CN219037844U - Axial clearance measuring device for flexible connecting shaft - Google Patents
Axial clearance measuring device for flexible connecting shaft Download PDFInfo
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- CN219037844U CN219037844U CN202222488602.9U CN202222488602U CN219037844U CN 219037844 U CN219037844 U CN 219037844U CN 202222488602 U CN202222488602 U CN 202222488602U CN 219037844 U CN219037844 U CN 219037844U
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Abstract
An axial clearance measuring device for a flexible connecting shaft comprises a workpiece clamping and positioning mechanism and a measuring executing mechanism; the workpiece clamping and positioning mechanism is provided with a base, a side pressing plate and a workpiece positioning pin assembly, and a workpiece accommodating cavity is formed in the middle of the base; the side pressure plate comprises two parts which are arranged in a front-back symmetrical way, the two parts are respectively arranged on the front elevation and the back elevation of the base, each part is provided with a positioning pin hole corresponding to a positioning hole on the lug of the rotary actuator, and the inner side of each part is provided with an attaching surface which is matched with the lug angle of the rotary actuator; the number of the workpiece positioning pin assemblies is consistent with that of the positioning holes on the rotary actuator lugs, and the rotary actuator lugs are fixedly connected with the side pressure plates through the workpiece positioning pin assemblies; the measuring executing mechanism is arranged on one side of the base, and a dial indicator is arranged in the measuring executing mechanism. The utility model meets the requirement of the maintenance operation standard of the aircraft and achieves the purpose of ensuring the assembly quality of the aircraft after maintenance.
Description
Technical Field
The utility model relates to a measuring device, in particular to an axial clearance measuring device for a flexible connecting shaft.
Background
In the process of taking off and landing of an aircraft, the wing is subjected to huge air external force, as shown in figures 1 and 2, in order to reduce the internal stress generated by the wing under the action of the air external force, the wing is stressed and deformed within a safe value range, and an aircraft manufacturer designs a rotary actuator 1 in a leading edge flap driving system into a joint-shaped flexible connection structure, so that the rotary actuator 1 can generate flexible deformation in the shape of I-IV curves as shown in figure 1 under the condition of the wing stress, and energy generated by the action of the air external force is released.
As shown in fig. 1 and 2, nine sets of lugs 1-1 connected with other mechanisms are arranged on two sides of a rotary actuator 1 in the front edge flap driving system of an aircraft, each set of lugs consists of two parts which are oppositely arranged, wherein the two parts which are oppositely arranged in the four upper sets of lugs form a certain inclination angle (8 degrees 36'±15') with the horizontal plane, the two parts which are oppositely arranged in the five lower sets of lugs are parallel to the horizontal plane, after the aircraft passes a certain flight time, the locating holes and internal parts on the lugs 1-1 of the rotary actuator 1 are worn to different degrees, so that certain index parameters of the rotary actuator 1 exceed a set range, therefore, when the aircraft is overhauled, parts with serious wear and due service life are needed to be replaced, after the aircraft is reassembled, the axial movement clearance of the rotary actuator is also needed to be measured, so as to judge whether the technical requirement of 0.10-0.15 mm of the axial movement clearance is met.
According to the maintenance operation standard of the aircraft, the measurement of the axial movement clearance of the rotary actuator is carried out under the theoretical state (without flexible deformation) when the rotary actuator is simulated to leave the factory, namely, the relative dimensions and tolerances such as the hole pitch dimension (45+/-0.1 mm), the one-side lug angle (8 degrees 36 '+/-15'), the flatness (less than or equal to 0.05 mm), the coaxiality (less than 0.1 mm) and the like of two adjacent sets of lugs of the rotary actuator are required to be consistent with those when the rotary actuator leaves the factory. Therefore, an axial clearance measuring device for the flexible connecting shaft needs to be designed so as to meet the requirement of the maintenance operation standard of the aircraft and ensure the assembly quality of the aircraft after maintenance.
