An aircraft rotary actuator axial clearance measuring device

Abstract

An axial clearance measuring device for an aircraft rotary actuator includes a workpiece clamping and positioning mechanism and a measuring execution mechanism. The workpiece clamping and positioning mechanism comprises a base, a side pressure plate, and a workpiece positioning pin assembly. The base has a workpiece receiving cavity in its center. The side pressure plate comprises two symmetrically arranged parts, respectively mounted on the front and rear surfaces of the base. Each part has a positioning pin hole corresponding to a positioning hole on the rotary actuator lug, and the inner side of each part has a mating surface matching the angle of the rotary actuator lug. The number of workpiece positioning pin assemblies is the same as the number of positioning holes on the rotary actuator lug, and the lug and side pressure plate are fixedly connected by the workpiece positioning pin assemblies. The measuring execution mechanism is mounted on one side of the base and includes a dial indicator. This invention meets the requirements of aircraft maintenance operation specifications and achieves the goal of ensuring the assembly quality after aircraft maintenance.

Description

Technical Field

[0001] This invention relates to a measuring device, and more particularly to a dedicated measuring device for measuring the axial clearance of a rotary actuator in an aircraft leading-edge flap drive system during maintenance. Background Technology

[0002] During takeoff and landing, the wings of an aircraft are subjected to enormous aerodynamic forces, such as... Figure 1 , Figure 2 As shown, in order to reduce the internal stress generated by the wing under the action of external aerodynamic forces and to ensure that the wing deforms within a safe range, the aircraft manufacturer designed the rotary actuator 1 in the leading-edge flap drive system as a jointed flexible connection structure. This allows the rotary actuator 1 to generate a flexible connection structure under wing stress, such as... Figure 1 The flexible deformation of the curves I to IV shown in the figure is used to release the energy generated by the external force of the air.

[0003] As attached Figure 1 , Figure 2 As shown, the rotary actuator 1 in the leading edge flap drive system of the aircraft has nine sets of lugs 1-1 on both sides that are connected to other mechanisms. Each set of lugs consists of two parts arranged opposite each other. The two parts of the four upper sets of lugs are inclined at a certain angle (8°36′±15′) to the horizontal plane, while the two parts of the five lower sets of lugs are parallel to the horizontal plane. After the aircraft has flown for a certain period of time, the positioning holes and internal parts of the rotary actuator 1 lugs 1-1 are worn to varying degrees, causing some parameters of the rotary actuator 1 to exceed the set range. Therefore, when the aircraft is overhauled, the rotary actuator 1 needs to be disassembled and the severely worn and expired parts replaced. After reassembly, the axial clearance of the rotary actuator also needs to be measured to determine whether it meets the technical requirement of 0.10 to 0.15 mm.

[0004] According to the operational specifications for aircraft maintenance, the measurement of the axial clearance of a rotary actuator should be performed under conditions simulating the theoretical state of the rotary actuator at the time of manufacture (without any flexible deformation). This means that the relevant dimensions and tolerances, such as the hole spacing between adjacent sets of lugs (45±0.1mm), the angle of one lug (8°36′±15′), flatness (≤0.05mm), and coaxiality (<0.1mm), must be consistent with those at the time of manufacture. Therefore, a dedicated measuring device is needed to measure the axial clearance of the rotary actuator to comply with the aircraft maintenance operational specifications and ensure the assembly quality after aircraft maintenance. Summary of the Invention

[0005] This invention provides an axial clearance measuring device for an aircraft rotary actuator. It aims to meet the requirements of aircraft maintenance operation specifications and ensure the assembly quality after aircraft maintenance by innovatively designing the workpiece clamping and positioning mechanism and the measuring execution mechanism.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] An axial clearance measuring device for a rotary actuator of an aircraft includes a workpiece clamping and positioning mechanism and a measuring execution mechanism. The workpiece clamping and positioning mechanism has a base, a side pressure plate, and a workpiece positioning pin assembly. The base is a box-frame structure with a workpiece receiving cavity in the middle. The side pressure plate includes two symmetrically arranged parts, which are respectively installed on the front and rear surfaces of the base. Each part is provided with a positioning pin hole corresponding to the positioning hole on the rotary actuator lug, and the inner side of each part is provided with a mating surface matching the angle of the rotary actuator lug. The number of workpiece positioning pin assemblies is the same as the number of positioning holes on the rotary actuator lug, and the lug of the rotary actuator and the side pressure plate are fixedly connected by the workpiece positioning pin assemblies. The measuring execution mechanism is installed on one side of the base, and a dial indicator is installed in the measuring execution mechanism. The measuring rod of the dial indicator passes into the workpiece receiving cavity of the base, and its end is in axial contact with the rotary actuator being measured.

