CN204008128U - Precise planetary reducer torsional rigidity and return difference pick-up unit - Google Patents
Precise planetary reducer torsional rigidity and return difference pick-up unit Download PDFInfo
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- CN204008128U CN204008128U CN201420387041.6U CN201420387041U CN204008128U CN 204008128 U CN204008128 U CN 204008128U CN 201420387041 U CN201420387041 U CN 201420387041U CN 204008128 U CN204008128 U CN 204008128U
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Abstract
The utility model discloses a kind of precise planetary reducer torsional rigidity and return difference pick-up unit, comprise that fuselage, loading unit, measuring unit are equipped with fuselage and for being connected the latch mechanism of its locking with tested speed reduction unit input end; Can apply continuously loading being greater than in rated load torque range to realize by loading unit, can detect the torque value being applied on tested reducer output shaft by torque sensor, and detect the corner situation of change of output shaft by the angular transducer on output shaft, thereby calculate torsional rigidity and the return difference of tested speed reduction unit.
Description
Technical field
The utility model relates to precision gear transmission performance field of measuring technique, particularly a kind of precise planetary reducer torsional rigidity and return difference pick-up unit.
Background technology
Along with improving constantly of China's scientific and technical innovation technical merit and scientific research strength, industry-by-industry is had higher requirement to the performance of precision speed reduction device.At present, taking the accurate epicyclic transmission mechanism of cycloid as example, as New-type cycloidal planetary reduction gear, RV speed reduction unit etc., with its high precision, large speed ratio, the advantages such as high pulling torque, and be widely used in the fields such as industrial robot, Aero-Space, national defense and military, industrial automation.The transmission performance of cycloid precise planetary reducer directly affects the performance of whole system, most important to the detection of its torsional rigidity and return difference.Torsional rigidity to cycloid precision speed reduction device and return difference test and detection at present also do not have the specialized equipment of complete set, and conventional method is to build or combine installation testing platform, takes the static mode that applies step by step external applied load.This test mode conventionally needs repeatedly frock and has adjusted, and equipment precision is limited, and moment of torsion loading does not have continuity, and repeatability can not ensure, debug time is long, poor reliability, and electromechanical integration degree deficiency, testing efficiency is low.
Utility model content
In view of this, the utility model provides a kind of precise planetary reducer torsional rigidity and return difference pick-up unit, it can be realized and apply continuously loading, and can fast detecting be applied to torque value and the corner variation on tested reducer output shaft, thereby improve testing efficiency.
Precise planetary reducer torsional rigidity of the present utility model and return difference pick-up unit, comprise that fuselage, loading unit, measuring unit are equipped with fuselage and for being connected the latch mechanism of its locking with tested speed reduction unit input end, loading unit comprises and being arranged in fuselage for the drive motor of load application and the Lug-Down device coordinating with the axial transmission of drive motor continuously;
Measuring unit comprises torque sensor and angular transducer, torque sensor one end face is axially connected with Lug-Down device clutch end, other end coordinates with the axial transmission of tested reducer output shaft, and angular transducer overcoat is fixedly installed on tested reducer output shaft and for angle signal collection.
Further, the centre of gyration of drive motor, Lug-Down device, torque sensor, angular transducer and tested speed reduction unit is all arranged on the vertical axial line in same deviation allowed band.
Further, drive motor is connected by the first shaft coupling transmission with described Lug-Down device, Lug-Down device is axially connected by the second shaft coupling with torque sensor, torque sensor coordinates with tested reducer output shaft transmission by a transmission component, transmission component comprises flange shaft 10 and the 3rd shaft coupling being connected by involute spline with the axial region of flange shaft 10, the flange portion of flange shaft 10 is connected with torque sensor upside end face, and the 3rd shaft coupling coordinates with tested reducer output shaft transmission.