Disclosure of Invention
The utility model provides an axial clearance measuring device for a flexible connecting shaft, which aims to meet the requirement of an aircraft overhaul operation standard by innovative design of a workpiece clamping and positioning mechanism and a measuring and executing mechanism and achieve the aim of ensuring the assembly quality after the aircraft overhaul.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
an axial clearance measuring device for a flexible connecting shaft comprises a workpiece clamping and positioning mechanism and a measuring executing mechanism; the workpiece clamping and positioning mechanism is provided with a base, a side pressing plate and a workpiece positioning pin assembly, wherein the base is of a box frame structure, and a workpiece accommodating cavity is formed in the middle of the base; the side pressure plate comprises two parts which are arranged in a front-back symmetrical way, the two parts are respectively arranged on the front elevation and the back elevation of the base, each part is provided with a positioning pin hole corresponding to a positioning hole on the lug of the rotary actuator, and the inner side of each part is provided with an attaching surface which is matched with the lug angle of the rotary actuator; the number of the workpiece locating pin assemblies is consistent with that of the locating holes in the lugs of the rotary actuator, and the lugs of the rotary actuator are fixedly connected with the side pressing plate through the workpiece locating pin assemblies; the measuring actuating mechanism is arranged on one side of the base, the dial indicator is arranged in the measuring actuating mechanism, a measuring rod of the dial indicator penetrates into a workpiece accommodating cavity of the base, and the tail end of the measuring rod is axially abutted to the measured rotary actuator.
According to the axial clearance measuring device for the flexible connecting shaft, the diameter size of the positioning pin hole on the side pressing plate is larger than the outer diameter size of the workpiece positioning pin assembly.
The workpiece positioning pin assembly comprises a positioning sleeve and a positioning pin; the positioning sleeve is arranged in the positioning pin hole of the side pressing plate and is fixedly connected with the positioning pin hole by filling adhesive; the locating pin passes through locating holes on the locating sleeve and the lug plate of the rotary actuator, and the tail end of the locating pin is connected with a corresponding part on the aircraft.
The axial clearance measuring device for the flexible connecting shaft is characterized in that the positioning pin is provided with an operating handle, a positioning part and a locking part; the operating handle is of a cylindrical structure, and the outer wall of the operating handle is provided with anti-skid textures; the positioning part is positioned between the operating handle and the locking part and is a cylinder matched with the inner hole of the positioning sleeve; the locking part is of a cylindrical pin structure and is positioned at the tail end of the locating pin.
According to the axial clearance measuring device for the flexible connecting shaft, the locking part of the locating pin is matched with the assembly hole of the lug of the rotary actuator on the aircraft body.
According to the axial clearance measuring device for the flexible connecting shaft, the spiral groove is formed in the outer side wall of the positioning sleeve.
The axial clearance measuring device for the flexible connecting shaft is characterized in that the four corners of the base are provided with the supporting feet; the support legs are hexagon head bolts arranged on the base.
The axial clearance measuring device for the flexible connecting shaft is characterized in that the measuring executing mechanism is further provided with a reference plate, a clamping seat, a spring sleeve and a locking cap; the reference plate is fixedly arranged on the left side wall or the right side wall of the base, and the clamping seat is arranged in the middle of the reference plate; the clamping seat is provided with a conical inner hole, the outer wall of the clamping seat is provided with threads matched with the locking cap, and the clamping seat and the locking cap are assembled through a threaded connection structure; the spring sleeve is a conical sleeve with an axial groove on the side wall, the conical sleeve is arranged in a conical inner hole of the clamping seat, the inner hole is a cylindrical hole, the mounting part of the dial indicator is clamped in the inner hole of the spring sleeve, and radial pressure is applied to the spring sleeve through the matching of the locking cap and the clamping seat to clamp and fix the dial indicator.
According to the axial clearance measuring device for the flexible connecting shaft, the number of the axial grooves on the outer wall of the spring sleeve is four, the four groups of the axial grooves are uniformly distributed along the circumferential direction, and one group of the axial grooves is a radial through groove.
According to the axial clearance measuring device for the flexible connecting shaft, the spring sleeve is made of H62 copper-zinc alloy materials.