[0008] In the aforementioned aircraft rotary actuator axial clearance measuring device, the diameter of the locating pin hole on the side pressure plate is larger than the outer diameter of the workpiece locating pin assembly.

[0009] The aforementioned axial clearance measuring device for the rotary actuator of an aircraft includes a workpiece positioning pin assembly comprising a positioning sleeve and a positioning pin. The positioning sleeve is placed in the positioning pin hole of the side pressure plate and is fixedly connected to the positioning pin hole by filling with adhesive. The positioning pin passes through the positioning sleeve and the positioning hole on the rotary actuator lug, and its end is connected to the corresponding component on the aircraft.

[0010] The aforementioned axial clearance measuring device for the aircraft rotary actuator includes a positioning pin with an operating handle, a positioning part, and a locking part. The operating handle is a cylindrical structure with anti-slip textures on its outer wall. The positioning part is located between the operating handle and the locking part and is a cylinder that mates with the inner hole of the positioning sleeve. The locking part is a cylindrical pin structure located at the tail end of the positioning pin.

[0011] In the aforementioned aircraft rotary actuator axial clearance measuring device, the locking part of the positioning pin matches the mounting hole of the rotary actuator lug on the aircraft fuselage.

[0012] The aforementioned axial clearance measuring device for the aircraft rotary actuator has a spiral groove provided on the outer wall of the positioning sleeve.

[0013] The aforementioned axial clearance measuring device for the aircraft rotary actuator has feet installed at the four corners of the base; the feet are hexagonal head bolts mounted on the base.

[0014] The aforementioned axial clearance measuring device for the aircraft rotary actuator further comprises a reference plate, a clamping seat, a spring sleeve, and a locking cap. The reference plate is fixedly installed on the left or right side wall of the base plate, and the clamping seat is installed in the middle of the reference plate. The clamping seat has a conical inner hole, and the outer wall of the clamping seat has a thread that mates with the locking cap. The clamping seat and the locking cap are assembled through a threaded connection structure. The spring sleeve is a conical sleeve with axial grooves on its side wall, which is installed in the conical inner hole of the clamping seat. Its inner hole is a cylindrical hole. The mounting part of the dial indicator is clamped in the inner hole of the spring sleeve. The dial indicator is clamped and fixed by applying radial pressure to the spring sleeve through the engagement of the locking cap and the clamping seat.

[0015] The aforementioned axial clearance measuring device for the aircraft rotary actuator has four sets of axial grooves on the outer wall of the spring sleeve, which are evenly arranged circumferentially, one of which is a radially penetrating slot.

[0016] The aforementioned axial clearance measuring device for the aircraft rotary actuator uses a spring sleeve made of H62 copper-zinc alloy.

[0017] This invention provides an axial clearance measuring device for an aircraft rotary actuator. The rotary actuator to be measured is positioned and clamped by the cooperation of a base, a side pressure plate, and a workpiece positioning pin assembly, so that it retains only the axial degree of freedom. When measuring the axial clearance of the rotary actuator, an axial push-pull force can be applied to one end of the workpiece being measured, and the axial movement distance of the workpiece is measured by a dial indicator in the measuring actuator. This measured value is the axial clearance of the rotary actuator. In this invention, the diameter of the locating pin hole on the side pressure plate is larger than the outer diameter of the workpiece locating pin assembly. A locating sleeve is installed in the workpiece locating pin assembly, and the locating sleeve is fixedly connected to the locating pin hole by applying adhesive. Before applying the adhesive, a rotary actuator (a new, unused part) manufactured by the original aircraft manufacturer is used as a standard sample. It is clamped in the workpiece receiving cavity of the base and then clamped and fixed by the side pressure plate. The locating sleeve is inserted into the locating pin hole of the side pressure plate, and the locating pin specification is selected so that the locking part at the end of the locating pin can reliably connect with the lug locating hole of the standard sample of the rotary actuator, and ensure that the locating part of the locating pin is in contact with the locating pin hole. The positioning sleeve is then fitted and fixed in place. Adhesive is then applied, and after the adhesive has solidified, the positioning pins and side pressure plates are removed, and the standard sample is taken out. The two rotary actuator workpieces to be tested are then replaced, and the axial clearance is measured. Thus, this invention employs a "pin-fixed sleeve, sleeve-fixed hole" method, ensuring the consistency between the positioning pin hole on the side pressure plate and the positioning hole on the original rotary actuator lug. This allows the axial clearance measurement of the rotary actuator to be performed under conditions simulating the theoretical state of the rotary actuator at the factory (without flexible deformation), thereby meeting the requirements of aircraft maintenance procedures and achieving the goal of ensuring the assembly quality after aircraft maintenance. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the rotary actuator structure of the leading edge flap drive system of an aircraft;

