CN210090020U - Power takeoff output end loading inertia device - Google Patents
Power takeoff output end loading inertia device Download PDFInfo
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- CN210090020U CN210090020U CN201920817634.4U CN201920817634U CN210090020U CN 210090020 U CN210090020 U CN 210090020U CN 201920817634 U CN201920817634 U CN 201920817634U CN 210090020 U CN210090020 U CN 210090020U
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Abstract
The utility model provides a power takeoff output loading inertia device, the output of power takeoff when solving current synchronizer shift test is unloaded, this problem of actual state when unable simulation appears unusually if power takeoff work. The loading inertia device comprises a supporting base, a bearing seat and a rotating through shaft; the bearing seat is arranged above the supporting base; the rotary through shaft is arranged in the bearing block through a bearing; one end of the rotating through shaft is provided with a coupler, and the other end of the rotating through shaft is provided with an inertia disc; the rotational inertia of the coupler is equal to that of the inertia disc. The utility model has simple and compact structure, adopts the mode of respectively installing the same rotary inertia at the two ends of the rotary through shaft, can greatly shorten the axial distance and save the installation space; the actual state of the power takeoff when working abnormally can be simulated to grasp what kind of influence exists to the synchronizer when the power takeoff takes place abnormal work, and research personnel can conveniently carry out targeted improvement to the synchronizer aiming at the condition.
Description
Technical Field
The utility model belongs to automotive machinery tests the field, concretely relates to power takeoff flange end loading inertia device.
Background
When a transmission with a power takeoff is subjected to a synchronizer gear shifting test in the prior art, the output end of the power takeoff is in no-load, which is not consistent with the actual operation working condition of a whole vehicle; in fact, the output end (namely, the flange end) of the power takeoff is connected with a load, when the power takeoff works normally, the power takeoff can be separated from the load at the rear end of the power takeoff, but if the power takeoff works abnormally and is not completely disengaged or stuck, the load of the power takeoff can become a part of synchronous inertia of a synchronizer, and the part of inertia has great influence on the performance and the service life of the synchronizer.
Therefore, the existing synchronizer gear shifting test of the transmission with the power takeoff cannot actually simulate the actual state of the power takeoff working on the whole vehicle when the power takeoff working is abnormal, has certain influence on the gear shifting performance and the service life test result of the synchronizer to be tested, and further cannot perform targeted improvement on the synchronizer.
In order to grasp the actual state of the synchronizer when the power takeoff works abnormally and what kind of influence the state has on the synchronizer, it is necessary to design a power takeoff output end loading inertia device capable of simulating the actual load, so that research and development personnel can improve the synchronizer according to the simulation condition.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the output of power takeoff unloaded when current synchronizer shifts the experiment, this problem of actual state when unable simulation appears unusual if the power takeoff work, and provided a power takeoff output loading inertia device, be exclusively used in and assist the synchronizer to shift the experiment simulation power takeoff actual state when working unusually to grasp what kind of influence exists to the synchronizer when taking place unusual work for the power takeoff, the research and development personnel of being convenient for improve the synchronizer to this kind of condition.
In order to achieve the above object, the present invention provides a technical solution:
an inertia loading device at the output end of a power takeoff is characterized by comprising a supporting base, a bearing seat and a rotary through shaft; the bearing seat is arranged above the supporting base; the rotating through shaft is arranged in the bearing block through a bearing; one end of the rotating through shaft is provided with a coupler, and the other end of the rotating through shaft is provided with an inertia disc; the coupling is equal to the inertia moment of the inertia disc, and the inertia moment can be calculated according to a torque value needing to be loaded at the output end (flange end) of the power takeoff. The supporting base is used for fixing the whole loading inertia device at a station for testing.
Further, the coupler adopts the plum blossom shaft coupling, also can choose for use other couplers certainly, nevertheless uses the plum blossom shaft coupling as preferred, the plum blossom shaft coupling simple structure, need not lubricated, convenient maintenance, be convenient for the inspection, can run for a long time in succession, and the axial distance of plum blossom shaft coupling is shorter, can install smoothly in limited experimental space, because the plum blossom shaft coupling middle part has the elastomer, can take place certain elastic deformation, inertial rotation demand when also can satisfying the experiment.
Further, the bearing adopts a duplex bearing mode, and other bearing modes can be adopted during installation, but the duplex bearing is preferred, and the duplex bearing is adopted, so that the stability during rotation is better.
Furthermore, the coupling and the inertia disc are both installed on the rotary through shaft through rectangular keys, and the installation is reliable and simple.