The utility model provides an axial clearance measuring device for a flexible connecting shaft, which is used for positioning and clamping a rotary actuator to be measured through the cooperation of a base, a side pressure plate and a workpiece positioning pin assembly, so that only axial freedom degree is reserved, when axial clearance measurement is carried out on the rotary actuator, axial push-pull force can be applied to one end of a measured workpiece, and the axial movement distance of the workpiece is measured through a dial indicator in a measurement executing mechanism, wherein the measured value is the axial clearance of the rotary actuator. In the structure, the diameter size of a positioning pin hole on a side pressing plate is larger than the outer diameter size of a workpiece positioning pin assembly, a positioning sleeve is arranged in the workpiece positioning pin assembly, the positioning sleeve is fixedly connected with the positioning pin hole through adhesive filling, and before adhesive filling operation, a rotary actuator (a new piece which is not used) produced by an aircraft factory is firstly utilized as a standard sample piece, and is clamped in a workpiece accommodating cavity of a base and then clamped and fixed through the side pressing plate; penetrating the positioning sleeve into the positioning pin hole of the side pressing plate, selecting and matching the specification of the positioning pin, enabling the locking part at the tail end of the positioning pin to be reliably connected with the lug positioning hole of the standard sample piece of the rotary actuator, and ensuring that the positioning part of the positioning pin is attached to the positioning sleeve, wherein the positioning sleeve is positioned and fixed; filling the adhesive, removing the positioning pin and the side pressing plate after the adhesive is solidified, and taking out the standard sample; changing the workpiece of the rotary actuator to be tested and measuring the axial clearance; therefore, the utility model adopts a pin sleeve and a sleeve fixing hole mode, ensures the consistency of the positions of the positioning pin holes on the side pressing plates and the positioning holes on the lugs of the rotary actuator of the original factory, and enables the axial clearance measurement of the rotary actuator to be carried out in a theoretical state (without flexible deformation) when the rotary actuator is simulated to leave a factory, thereby meeting the requirement of the maintenance operation standard of the aircraft and achieving the purpose of ensuring the assembly quality after the maintenance of the aircraft.
Drawings
FIG. 1 is a schematic illustration of the configuration of a rotary actuator of an aircraft leading edge flap drive system;
FIG. 2 is a schematic view of the cross-sectional structure A-A of FIG. 1;
FIG. 3 is a schematic view of an axial gap measurement device for a flexible connection shaft in accordance with the present utility model;
FIG. 4 is a schematic view of the cross-sectional structure B-B in FIG. 3;
FIG. 5 is a front view of a base in an axial gap measurement device for a flexible connection shaft;
FIG. 6 is a side view of a base in an axial gap measurement device for a flexible connection shaft;
FIG. 7 is a front view of a side pressure plate in an axial gap measurement device for a flexible connection shaft;
FIG. 8 is a schematic view of the cross-sectional structure of C-C in FIG. 7;
FIG. 9 is a schematic view of the structure of a locating pin in an axial clearance measurement device for a flexible connection shaft;
FIG. 10 is a schematic view of the positioning sleeve structure in an axial clearance measurement device for a flexible connection shaft;
FIG. 11 is a schematic illustration of the determination of the position of a spacer sleeve by a master sample;
FIG. 12 is a schematic illustration of a spacer collar filled adhesive;
FIG. 13 is a schematic illustration of measuring the axial clearance of a rotary actuator;
FIG. 14 is an enlarged view of the structure shown at I in FIG. 13;
FIG. 15 is a schematic view of the spring case structure of the measurement actuator;
FIG. 16 is a side view of FIG. 15;
FIG. 17 is a schematic view of the structure of section D-D in FIG. 15;
fig. 18 is a side view of fig. 13.
The reference numerals in the drawings are defined as follows:
1 is a rotary actuator, 1-1 is an ear piece;
2 is an axial clearance measuring device of a rotary actuator
2-1 is a base, and 2-1-1 is a workpiece accommodating cavity;
2-2 is a side pressure plate, 2-2-1 is a positioning pin hole, and 2-2-2 is a bonding surface;
2-3 is a locating pin, 2-3-1 is an operating handle, 2-3-2 is a locating part, and 2-3-3 is a locking part;
2-4 is a positioning sleeve, and 2-4-1 is a spiral groove;
2-5 are supporting legs;
2-6 is a measurement executing mechanism, 2-6-1 is a dial indicator, 2-6-2 is a clamping seat, 2-6-3 is a locking cap, 2-6-4 is a spring sleeve, 2-6-4a is an axial groove, 2-6-4b is a radial through notch, and 2-6-5 is a reference plate;
3 is a viscose.
Detailed Description
The utility model will be further described with reference to the accompanying drawings and specific examples.