Further, between torque sensor and tested speed reduction unit, be also provided with one for the positioning component to flange shaft 10 positioning supports, positioning component comprises axis of rolling bearing sleeve and rolling bearing, axis of rolling bearing sleeve is installed on fuselage, and rolling bearing and described flange shaft 10 are installed on rolling bearing and put after circumferencial direction secure fit.
Further, latch mechanism comprises latch mechanism body and lock-screw, latch mechanism body is convex disks structure, along the circumferential direction be provided with the interface coordinating with tested speed reduction unit body upper, latch mechanism body is provided with the center pit coordinating with tested reducer input shaft, and by lock-screw, input shaft is fixed.
Further, a set nut coordinates the rotor of angular transducer is connected with tested reducer output shaft with the external thread arranging on tested reducer output shaft.
Further, pick-up unit also comprises that one for installing the installing ring of tested speed reduction unit body, and the top of fuselage is provided with the mounting interface I for described installing ring and angular transducer are installed, and latch mechanism body is equipped with by screw and installing ring.
Further, fuselage is integrated the vertical stereoscopic level structure of casting, also be provided with mounting interface II for axis of rolling bearing sleeve is installed from top to bottom, drive the mounting interface III of speed reduction unit and for the mounting interface IV of drive motor is installed for installing, four mounting interfaces all coaxially arrange, each mounting interface place all forms surface level annular brace, after corresponding installing component is all put into fuselage corresponding interface along described vertical axial line perpendicular to surface level direction, form location and installation, all mounting interfaces are processed into by one-time positioning.
Further, the second shaft coupling is flange plate type shaft coupling.
Further, measuring unit also comprises signal receiving device and signal processing terminal, and signal receiving device is connected with angular transducer with torque sensor respectively, and the signal that is received from torque sensor and angular transducer is transferred to signal processing terminal processes.
The beneficial effects of the utility model: precise planetary reducer torsional rigidity of the present utility model and return difference pick-up unit, adopt monoblock type airframe structure, can apply continuously loading being greater than in rated load torque range to realize by loading unit, can detect the torque value being applied on tested reducer output shaft by torque sensor, and detect the corner situation of change of output shaft by the angular transducer on output shaft, thereby calculate torsional rigidity and the return difference of tested speed reduction unit, realize speed reduction unit high pulling torque to be measured by this pick-up unit imposed load, the tested speed reduction unit torsional rigidity that the detection of micro-corner obtains and return difference are more of practical significance than the speed reduction unit torsional rigidity and the return difference that obtain under stress state step by step, the torsional rigidity and the rotation curve figure that obtain are more accurate, also there is fitting operation easy, measuring accuracy is high, good stability, high and the electromechanical integration degree high of detection efficiency, meet industrial robot completely, Aero-Space, national defense and military, industrial automation is to precise planetary reducer high precision, high pulling torque, the test of high reliability characteristic and testing requirement.
Brief description of the drawings
Below in conjunction with drawings and Examples, the utility model is further described.
Fig. 1 is precise planetary reducer torsional rigidity of the present utility model and return difference structure of the detecting device schematic diagram;
Fig. 2 is precise planetary reducer torsional rigidity of the present utility model and return difference structure of the detecting device explosive view;
Fig. 3 is the structural representation of the fuselage of precise planetary reducer torsional rigidity of the present utility model and return difference pick-up unit.
Embodiment
As shown in the figure: the precise planetary reducer torsional rigidity of the present embodiment and return difference pick-up unit, comprise that fuselage 1, loading unit, measuring unit are equipped with fuselage 1 and for being connected the latch mechanism of its locking 3 with tested speed reduction unit 2 input ends, loading unit comprises and being arranged in fuselage 1 for the drive motor 4 of load application and the Lug-Down device 5 coordinating with the axial transmission of drive motor 4 continuously;
Measuring unit comprises torque sensor 6 and angular transducer 7, torque sensor 6 one end faces are axially connected with Lug-Down device 5 clutch ends, other end coordinates with the axial transmission of tested reducer output shaft 2a, and angular transducer 7 overcoats are fixedly installed on tested speed reduction unit 2 output shafts and for angle signal collection.