[0019] Figure 2 yes Figure 1 Schematic diagram of the cross-sectional structure of the middle AA section;

[0020] Figure 3 This is a schematic diagram of the axial clearance measuring device for the aircraft rotary actuator described in this invention;

[0021] Figure 4 yes Figure 3 Schematic diagram of the cross-sectional structure of the middle BB section;

[0022] Figure 5 This is the front view of the base in the axial clearance measuring device for the aircraft rotary actuator;

[0023] Figure 6 This is a side view of the base in the axial clearance measuring device for the aircraft rotary actuator;

[0024] Figure 7 This is the front view of the side pressure plate in the axial clearance measuring device for the aircraft rotary actuator;

[0025] Figure 8 yes Figure 7 Schematic diagram of the cross-sectional structure of the middle CC section;

[0026] Figure 9 This is a schematic diagram of the positioning pin structure in the axial clearance measuring device of the aircraft rotary actuator;

[0027] Figure 10 This is a schematic diagram of the positioning sleeve structure in the axial clearance measuring device of the aircraft rotary actuator;

[0028] Figure 11 This is a schematic diagram showing how the position of the positioning sleeve is determined using a standard sample;

[0029] Figure 12 This is a schematic diagram of the positioning sleeve being filled with adhesive;

[0030] Figure 13 This is a schematic diagram of measuring the axial clearance of a rotary actuator.

[0031] Figure 14 yes Figure 13 Enlarged view of the structure at point I;

[0032] Figure 15 This is a schematic diagram of the spring sleeve structure in the measuring actuator;

[0033] Figure 16 yes Figure 15 Side view;

[0034] Figure 17 yes Figure 15 Schematic diagram of the cross-sectional structure of the middle DD;

[0035] Figure 18 yes Figure 13 Side view.

[0036] Explanation of each label in the diagram:

[0037] 1 is a rotary actuator, and 1-1 is an ear plate;

[0038] 2 is a rotary actuator axial clearance measuring device.

[0039] 2-1 is the base, and 2-1-1 is the workpiece receiving cavity;

[0040] 2-2 is the side pressure plate, 2-2-1 is the positioning pin hole, and 2-2-2 is the mating surface;

[0041] 2-3 is the positioning pin, 2-3-1 is the operating handle, 2-3-2 is the positioning part, and 2-3-3 is the locking part;

[0042] 2-4 is the positioning sleeve, and 2-4-1 is the spiral groove;

[0043] 2-5 are support legs;

[0044] 2-6 is the measuring actuator, 2-6-1 is the dial indicator, 2-6-2 is the clamping seat, 2-6-3 is the locking cap, 2-6-4 is the spring sleeve, 2-6-4a is the axial groove, 2-6-4b is the radial through slot, and 2-6-5 is the reference plate;

[0045] 3 represents the adhesive. Detailed Implementation

[0046] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0047] See Figure 1. Figure 2 In the aircraft's leading-edge flap drive system, the rotary actuator 1 is a jointed flexible connection structure. During takeoff and landing, the wing is subjected to significant air resistance. The rotary actuator 1 responds by... Figure 1 The flexible deformation of curves I to IV shown in the diagram releases the deformation energy generated by external air forces. Nine sets of lugs 1-1 are provided on both sides of the rotary actuator 1, connecting to other mechanisms on the aircraft. Each set of lugs consists of two opposing parts. The two opposing parts of the upper four sets of lugs are at a certain angle (8°36′±15′) to the horizontal plane, while the two opposing parts of the lower five sets of lugs are parallel to the horizontal plane. After a certain flight time, the positioning holes and internal parts of the rotary actuator 1 lugs 1-1 will wear to varying degrees, causing some parameters of the rotary actuator 1 to exceed the set range. Therefore, during aircraft maintenance, the rotary actuator 1 needs to be disassembled, severely worn or expired parts replaced, and the axial clearance of the reassembled rotary actuator measured to determine if it meets the technical requirement of 0.10–0.15 mm.