Referring to fig. 1 and 2, a rotary actuator 1 in a leading edge flap driving system of an aircraft is of an articulated flexible connection structure, wings are affected by huge air resistance during take-off and landing of the aircraft, and the rotary actuator 1 releases deformation energy generated by the action of external air force through flexible deformation of a curve shape of i-iv as shown in fig. 1. Nine groups of lugs 1-1 connected with other mechanisms on the aircraft are arranged on two sides of the rotary actuator 1, each group of lugs consists of two parts which are oppositely arranged, wherein the two parts which are oppositely arranged in the four groups of lugs on the upper part form a certain inclination angle (8 degrees 36 '+/-15') with the horizontal plane, the two parts which are oppositely arranged in the five groups of lugs on the lower part are parallel to the horizontal plane, after the aircraft passes a certain flight time, the locating holes and internal parts on the lugs 1-1 of the rotary actuator 1 are worn to different extents, so that certain index parameters of the rotary actuator 1 exceed a set range, and therefore, when the aircraft is overhauled, the rotary actuator 1 needs to be disassembled, parts with serious wear and due service life are replaced, and then the axial movement clearance of the assembled rotary actuator is measured to judge whether the technical requirement that the axial movement clearance is 0.10-0.15 mm is met.
Referring to fig. 1, 2, 3 and 4, according to the operation specification of aircraft overhaul, the measurement of the axial movement clearance of the rotary actuator should be performed under the theoretical state (without flexible deformation) when the rotary actuator is simulated to leave the factory, namely, the relative dimensions and tolerances of the adjacent two sets of lugs of the rotary actuator such as the hole pitch dimension (45+/-0.1 mm), the angle of one lug (8+/-15'), the flatness (less than or equal to 0.05 mm), the coaxiality (less than 0.1 mm) and the like must be ensured to be consistent with those when leaving the factory. In order to meet the requirements, the utility model provides an axial clearance measuring device 2 for a rotary actuator of an aircraft, which positions and clamps the rotary actuator 1 to be measured through the cooperation of a base 2-1, a side pressure plate 2-2 and a workpiece positioning pin assembly, so that only axial freedom degree is reserved, when axial clearance measurement is carried out on a workpiece of the rotary actuator 1, axial push-pull force can be applied to one end of the workpiece, and the axial movement distance of the workpiece is measured through a dial indicator in a measuring executing mechanism, wherein the measured value is the axial clearance of the rotary actuator.
Referring to fig. 3, 4, 5 and 6, the axial clearance measuring device 2 of the rotary actuator according to the present utility model comprises a workpiece clamping and positioning mechanism and a measuring actuator 2-6; the workpiece clamping and positioning mechanism is provided with a base 2-1, a side pressing plate 2-2 and a workpiece positioning pin assembly, wherein the base 2-1 is of a box body frame structure, a workpiece accommodating cavity 2-1-1 is arranged in the middle of the base 2-1, supporting feet 2-5 are arranged at four corners of the base 2-1, and the supporting feet 2-5 are hexagon head bolts arranged on the base 2-1.
Referring to fig. 3, 4, 7 and 8, the axial clearance measuring device 2 for a rotary actuator according to the present utility model includes two parts symmetrically arranged in front and rear, a side pressure plate 2-2 mounted on front and rear vertical surfaces of a base 2-1, a positioning pin hole 2-2-1 corresponding to a positioning hole on an ear piece 1-1 of the rotary actuator 1 disposed on each part, and an attaching surface 2-2-2 matching an angle of the ear piece 1 of the rotary actuator disposed on an inner side of each part.
Referring to fig. 2, 4, 9 and 10, the axial clearance measuring device 2 of the rotary actuator according to the present utility model comprises a workpiece positioning pin assembly including a positioning sleeve 2-4 and a positioning pin 2-3; the positioning sleeve 2-4 is arranged in a positioning pin hole 2-2-1 of the side pressing plate 2-2, a spiral groove 2-4-1 is arranged on the outer side wall of the positioning sleeve, and the positioning sleeve is fixedly connected with the positioning pin hole 2-2-1 by filling adhesive 3; the locating pin 2-3 is provided with an operating handle 2-3-1, a locating part 2-3-2 and a locking part 2-3-3, the operating handle 2-3-1 is of a cylindrical structure, anti-slip textures are arranged on the outer wall of the operating handle, the locating part 2-3-2 is located between the operating handle 2-3-1 and the locking part 2-3, and is of a cylinder matched with an inner hole of the locating sleeve 2-4, the locking part 2-3 is of a cylindrical pin structure and is located at the tail end of the locating pin 2-3, the locating part 2-3-2 of the locating pin 2-3 penetrates through the locating sleeve 2-4, and the locking part 2-3-3 of the locating pin 2-3 penetrates through a locating hole in the lug 1-1 of the rotary actuator 1.