Wherein, drive motor 4 is servomotor, and torque sensor 6 is high-precision digital torque sensor 6, angular transducer 7 is high precision incremental angle encoder, fuselage 1 is monolithic construction, and fuselage 1 both sides are Open architecture, is convenient to installing/dismounting and the maintenance of checkout equipment, this pick-up unit takes tested speed reduction unit 2 input ends to fix, the mode that output terminal loads is worked, the drive motor 4 of loading unit is arranged on fuselage 1 bottom, Lug-Down device 5 drives running output torque by drive motor 4, torque sensor 6 is arranged on fuselage 1, between Lug-Down device 5 and angular transducer 7, the loading acting force being subject to detect tested speed reduction unit 2, latch mechanism 3 is connected with tested speed reduction unit 2 input ends, and be installed on downwards fuselage 1 from fuselage 1 top together with tested speed reduction unit 2, fix tested speed reduction unit 2 input shafts by elastic clamping, angle with reflection output shaft changes, in addition, angular transducer 7 and tested speed reduction unit 2 output shaft fixed connections, to detect tested speed reduction unit 2 at the rotational angle that is subject to loading tested speed reduction unit 2 output shafts under torsional interaction.
In the present embodiment, drive motor 4, Lug-Down device 5, torque sensor 6, angular transducer 7 are all arranged on the vertical axial line in same deviation allowed band with the centre of gyration of tested speed reduction unit 2; Keep the high alignment of each parts.
In the present embodiment, drive motor 4 is in transmission connection by the first shaft coupling 8 with described Lug-Down device 5, Lug-Down device 5 is axially connected by the second shaft coupling 9 with torque sensor 6, torque sensor 6 coordinates with tested speed reduction unit 2 output shaft transmissions by a transmission component, transmission component comprises flange shaft 10 and the 3rd shaft coupling 11 being connected by involute spline with the axial region of flange shaft 10, the flange portion of flange shaft 10 is connected with torque sensor 6 upside end faces, and the 3rd shaft coupling 11 coordinates with tested speed reduction unit 2 output shaft transmissions; As shown in the figure, tested speed reduction unit 2 output shaft front ends form transmission fit key structure, this bond structure coordinates and is in transmission connection with the keyway of the 3rd shaft coupling 11 ends settings, in addition, connect as the 3rd shaft coupling 11 between torque sensor 6 and tested speed reduction unit 2 owing to having designed using involute spline, can make becomes and is flexibly connected between torque sensor 6 and tested speed reduction unit 2, be convenient to install and remove, improve detection efficiency, avoid rigidity simultaneously or flexibly connected the impact that pretightning force causes tested speed reduction unit 2 output shafts, improved the reliability of checkout equipment.
In the present embodiment, between torque sensor 6 and tested speed reduction unit 2, be also provided with one for the positioning component to flange shaft 10 positioning supports, positioning component comprises axis of rolling bearing sleeve 12 and rolling bearing 13, axis of rolling bearing sleeve 12 is installed on fuselage 1, and rolling bearing 13 is installed on axis of rolling bearing sleeve 12 after circumferencial direction secure fit with described flange shaft 10.
In the present embodiment, latch mechanism 3 comprises latch mechanism body 14 and lock-screw, latch mechanism body 14 is convex disks structure, along the circumferential direction be provided with the interface coordinating with tested speed reduction unit 2 body upper, latch mechanism body 14 is provided with the center pit coordinating with tested speed reduction unit 2 input shafts, and by lock-screw, input shaft is fixed.
In the present embodiment, a set nut 15 coordinates the rotor of angular transducer 7 is connected with tested speed reduction unit 2 output shafts with the external thread arranging on tested speed reduction unit 2 output shafts; It is fastening that this set nut makes angular transducer 7 be connected with output shaft by screw thread precession.