[0048] See Figure 1 , Figure 2 , Figure 3 , Figure 4According to the operational specifications for aircraft maintenance, the measurement of the axial clearance of a rotary actuator should be performed under conditions simulating the theoretical state of the rotary actuator at the time of manufacture (without flexible deformation). This means that the relevant dimensions and tolerances, such as the hole spacing between adjacent sets of lugs (45±0.1mm), the angle of one lug (8°36′±15′), flatness (≤0.05mm), and coaxiality (<0.1mm), must be consistent with those at the time of manufacture. To meet these requirements, this invention provides an axial clearance measuring device 2 for rotary actuators in aircraft. It uses a base 2-1, a side pressure plate 2-2, and a workpiece positioning pin assembly to position and clamp the rotary actuator 1 to be measured, ensuring it retains only axial freedom. When measuring the axial clearance of the rotary actuator 1, an axial pushing or pulling force can be applied to one end of the workpiece. The axial movement distance of the workpiece is measured using a dial indicator in the measuring actuator mechanism; this measured value is the axial clearance of the rotary actuator.

[0049] See Figure 3 , Figure 4 , Figure 5 , Figure 6 The rotary actuator axial clearance measuring device 2 of the present invention includes a workpiece clamping and positioning mechanism and a measuring and executing mechanism 2-6; the workpiece clamping and positioning mechanism is provided with a base 2-1, a side pressure plate 2-2 and a workpiece positioning pin assembly, the base 2-1 is a box frame structure, a workpiece receiving cavity 2-1-1 is provided in the middle of the base 2-1, and support legs 2-5 are provided at the four corners of the base 2-1, the support legs 2-5 are hexagonal head bolts installed on the base 2-1.

[0050] See Figure 3 , Figure 4 , Figure 7 , Figure 8 The rotary actuator axial clearance measuring device 2 of the present invention has a side pressure plate 2-2 comprising two symmetrically arranged parts, which are respectively installed on the front and rear surfaces of the base 2-1. Each part is provided with a positioning pin hole 2-2-1 corresponding to the positioning hole on the lug 1-1 of the rotary actuator 1, and a mating surface 2-2-2 matching the angle of the lug 1 of the rotary actuator 1 is provided on the inner side of each part.

[0051] See Figure 2 , Figure 4 , Figure 9 , Figure 10The rotary actuator axial clearance measuring device 2 of the present invention includes a workpiece positioning pin assembly comprising a positioning sleeve 2-4 and a positioning pin 2-3. The positioning sleeve 2-4 is placed in the positioning pin hole 2-2-1 of the side pressure plate 2-2, and a spiral groove 2-4-1 is provided on its outer side wall. It is fixedly connected to the positioning pin hole 2-2-1 by filling with adhesive 3. The positioning pin 2-3 is provided with an operating handle 2-3-1, a positioning part 2-3-2, and a locking part 2-3-3. The operating handle 2-3-1 has a cylindrical structure. The outer wall is provided with anti-slip texture. The positioning part 2-3-2 is located between the operating handle 2-3-1 and the locking part 2-3-3. It is a cylinder that fits into the inner hole of the positioning sleeve 2-4. The locking part 2-3-3 is a cylindrical pin structure located at the tail end of the positioning pin 2-3. The positioning part 2-3-2 of the positioning pin 2-3 passes through the positioning sleeve 2-4. The locking part 2-3-3 of the positioning pin 2-3 passes through the positioning hole on the lug 1-1 of the rotary actuator 1. Its end matches the mounting hole of the rotary actuator lug on the aircraft body.