Referring to fig. 13 to 18, the axial clearance measuring device 2 of the rotary actuator of the present utility model is further provided with a reference plate 2-6-5, a clamping seat 2-6-2, a spring housing 2-6-4 and a locking cap 2-6-3 in a measuring actuator 2-6 thereof; the reference plate 2-6-5 is fixedly arranged on the left side wall or the right side wall of the base 2-1, and the clamping seat 2-6-2 is arranged in the middle of the reference plate 2-6-5; the clamping seat 2-6-2 is provided with a conical inner hole, the outer wall of the clamping seat 2-6-2 is provided with threads matched with the locking cap 2-6-3, and 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 of a conical sleeve structure, an H62 copper zinc alloy material is adopted, four groups of axial grooves 2-6-4a which are uniformly distributed along the circumferential direction are formed in the side wall of the spring sleeve, one group of the axial grooves is a radial through notch 2-6-4b, the spring sleeve 2-6-4 is installed in a conical inner hole of the clamping seat 2-6-2, the inner hole of the spring sleeve is a cylindrical hole, the installation part of the dial indicator 2-6-1 is clamped in the inner hole of the spring sleeve 2-6-4, radial pressure is applied to the spring sleeve 2-6-4 through the matching of the locking cap 2-6-3 and the clamping seat 2-6-2, and radial shrinkage deformation is generated on the spring sleeve 2-6-4, so that the dial indicator 2-6-1 is clamped and fixed.
Referring to fig. 1 to 18, when the axial clearance measuring device 2 for the rotary actuator of the present utility model performs an axial clearance measuring operation for the rotary actuator of an aircraft, firstly, the rotary actuator (an unused new piece) produced by an aircraft factory is used as a standard sample, and is placed in the workpiece accommodating cavity 2-1-1 of the base 2-1, and then is clamped and fixed by the side pressing plate 2-2 (as shown in fig. 11); penetrating a positioning sleeve 2-4 into a positioning pin hole 2-2-1 of a side pressing plate 2-2, selecting and matching a positioning pin 2-3 specification, enabling a locking part 2-3-3 at the tail end of the positioning pin 2-3 to be reliably connected with a positioning hole on a standard sample piece of a rotary actuator, and ensuring that the positioning part 2-3-2 of the positioning pin 2-3 is attached to an inner hole of the positioning sleeve 2-4, wherein the positioning sleeve 2-4 is positioned and fixed; filling the adhesive (as shown in figure 12), wherein the adhesive 3 flows along the spiral groove 2-4-1 on the outer wall of the positioning sleeve 2-4, so that the adhesive 3 fills the gap between the positioning sleeve 2-4 and the positioning pin hole 2-2-1 of the side pressing plate 2-2, and after the adhesive 3 is solidified, the positioning pin 2-3 and the side pressing plate 2-2 are removed, and the standard sample is taken out; the rotary actuator 1 to be tested is replaced, and the rotary actuator 1 is positioned and clamped through the cooperation of the base 2-1, the side pressure plate 2-2 and the workpiece positioning pin assembly, so that only the axial freedom degree is reserved (as shown in fig. 13); and then the measuring actuator 2-6 is arranged on the left side or the right side outer wall of the base 2-1, axial push-pull force is applied to one end of the measured rotary actuator 1, and the axial moving distance of the rotary actuator 1 is measured through the dial indicator 2-6-1 in the measuring actuator 2-6, and the measured value is the axial clearance of the measured rotary actuator 1.
Claims (10)
1. An axial clearance measuring device for a flexible connection shaft, characterized in that: the rotary actuator axial clearance measuring device (2) comprises a workpiece clamping and positioning mechanism and a measuring 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, wherein the base (2-1) is of a box frame structure, and a workpiece accommodating cavity (2-1-1) is arranged in the middle of the base (2-1); the side pressure plate (2-2) comprises two parts which are arranged in a front-back symmetrical way, the two parts are respectively arranged on the front elevation and the back elevation of the base (2-1), each part is provided with a positioning pin hole (2-2-1) corresponding to a positioning hole on the lug (1-1) of the rotary actuator (1), and the inner side of each part is provided with an attaching surface (2-2-2) which is matched with the lug angle of the rotary actuator (1); the number of the workpiece locating pin assemblies is consistent with the number of locating holes in lugs (1-1) of the rotary actuator (1), and the lugs (1-1) of the rotary actuator (1) are fixedly connected with the side pressure plate (2-2) through the workpiece locating pin assemblies; the measuring executing mechanism (2-6) is arranged on one side of the base (2-1), the dial indicator (2-6-1) is arranged in the measuring executing mechanism (2-6), a measuring rod of the dial indicator (2-6-1) penetrates into the workpiece accommodating cavity (2-1-1) of the base (2-1), and the tail end of the measuring rod axially abuts against the measured rotary actuator (1).