In the present embodiment, pick-up unit also comprises that one for installing the installing ring 16 of tested speed reduction unit 2 bodies, the top of fuselage 1 is provided with the mounting interface I 17 for described installing ring 16 and angular transducer 7 are installed, and latch mechanism body 14 is equipped with by screw and installing ring 16; Installing ring 16 is located on fuselage 1 by shaft hole matching, and is fixed on fuselage 1 by screw; Then tested speed reduction unit 2 is arranged on installing ring 16 by shaft hole matching; Next latch mechanism and tested speed reduction unit are connected, and lock input shaft, finally by screw, latch mechanism, tested speed reduction unit are fixedly connected with installing ring; Tested speed reduction unit 2 and latch mechanism 3 are taked to same positioning datum, and the mode that same interface is installed, has reduced to install fixedly to have brought respectively with latch mechanism 3 and relatively rotate error due to tested speed reduction unit 2.
In the present embodiment, fuselage 1 is integrated the vertical stereoscopic level structure of casting, also be provided with mounting interface II 18 for axis of rolling bearing sleeve 12 is installed from top to bottom, drive the mounting interface III 19 of speed reduction unit and for the mounting interface IV 20 of drive motor 4 is installed for installing, four mounting interfaces all coaxially arrange, each mounting interface place all forms surface level annular brace, after corresponding installing component is all put into fuselage 1 corresponding interface along described vertical axial line perpendicular to surface level direction, form location and installation, all mounting interfaces are processed into by one-time positioning; Compare and the axial mounting means of previous level, avoid the problem of the installation riser rigidity deficiency causing because of gravity, horizontal curvature internal force, pick-up unit integral rigidity is more superior, stability is changed, in addition, all mounting interfaces take one-time positioning to be processed into, and have ensured high right alignment and axial line linearity.
By this airframe structure, having designed angular transducer 7 is directly connected with tested speed reduction unit 2 output shafts in parallel with loading unit, the corner that angular transducer 7 sampled signals are directly measured tested speed reduction unit 2 output shafts changes, reduced the accuracy requirement being connected between loading unit and tested speed reduction unit 2 simultaneously, to the unstable variable of having avoided indirect measurement to introduce, cause the error that angle signal sample data is produced, be convenient to data to carry out analyzing and processing.
In the present embodiment, the second shaft coupling 9 is flange plate type shaft coupling; The second shaft coupling 9 comprises top 91 and the bottom 92 that axial circumference coordinates, its middle and lower part and top all carry flange arrangement, the ring flange arranging in the power output shaft of the flange arrangement on bottom and Lug-Down device 5 is fixedly connected with, in power output shaft, be set in the axial region of bottom, the flange arrangement on the top of the second shaft coupling 9 is fixedly connected with the downside end face of torque sensor 6 simultaneously.
In the present embodiment, measuring unit also comprises signal receiving device and signal processing terminal, signal receiving device is connected with angular transducer 7 with torque sensor 6 respectively, and the signal that is received from torque sensor 6 and angular transducer 7 is transferred to signal processing terminal processes.Wherein, signal processing terminal is computing machine, the utility model pick-up unit embodiment in use, first tested speed reduction unit 2 is installed on fuselage 1 with latch mechanism 3, fixing tested speed reduction unit 2 input ends, retelling angular transducer 7 tightens by set nut 15, connect again the 3rd shaft coupling 11, by computer settings charger working method, start this pick-up unit, the signalman who receives torque sensor 6 and angular transducer 7 by signal receiving device is transferred to computing machine and processes, calculate torsional rigidity and the return difference of tested speed reduction unit 2, and draw corner torque curve, generate speed reduction unit rigidity and return difference data file, and print testing result.