Further, the device also comprises two glands; bolt holes are formed in the two ends of the rotary through shaft; the two pressing covers are respectively pressed on the coupler and the inertia disc through bolts, so that the rectangular key is prevented from being separated during rotation.
Further, the coupler is mounted at one end of the rotating through shaft through an A-type flat key; for the convenience of design, convenient to process, the inertia dish is the disc, and it is installed through C type flat key the other end of rotatory through-shaft.
Furthermore, the bearing is a self-lubricating angular contact bearing, belongs to a maintenance-free bearing, and can prolong the service life of the bearing.
Furthermore, the bearing is axially pressed on the bearing seat through the bearing covers at two ends, so that the axial movement of the bearing in the movement process can be prevented.
Furthermore, the bearing seat is installed on the supporting base through an outer hexagon bolt, and the dismounting and the mounting are convenient.
Further, in view of some specific test environments, the support base is provided with a U-shaped mounting groove for fixedly connecting the support base with the trench T-shaped sliding block.
The utility model has the advantages that:
1. the utility model has simple and compact structure, adopts the mode of respectively installing the same rotary inertia at the two ends of the rotary through shaft, can greatly shorten the axial distance and save the installation space; the inertia can be obtained by calculation according to a torque value needing to be loaded at the flange end of the power takeoff, and the actual state of the power takeoff in abnormal working can be simulated so as to master the influence on the synchronizer in abnormal working of the power takeoff, thereby facilitating the research and development personnel to pertinently improve the synchronizer in the case. Meanwhile, the rear auxiliary box of the transmission needs to be frequently disassembled and assembled in a test period, and the device is easy to disassemble and move, so that the device is divided into an upper part and a lower part, and the device is convenient to maintain.
2. The utility model adopts the plum coupling, which can be smoothly installed in the limited test space due to the short axial distance, and can generate certain elastic deformation due to the elastic body in the middle of the plum coupling, thereby meeting the requirement of inertial rotation during the test; the whole structure is simple, no lubrication is needed, the maintenance and the inspection are convenient, and the device can continuously run for a long time.
3. The utility model discloses a self-lubricating non-maintaining pair bearing can prolong the life of bearing, and stability is better during the rotation, reduces the maintenance cost on the whole.
Drawings
Fig. 1 is a first schematic structural diagram of the present invention;
FIG. 2 is a second schematic structural view of the present invention;
fig. 3 is a cross-sectional view of the present invention;
the reference numbers are as follows: 1-a support base; 2-bearing seat; 3, coupling; 4-inertia disc; 5-a bearing; a 6-A type flat bond; 7-C type flat bond; 8-pressing cover; 10-rotating the through shaft; 11-a bearing cap; 12-outer hexagon bolt.
Detailed Description
The invention is described in further detail below with reference to the following figures and specific examples:
as shown in fig. 1-3, the device for loading inertia at the output end of a power takeoff comprises a supporting base 1, a bearing seat 2, a rotating through shaft 10 and a gland 8.
In order to match with a specific test environment, the bottom of the supporting base 1 is provided with a U-shaped mounting groove for fixedly connecting the supporting base 1 with a T-shaped sliding block of a trench; of course, the supporting base 1 can be fixed in other ways in different test environments. The bearing seat 2 is arranged above the supporting base 1 through an outer hexagon bolt 12, and is convenient to disassemble and assemble.
The rotating through shaft 10 is arranged in the bearing seat 2 through a duplex bearing 5, one end of the rotating through shaft is provided with a plum coupling 3, and the other end of the rotating through shaft is provided with an inertia disc 4; although the shapes of the plum blossom coupling 3 and the inertia disc 4 are different, the rotational inertia of the plum blossom coupling and the inertia disc 4 is equal, and the inertia can be obtained by calculation according to a torque value required to be loaded at the output end of the power takeoff. The duplex bearing 5 is pressed tightly in the bearing seat 2 through the bearing caps 5 at both ends, and the bearing 5 selects the self-lubricating angular contact bearing 5, so that the service life of the bearing 5 can be prolonged, and the replacement cost is reduced.
For the installation is reliable simple and convenient, plum blossom shaft coupling 3 passes through A type flat key 6 and installs on rotatory through-shaft 10, and inertia dish 4 passes through C type flat key 7 and installs on rotatory through-shaft 10, and the both ends of rotatory through-shaft 10 all are provided with the bolt hole, and gland 8 passes through the bolt and compresses tightly on shaft coupling 3 and inertia dish 4, prevents A type flat key 6, C type flat key 7 and deviates from when rotatory.