2. The axial gap measurement device for a flexible connection shaft as claimed in claim 1, wherein: the diameter size of the locating pin hole (2-2-1) on the side pressure plate (2-2) is larger than the outer diameter size of the workpiece locating pin assembly.
3. The axial gap measurement device for a flexible connection shaft as claimed in claim 2, wherein: the workpiece locating pin assembly comprises a locating sleeve (2-4) and a locating pin (2-3); the positioning sleeve (2-4) is arranged in the positioning pin hole (2-2-1) of the side pressing plate (2-2) and is fixedly connected with the positioning pin hole (2-2-1) by filling the adhesive (3); the locating pin (2-3) passes through locating holes on the locating sleeve (2-4) and the lug (1-1) of the rotary actuator (1), and the tail end of the locating pin is connected with corresponding parts on the aircraft.
4. An axial gap measuring device for a flexible connection shaft as claimed in claim 3, wherein: 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 of a cylindrical structure, and the outer wall of the operating handle is provided with anti-skid textures; the positioning part (2-3-2) is positioned between the operating handle (2-3-1) and the locking part (2-3-3) and is a cylinder matched with the inner hole of the positioning sleeve (2-4); the locking part (2-3-3) is of a cylindrical pin structure and is positioned at the tail end of the positioning pin (2-3).
5. The axial gap measurement device for a flexible connection shaft as claimed in claim 4, wherein: the locking part of the locating pin (2-3) is matched with the assembly hole of the lug (1-1) of the rotary actuator (1) on the aircraft body.
6. The axial gap measuring device for a flexible connection shaft as claimed in claim 3 or 4 or 5, wherein: the outer side wall of the locating sleeve (2-4) is provided with a spiral groove (2-4-1).
7. The axial gap measurement device for a flexible connection shaft as claimed in claim 6, wherein: the four corners of the base (2-1) are provided with supporting feet (2-5); the support legs (2-5) are hexagon head bolts arranged on the base (2-1).
8. The axial gap measurement device for a flexible connection shaft as claimed in claim 6, wherein: the measuring executing mechanism (2-6) is also provided with 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 arranged on the left side wall or the right side wall of the base (2-1), and the clamping seat (2-6-2) is arranged in the middle of the reference plate (2-6-5); the clamping seat (2-6-2) is provided with a conical inner hole, the outer wall of the clamping seat (2-6-2) is provided with threads matched with the locking cap (2-6-3), and 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 with an axial groove (2-6-4 a) on the side wall, the conical sleeve is arranged in a conical inner hole of the clamping seat (2-6-2), the 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), and the radial pressure is applied to the spring sleeve (2-6-4) through the matching of the locking cap (2-6-3) and the clamping seat (2-6-2) to clamp and fix the dial indicator (2-6-1).
9. The axial gap measurement device for a flexible connection shaft as claimed in claim 8, wherein: the number of the axial grooves (2-6-4 a) on the outer wall of the spring sleeve (2-6-4) is four, the axial grooves are uniformly distributed along the circumferential direction, and one group is a radial through notch (2-6-4 b).
10. The axial gap measurement device for a flexible connection shaft as claimed in claim 9, wherein: the spring sleeve (2-6-4) is made of H62 copper zinc alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222488602.9U CN219037844U (en) | 2022-09-20 | 2022-09-20 | Axial clearance measuring device for flexible connecting shaft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222488602.9U CN219037844U (en) | 2022-09-20 | 2022-09-20 | Axial clearance measuring device for flexible connecting shaft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219037844U true CN219037844U (en) | 2023-05-16 |
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ID=86273005
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222488602.9U Active CN219037844U (en) | 2022-09-20 | 2022-09-20 | Axial clearance measuring device for flexible connecting shaft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219037844U (en) |
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2022
- 2022-09-20 CN CN202222488602.9U patent/CN219037844U/en active Active
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