CN217210704U - Aviation cardan shaft coaxiality testing device - Google Patents
Aviation cardan shaft coaxiality testing device Download PDFInfo
- Publication number
- CN217210704U CN217210704U CN202122381214.6U CN202122381214U CN217210704U CN 217210704 U CN217210704 U CN 217210704U CN 202122381214 U CN202122381214 U CN 202122381214U CN 217210704 U CN217210704 U CN 217210704U
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- fixed
- shaft seat
- dynamic balance
- aviation
- base
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- A Measuring Device Byusing Mechanical Method (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model provides an aviation cardan shaft axiality testing arrangement, includes dynamic balance tester (1), fixes adjustment subassembly (2) on dynamic balance tester (1), sets up motor (4) at adjustment subassembly (2) input, and its technical essential is: the adjusting component (2) comprises a base (24) fixed on the dynamic balance tester (1) and arranged along the length direction, a fixed end shaft seat (21) fixed at one end of the base (24), a sliding rail component (23) fixed at the other end of the base (24) and a movable end shaft seat (22) limited on the sliding rail component (23) in a sliding mode, and the fixed end shaft seat (21) and the movable end shaft seat (22) are arranged in a centering mode. It has the advantages of simple structure, convenient use and the like. The test is convenient and the test accuracy is improved.
Description
Technical Field
The utility model relates to an aviation check out test set, an aviation cardan shaft axiality testing arrangement specifically says so, its axiality test that is mainly applicable to the aviation cardan shaft.
Background
The dynamic balance tester is used for testing the coaxiality of aviation shaft parts under the common condition, the coaxiality condition of the shaft parts can be detected visually, but for an aviation universal shaft, because the two ends of the universal shaft are provided with slipknots, the dynamic balance tester can not finish clamping the universal shaft well, and difficulty and inaccuracy are brought to the coaxiality test.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an aviation cardan shaft axiality testing arrangement, fundamentally has solved above-mentioned problem, and it has advantages such as simple structure, convenient to use. Mainly make the improvement to the clamping of cardan shaft, the convenience is tested and the accuracy of improvement test.
In order to achieve the above purpose, the utility model provides a following technical scheme: this aviation cardan shaft axiality detection device includes the dynamic balance tester, fixes adjustment assembly on the dynamic balance tester, sets up the motor at the adjustment assembly input, and its technical essential is: the adjusting component comprises a base fixed on the dynamic balance tester along the length direction, a fixed end shaft seat fixed at one end of the base, a slide rail component fixed at the other end of the base, and a movable end shaft seat sliding and limited on the slide rail component, wherein the fixed end shaft seat and the movable end shaft seat are arranged in a centering way.
The utility model has the advantages that: on the whole technical scheme, through fixing adjustable to be tested a clamping structure on the platform of dynamic balance tester, the dynamic balance tester can drive the motor that is located one side rotatory in order to survey the axiality of a to be tested cardan shaft.
In a specific structure, the axes of the fixed end shaft seat and the movable end shaft seat are installed in a centering mode, so that the balance of a piece to be measured is ensured. And the movable end shaft seat is adjustably installed through the sliding rail assembly, so that the application range of the piece to be measured is improved, and the adjustment of the gap of the piece to be measured can be realized. During detection, the slipknots at the two ends of the aviation universal shaft are straightened to enable the aviation universal shaft to be coaxial and to be kept horizontal, and a dynamic balance tester can conveniently test the coaxiality of the aviation universal shaft.
Drawings
Fig. 1 is a schematic view of the structure of the present invention.
Fig. 2 is an isometric side view schematic of an adjustment assembly.
Detailed Description
The following describes the specific contents of the present invention in detail with reference to fig. 1 to 2. The aviation cardan shaft coaxiality testing device comprises a dynamic balance tester 1, an adjusting component 2 fixed on the dynamic balance tester 1, and a motor 4 arranged at the input end of the adjusting component 2. The adjusting component 2 comprises a base 24 fixed on the dynamic balance tester 1 and arranged along the length direction, a fixed end shaft seat 21 fixed at one end of the base 24, a slide rail component 23 fixed at the other end of the base 24, and a movable end shaft seat 22 limited on the slide rail component 23 in a sliding manner, wherein the fixed end shaft seat 21 and the movable end shaft seat 22 are arranged in a shaft center alignment manner. In particular, the sliding rail assembly 23 comprises a rail and a slider (not numbered) which are slidably fitted, and the slider can be locked on the rail (for example, by a bolt penetrating the slider and fastening the slider by tightening the bolt), and the moving shaft seat 22 is fixed on the slider by a bolt (not numbered). The movable clearance of the slipknots at the two ends of the piece to be measured 3 can be eliminated by adjusting the movable end shaft seat 22, and the two ends of the piece to be measured 3 are locked after the clearance is eliminated.
Further, the fixed shaft seat 21 is fixed on a mounting block (not labeled), and when the fixed shaft seat 21 and the movable shaft seat 22 adopt shaft seat fittings with the same structure, the thickness of the mounting block in the Y direction is equal to the thickness of the slide rail assembly, so as to ensure that the axis connecting line of the fixed shaft seat 21 and the movable shaft seat 22 is always kept horizontal. Once the sliding rail assembly 23 is worn, the installation block on one side of the fixed end shaft seat 21 can be directly replaced, so as to achieve the purpose of leveling.
During the use, will await measuring 3 (aviation cardan shaft) one end is fixed in stiff end axle bed 21, and the other end is fixed in and removes end axle bed 22, removes and removes end axle bed 22 and evens out await measuring 3, fixes the slider in the sliding rail set spare 23, opens the dynamic balance tester, and actuating motor 4 drives the rotation of awaiting measuring 3, can carry out the axiality test.
Description of reference numerals:
1 dynamic balance tester
2 adjusting assembly
21 fixed end shaft base
22 movable end shaft seat
23 slide rail assembly
24 base
3 to-be-tested piece (aviation universal shaft)
4 motor.
Claims (1)
1. The utility model provides an aviation cardan shaft axiality testing arrangement, includes dynamic balance tester (1), fixes adjustment subassembly (2) on dynamic balance tester (1), sets up motor (4) at adjustment subassembly (2) input, its characterized in that: the adjusting component (2) comprises a base (24) fixed on the dynamic balance tester (1) and arranged along the length direction, a fixed end shaft seat (21) fixed at one end of the base (24), a sliding rail component (23) fixed at the other end of the base (24) and a movable end shaft seat (22) limited on the sliding rail component (23) in a sliding mode, and the fixed end shaft seat (21) and the movable end shaft seat (22) are arranged in a centering mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122381214.6U CN217210704U (en) | 2021-09-30 | 2021-09-30 | Aviation cardan shaft coaxiality testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122381214.6U CN217210704U (en) | 2021-09-30 | 2021-09-30 | Aviation cardan shaft coaxiality testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217210704U true CN217210704U (en) | 2022-08-16 |
Family
ID=82750757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122381214.6U Active CN217210704U (en) | 2021-09-30 | 2021-09-30 | Aviation cardan shaft coaxiality testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217210704U (en) |
-
2021
- 2021-09-30 CN CN202122381214.6U patent/CN217210704U/en active Active
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| GR01 | Patent grant |