Generally speaking, detecting according to the precise planetary reducer torsional rigidity of embodiment of the present utility model and return difference pick-up unit the precision cycloid decelerator torsional rigidity and the return difference that obtain is more of practical significance, systematic error and stochastic error that original measurement device weak point causes are reasonably reduced, rigidity and the return difference characteristic of cycloidal reducer are reflected more accurately, improve the efficiency detecting simultaneously, be conducive to the industrialized development of experimental study and precise planetary reducer.
Finally explanation is, above embodiment is only unrestricted in order to the technical solution of the utility model to be described, although the utility model is had been described in detail with reference to preferred embodiment, those of ordinary skill in the art is to be understood that, can modify or be equal to replacement the technical solution of the utility model, and not departing from aim and the scope of technical solutions of the utility model, it all should be encompassed in the middle of claim scope of the present utility model.
Claims (10)
1. a precise planetary reducer torsional rigidity and return difference pick-up unit, it is characterized in that: comprise that fuselage, loading unit, measuring unit are equipped with fuselage and for being connected the latch mechanism of its locking with tested speed reduction unit input end, described loading unit comprises and being arranged in fuselage for the drive motor of load application and the Lug-Down device coordinating with the axial transmission of described drive motor continuously;
Described measuring unit comprises torque sensor and angular transducer, described torque sensor one end face is axially connected with Lug-Down device clutch end, other end coordinates with the axial transmission of tested reducer output shaft, and described angular transducer overcoat is fixedly installed on tested reducer output shaft and for angle signal collection.
2. precise planetary reducer torsional rigidity according to claim 1 and return difference pick-up unit, is characterized in that: the centre of gyration of drive motor, Lug-Down device, torque sensor, angular transducer and tested speed reduction unit is all arranged on the vertical axial line in same deviation allowed band.
3. precise planetary reducer torsional rigidity according to claim 2 and return difference pick-up unit, it is characterized in that: described drive motor is connected by the first shaft coupling transmission with described Lug-Down device, described Lug-Down device is axially connected by the second shaft coupling with described torque sensor, described torque sensor coordinates with tested reducer output shaft transmission by a transmission component, described transmission component comprises flange shaft (10) and the 3rd shaft coupling being connected by involute spline with the axial region of flange shaft (10), the flange portion of described flange shaft (10) is connected with torque sensor upside end face, described the 3rd shaft coupling coordinates with tested reducer output shaft transmission.
4. precise planetary reducer torsional rigidity according to claim 3 and return difference pick-up unit, it is characterized in that: between described torque sensor and described tested speed reduction unit, be also provided with one for the positioning component to flange shaft (10) positioning supports, described positioning component comprises axis of rolling bearing sleeve and rolling bearing, described axis of rolling bearing sleeve is installed on fuselage, and described rolling bearing and described flange shaft (10) are installed on described rolling bearing and put after circumferencial direction secure fit.
5. precise planetary reducer torsional rigidity according to claim 4 and return difference pick-up unit, it is characterized in that: described latch mechanism comprises latch mechanism body and lock-screw, described latch mechanism body is convex disks structure, along the circumferential direction be provided with the interface coordinating with tested speed reduction unit body upper, described latch mechanism body is provided with the center pit coordinating with tested reducer input shaft, and by lock-screw, input shaft is fixed.
6. precise planetary reducer torsional rigidity according to claim 5 and return difference pick-up unit, is characterized in that: a set nut coordinates the rotor of angular transducer is connected with tested reducer output shaft with the external thread arranging on tested reducer output shaft.
7. precise planetary reducer torsional rigidity according to claim 6 and return difference pick-up unit, it is characterized in that: described pick-up unit also comprises that one for installing the installing ring of tested speed reduction unit body, the top of described fuselage is provided with the mounting interface I for described installing ring and described angular transducer are installed, and described latch mechanism body is equipped with by screw and described installing ring.