[0052] See Figures 13 to 18 The rotary actuator axial clearance measuring device 2 of the present invention further includes a reference plate 2-6-5, a clamping seat 2-6-2, a spring sleeve 2-6-4, and a locking cap 2-6-3 in its measuring execution mechanism 2-6. The reference plate 2-6-5 is fixedly installed on the left or right side wall of the base plate 2-1, and the clamping seat 2-6-2 is installed in the middle of the reference plate 2-6-5. The clamping seat 2-6-2 has a conical inner hole, and the outer wall of the clamping seat 2-6-2 has a thread that mates with the locking cap 2-6-3. The clamping seat 2-6-2 and the locking cap 2-6-3 are assembled through a threaded connection structure. The spring... Sleeve 2-6-4 is a conical sleeve structure made of H62 copper-zinc alloy. It has four sets of axial grooves 2-6-4a evenly arranged circumferentially on its side wall, one of which is a radially penetrating notch 2-6-4b. Spring sleeve 2-6-4 is installed in the conical inner hole of clamping seat 2-6-2. The inner hole is a cylindrical hole. The mounting part of dial indicator 2-6-1 is clamped in the inner hole of spring sleeve 2-6-4. By locking cap 2-6-3 cooperating with clamping seat 2-6-2, radial pressure is applied to spring sleeve 2-6-4, causing spring sleeve 2-6-4 to undergo radial contraction deformation, thereby clamping and fixing dial indicator 2-6-1.

[0053] See Figures 1 to 18 The rotary actuator axial clearance measuring device 2 of the present invention, when performing axial clearance measurement of the aircraft rotary actuator, first uses the original rotary actuator (unused new part) manufactured by the aircraft manufacturer as a standard sample, places it in the workpiece receiving cavity 2-1-1 of the base 2-1, and then clamps and fixes it by the side pressure plate 2-2 (as shown in the attached figure). Figure 11(As shown); Insert the positioning sleeve 2-4 into the positioning pin hole 2-2-1 of the side pressure plate 2-2, and select the appropriate positioning pin 2-3 to ensure that the locking part 2-3-3 at the end of the positioning pin 2-3 can reliably connect with the lug positioning hole of the standard sample of the rotary actuator, and ensure that the positioning part 2-3-2 of the positioning pin 2-3 fits into the inner hole of the positioning sleeve 2-4. At this time, the positioning sleeve 2-4 is positioned and fixed; Perform the adhesive filling operation (as shown in the attached). Figure 12 As shown), adhesive 3 flows along the spiral groove 2-4-1 on the outer wall of the positioning sleeve 2-4, filling the gap between the positioning sleeve 2-4 and the positioning pin hole 2-2-1 of the side pressure plate 2-2. After the adhesive 3 cures, remove the positioning pin 2-3 and the side pressure plate 2-2, and take out the standard sample. Replace it with the rotary actuator 1 to be tested. Position and clamp the rotary actuator 1 through the cooperation of the base 2-1, the side pressure plate 2-2 and the workpiece positioning pin assembly, so that it retains only the axial degree of freedom (as shown in the attached figure). Figure 13 (As shown); then install the measuring actuator 2-6 on the left or right outer wall of the base 2-1, apply an axial push-pull force to one end of the rotary actuator 1 to be measured, and measure the axial movement distance of the rotary actuator 1 through the dial indicator 2-6-1 in the measuring actuator 2-6. This measured value is the axial clearance of the rotary actuator 1 to be measured.

Claims

1. An axial clearance measuring device for a flexible connecting shaft, characterized in that: The rotary actuator axial clearance measuring device (2) includes a workpiece clamping and positioning mechanism and a measuring execution mechanism (2-6); the workpiece clamping and positioning mechanism is provided with a base (2-1), a side pressure plate (2-2) and a workpiece positioning pin assembly. The base (2-1) is a box frame structure, and a workpiece receiving cavity (2-1-1) is provided in the middle of the base (2-1); the side pressure plate (2-2) includes two parts arranged symmetrically front and back, which are respectively installed on the front and rear surfaces of the base (2-1). Each part is provided with a positioning pin hole (2-2-1) corresponding to the positioning hole on the lug (1-1) of the rotary actuator (1), and the inner side of each part is provided with a positioning pin hole (2-2-1) corresponding to the positioning hole on the lug (1-1) of the rotary actuator (1). The contact surface (2-2-2) of the lug of the rotary actuator (1) is matched with the angle of the lug; the number of the workpiece positioning pin assembly is consistent with the number of positioning holes on the lug (1-1) of the rotary actuator (1), and the lug (1-1) and the side pressure plate (2-2) of the rotary actuator (1) are fixedly connected by the workpiece positioning pin assembly; the measuring execution mechanism (2-6) is installed on one side of the base (2-1), and a dial indicator (2-6-1) is set in the measuring execution mechanism (2-6). The measuring rod of the dial indicator (2-6-1) is inserted into the workpiece receiving cavity (2-1-1) of the base (2-1), and its end is in axial contact with the rotary actuator (1) being measured.