For the convenience of design, be convenient for process, inertia dish 4 designs for the disc, also can promote the pleasing to the eye degree of loading inertia device simultaneously.
The utility model discloses can realize the operating condition of power takeoff flange when according to certain moment of torsion loading, concrete working process as follows:
in the transmission bench test process, the power takeoff assembly is arranged at the right rear side position of the transmission, and power is taken through the auxiliary box intermediate shaft; externally venting the power take-off cylinder to an on state; the flange end of the transmission operates according to the required test rotating speed, when the auxiliary box synchronizer is switched between a high gear and a low gear through an auxiliary box cylinder, the rotating speed of an auxiliary box intermediate shaft is also changed continuously due to the difference of gear ratios, the power takeoff is in a switch-on state at the moment, the rotating speed of the flange of the power takeoff is changed along with the change of the rotating speed of the auxiliary box intermediate shaft, the flange end (namely the output end of the power takeoff) of the power takeoff is connected with the loading inertia device through an adapter (such as a connecting sleeve) and a plum coupling, the loading inertia device is further driven to rotate together, and the actual gear shifting condition of the synchronizer when the power takeoff is abnormal in work and still has load.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily think of various equivalent modifications or replacements within the technical scope of the present invention, and these modifications or replacements should be covered within the protection scope of the present invention.
Claims (10)
1. The utility model provides a power takeoff output loading inertia device which characterized in that: comprises a supporting base (1), a bearing seat (2) and a rotary through shaft (10);
the bearing seat (2) is arranged above the supporting base (1);
the rotary through shaft (10) is arranged in the bearing seat (2) through a bearing (5); one end of the rotating through shaft (10) is provided with a coupling (3), and the other end is provided with an inertia disc (4);
the rotational inertia of the coupling (3) is equal to that of the inertia disc (4).
2. The power take-off output loading inertia device of claim 1, wherein: the coupler (3) adopts a plum coupler.
3. The power take-off output loading inertia device as claimed in claim 1 or 2, wherein: the bearing (5) adopts a duplex bearing.
4. The power take-off output loaded inertia apparatus of claim 3, wherein: the coupler (3) and the inertia disc (4) are both installed on the rotary through shaft (10) through rectangular keys.
5. The power take-off output loading inertia device of claim 4, wherein: also comprises two glands (8);
bolt holes are formed in the two ends of the rotary through shaft (10); the two pressing covers (8) are respectively pressed on the coupler (3) and the inertia disc (4) through bolts.
6. The power take-off output loading inertia device of claim 5, wherein: the coupler (3) is arranged at one end of the rotary through shaft (10) through an A-shaped flat key (6); the inertia disc (4) is disc-shaped and is arranged at the other end of the rotary through shaft (10) through a C-shaped flat key (7).
7. The power take-off output loading inertia device of claim 6, wherein: the bearing (5) is a self-lubricating angular contact bearing.
8. The power take-off output loading inertia device of claim 7, wherein: the bearing (5) is axially pressed on the bearing seat (2) through the bearing covers (11) at two ends.
9. The power take-off output loaded inertia apparatus of claim 8, wherein: the bearing seat (2) is installed on the supporting base (1) through an outer hexagon bolt (12).
10. The power take-off output loaded inertia apparatus of claim 9, wherein: the support base (1) is provided with a U-shaped mounting groove for fixedly connecting the support base (1) with a trench T-shaped sliding block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920817634.4U CN210090020U (en) | 2019-05-31 | 2019-05-31 | Power takeoff output end loading inertia device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920817634.4U CN210090020U (en) | 2019-05-31 | 2019-05-31 | Power takeoff output end loading inertia device |
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| Publication Number | Publication Date |
|---|---|
| CN210090020U true CN210090020U (en) | 2020-02-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920817634.4U Active CN210090020U (en) | 2019-05-31 | 2019-05-31 | Power takeoff output end loading inertia device |
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| CN (1) | CN210090020U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113418720A (en) * | 2021-06-21 | 2021-09-21 | 哈尔滨东安汽车动力股份有限公司 | Power takeoff bench test device and test method thereof |
-
2019
- 2019-05-31 CN CN201920817634.4U patent/CN210090020U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113418720A (en) * | 2021-06-21 | 2021-09-21 | 哈尔滨东安汽车动力股份有限公司 | Power takeoff bench test device and test method thereof |
| CN113418720B (en) * | 2021-06-21 | 2022-07-19 | 哈尔滨东安汽车动力股份有限公司 | Power takeoff bench test device and test method thereof |
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