8. precise planetary reducer torsional rigidity according to claim 7 and return difference pick-up unit, it is characterized in that: described fuselage is integrated the vertical stereoscopic level structure of casting, also be provided with the mounting interface II for axis of rolling bearing sleeve is installed from top to bottom, for install drive speed reduction unit mounting interface III and for the mounting interface IV of drive motor is installed, four mounting interfaces all coaxially arrange, each mounting interface place all forms surface level annular brace, after all putting into fuselage corresponding interface along described vertical axial line perpendicular to surface level direction, corresponding installing component forms location and installation, all mounting interfaces are processed into by one-time positioning.
9. precise planetary reducer torsional rigidity according to claim 8 and return difference pick-up unit, is characterized in that: described the second shaft coupling is flange plate type shaft coupling.
10. precise planetary reducer torsional rigidity according to claim 9 and return difference pick-up unit, it is characterized in that: described measuring unit also comprises signal receiving device and signal processing terminal, described signal receiving device is connected with angular transducer with torque sensor respectively, and the signal that is received from torque sensor and angular transducer is transferred to signal processing terminal processes.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420387041.6U CN204008128U (en) | 2014-07-14 | 2014-07-14 | Precise planetary reducer torsional rigidity and return difference pick-up unit |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420387041.6U CN204008128U (en) | 2014-07-14 | 2014-07-14 | Precise planetary reducer torsional rigidity and return difference pick-up unit |
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| CN204008128U true CN204008128U (en) | 2014-12-10 |
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| CN201420387041.6U Expired - Fee Related CN204008128U (en) | 2014-07-14 | 2014-07-14 | Precise planetary reducer torsional rigidity and return difference pick-up unit |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104062121A (en) * | 2014-07-14 | 2014-09-24 | 重庆大学 | Device for detecting torsional rigidity and return difference of precision planetary reducer |
| CN105716861A (en) * | 2016-04-11 | 2016-06-29 | 四川志方科技有限公司 | Torsional rigidity detecting device for RV reducer and implementation method of detecting device |
| CN105784351A (en) * | 2016-03-04 | 2016-07-20 | 中南大学 | RV speed reducer transmission return difference testing device |
| CN106289771A (en) * | 2016-11-09 | 2017-01-04 | 北京工业大学 | A kind of measurement apparatus of harmonic gear reducer engagement torsional rigidity |
| CN109909911A (en) * | 2019-03-05 | 2019-06-21 | 山东帅克机械制造股份有限公司 | A kind of switching device based on high-tech precision inspection instrument |
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2014
- 2014-07-14 CN CN201420387041.6U patent/CN204008128U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104062121A (en) * | 2014-07-14 | 2014-09-24 | 重庆大学 | Device for detecting torsional rigidity and return difference of precision planetary reducer |
| CN105784351A (en) * | 2016-03-04 | 2016-07-20 | 中南大学 | RV speed reducer transmission return difference testing device |
| CN105784351B (en) * | 2016-03-04 | 2018-10-02 | 中南大学 | A kind of RV retarders transmission return difference test device |
| CN105716861A (en) * | 2016-04-11 | 2016-06-29 | 四川志方科技有限公司 | Torsional rigidity detecting device for RV reducer and implementation method of detecting device |
| CN105716861B (en) * | 2016-04-11 | 2019-03-19 | 四川志方科技有限公司 | RV retarder torsion stiffness detection device and its implementation |
| CN106289771A (en) * | 2016-11-09 | 2017-01-04 | 北京工业大学 | A kind of measurement apparatus of harmonic gear reducer engagement torsional rigidity |
| CN109909911A (en) * | 2019-03-05 | 2019-06-21 | 山东帅克机械制造股份有限公司 | A kind of switching device based on high-tech precision inspection instrument |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Tailong Decelerating Machine Co., Ltd., Jiangsu Assignor: Chongqing University Contract record no.: 2015320000085 Denomination of utility model: Device for detecting torsional rigidity and return difference of precision planetary reducer Granted publication date: 20141210 License type: Exclusive License Record date: 20150319 |
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| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141210 Termination date: 20160714 |