2. The axial clearance measuring device for a flexible connecting shaft according to claim 1, characterized in that: The diameter of the positioning pin hole (2-2-1) on the side pressure plate (2-2) is larger than the outer diameter of the workpiece positioning pin assembly.

3. The axial clearance measuring device for a flexible connecting shaft according to claim 2, characterized in that: The workpiece positioning pin assembly includes a positioning sleeve (2-4) and a positioning pin (2-3); the positioning sleeve (2-4) is placed in the positioning pin hole (2-2-1) of the side pressure plate (2-2) and is fixedly connected to the positioning pin hole (2-2-1) by filling with adhesive (3); the positioning pin (2-3) passes through the positioning hole on the positioning sleeve (2-4) and the lug (1-1) of the rotary actuator (1), and its end is connected to the corresponding part on the aircraft.

4. The axial clearance measuring device for a flexible connecting shaft according to claim 3, characterized in that: The positioning pin (2-3) is provided with an operating handle (2-3-1), a positioning part (2-3-2), and a locking part (2-3-3); the operating handle (2-3-1) is a cylindrical structure with anti-slip texture on its outer wall; the positioning part (2-3-2) is located between the operating handle (2-3-1) and the locking part (2-3-3), and is a cylinder that fits into the inner hole of the positioning sleeve (2-4); the locking part (2-3-3) is a cylindrical pin structure located at the tail end of the positioning pin (2-3).

5. The axial clearance measuring device for a flexible connecting shaft according to claim 4, characterized in that: The locking part of the positioning pin (2-3) matches the mounting hole of the lug (1-1) of the rotary actuator (1) on the aircraft body.

6. The axial clearance measuring device for a flexible connecting shaft according to claim 3, 4, or 5, characterized in that: A spiral groove (2-4-1) is provided on the outer wall of the positioning sleeve (2-4).

7. The axial clearance measuring device for a flexible connecting shaft according to claim 6, characterized in that: Support legs (2-5) are provided at the four corners of the base (2-1); the support legs (2-5) are hexagonal head bolts installed on the base (2-1).

8. The axial clearance measuring device for a flexible connecting shaft according to claim 6, characterized in that: The measuring actuator (2-6) also includes a reference plate (2-6-5), a clamping seat (2-6-2), a spring sleeve (2-6-4), and a locking cap (2-6-3). The reference plate (2-6-5) is fixedly installed on the left or right side wall of the base (2-1), and the clamping seat (2-6-2) is installed in the middle of the reference plate (2-6-5). The clamping seat (2-6-2) has a conical inner hole, and the outer wall of the clamping seat (2-6-2) has a thread that mates with the locking cap (2-6-3). -2) It is assembled with the locking cap (2-6-3) through a threaded connection structure; the spring sleeve (2-6-4) is a conical sleeve with an axial groove (2-6-4a) on the side wall, which is installed in the conical inner hole of the clamping seat (2-6-2). Its inner hole is a cylindrical hole. The mounting part of the dial indicator (2-6-1) is clamped in the inner hole of the spring sleeve (2-6-4). The locking cap (2-6-3) and the clamping seat (2-6-2) cooperate to apply radial pressure to the spring sleeve (2-6-4) to clamp and fix the dial indicator (2-6-1).

9. The axial clearance measuring device for a flexible connecting shaft according to claim 8, characterized in that: The spring sleeve (2-6-4) has four sets of axial grooves (2-6-4a) on its outer wall, which are evenly arranged in the circumferential direction. One set is a radially penetrating slot (2-6-4b).

10. The axial clearance measuring device for a flexible connecting shaft according to claim 9, characterized in that: The spring sleeve (2-6-4) is made of H62 copper-zinc alloy.

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