2, characterized in that: The pointer positioning unit (9) includes a Y-shaped frame (9-1) and a second clamping block (9-2). One end of the Y-shaped frame (9-1) is provided with a semi-circular groove (9-1-1) that matches the outer wall of the piston rod of the workpiece, and the other end is provided with a pointer sleeve (9-1-2). The two sides of the semi-circular groove (9-1-1) are respectively assembled with the second clamping block (9-2) through a pin and a locking pin. The pointer positioning unit (9) is fitted onto the outside of the piston rod (3) of the workpiece by the cooperation between the semi-circular groove (9-1-1) of the Y-shaped frame and the second clamping block (9-2).

4. The aircraft landing gear wheel assembly axle spatial angle detection device according to claim 3, characterized in that: The pointer unit (10) is provided with a pointer rod (10-1) and a pointer (10-2); one end of the pointer rod (10-1) is provided with a pointer mounting hole, and the other end is a square column (10-5) that cooperates with the positioning groove (11-1) at the bottom of the sleeve (11); one end of the pointer (10-2) is inserted into the pointer mounting hole of the pointer rod (10-1), and the other end points to the angle disk (6).

5. The aircraft landing gear wheel assembly axle spatial angle detection device according to claim 4, characterized in that: The pointer unit (10) is also provided with a spring (10-3) and a lever (4), and an elongated hole (10-6) is provided on the side wall of the pointer mounting hole of the pointer rod (10-1); the spring (10-3) is fitted in the pointer mounting hole of the pointer rod (10-1) and abuts against the insertion end of the pointer (10-2); the lever (4) passes through the elongated hole (10-6) on the side wall of the pointer mounting hole and is fixedly assembled with the pointer (10-2).

6. The aircraft landing gear wheel assembly axle spatial angle detection device according to claim 3, characterized in that: V-grooves (5-1) are provided on the top of the left and right parts of the first support base (5), and the left and right ends of the pin (2) of the workpiece are respectively placed in the corresponding V-grooves (5-1).

7. The aircraft landing gear wheel assembly axle spatial angle detection device according to claim 3, characterized in that: A vernier angle ruler (6-1) is set on the angle disk (6).

8. A method for detecting the spatial angle of an aircraft landing gear wheel assembly shaft, characterized in that: The aforementioned aircraft landing gear wheel assembly shaft spatial angle detection device was used to detect the spatial angle of the wheel assembly shaft in the aircraft landing gear shock absorber strut actuator assembly. The specific operating steps are as follows: a. Assembly of angle plate, angle plate fixing unit and workpiece: First, assemble the angle plate (6) with the fixing block (7-1) in the angle plate fixing unit (7), and then clamp the fixing block (7-1) and the first clamping block (7-2) in the angle plate fixing unit (7) outside the piston rod (3) of the shock absorber actuator cylinder assembly, so that the zero line of the upstream angle scale (6-1) on the angle plate (6) is in the same plane as the center axis of the piston rod and the center axis of the pin of the shock absorber actuator cylinder assembly; b. Workpiece placement: Place the two ends of the pin (3) of the shock absorber actuator assembly into the V-groove (5-1) of the left and right parts of the first support (5), and adjust the height of the second support (8) so that the plane containing the piston rod center axis, the pin center axis and the zero line of the angle scale on the angle dial is parallel to the test table surface (12). c. Assembly of the sleeve, pointer unit and pointer positioning seat unit with the workpiece: First, put the sleeve (11) on the outside of the wheel assembly shaft (4) of the shock absorber actuating cylinder assembly, so that the center axis of the positioning groove at the bottom of the sleeve (11) is located in the plane formed by the center axis of the wheel assembly shaft and the center axis of the piston rod. Then, insert the pointer unit (10) into the pointer sleeve at one end of the Y-shaped frame (9-1) of the pointer positioning seat unit (9). The square column end of the pointer unit is embedded in the positioning groove (11-1) at the bottom of the sleeve (11). Then, the semi-circular groove (9-1-1) of the Y-shaped frame (9-1) of the pointer positioning seat unit (9) cooperates with the second clamping block (9-2) to clamp the piston rod (3) outside. d. Detection of the spatial angle of the aircraft landing gear wheel assembly shaft: Move the lever (10-4) of the pointer unit (10) so that the pointer is accurately pointed to the scale (6-1) of the angle dial (6), read the angle value and compare it with the set value to determine whether the spatial angle of the wheel assembly shaft in the shock absorber strut actuator assembly meets the assembly requirements.

9. The method for detecting the spatial angle of the aircraft landing gear wheel assembly shaft according to claim 8, characterized in that: In step b, the distances between two points on the axial parallel line of the outer wall of the piston rod (3) of the shock absorber actuating cylinder assembly and the test table surface (12) are measured by a dial indicator to verify whether the plane containing the piston rod center axis, the pin center axis and the zero line of the angle scale on the angle dial of the shock absorber actuating cylinder assembly is parallel to the test table surface (12).

10. The method for detecting the spatial angle of the aircraft landing gear wheel assembly shaft according to claim 8, characterized in that: In step c, a vertical projection surface is set on the test table (12). The distance from two points on the axial parallel line of the outer wall of the pointer sleeve (9-1-2) in the pointer positioning seat unit (9) to the vertical projection surface is measured by a dial indicator. This verifies that the central axis of the piston rod of the shock absorber actuating cylinder assembly, the central axis of the wheel assembly shaft, and the central axis of the pointer unit are in the same plane.

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