CN217687613U - High low temperature motor test system of aircraft - Google Patents
High low temperature motor test system of aircraft Download PDFInfo
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- CN217687613U CN217687613U CN202221096436.1U CN202221096436U CN217687613U CN 217687613 U CN217687613 U CN 217687613U CN 202221096436 U CN202221096436 U CN 202221096436U CN 217687613 U CN217687613 U CN 217687613U
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- 238000012360 testing method Methods 0.000 title claims abstract description 62
- 230000008878 coupling Effects 0.000 claims description 20
- 238000010168 coupling process Methods 0.000 claims description 20
- 238000005859 coupling reaction Methods 0.000 claims description 20
- 239000006247 magnetic powder Substances 0.000 claims description 16
- 239000006249 magnetic particle Substances 0.000 claims description 3
- 230000033228 biological regulation Effects 0.000 claims description 2
- 230000000149 penetrating effect Effects 0.000 abstract description 4
- 230000017525 heat dissipation Effects 0.000 description 4
- 238000010998 test method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000008093 supporting effect Effects 0.000 description 1
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Abstract
The utility model discloses an aircraft high low temperature motor test system, include: a motor arrangement assembly; the measuring device assembly can apply load and can test torque and rotating speed; the high-low temperature box can adjust the temperature, the motor device assembly is arranged in the high-low temperature box, the motor device assembly is rotatably connected with the measuring device assembly through the transfer shaft assembly, and the transfer shaft assembly penetrates through the high-low temperature box and is fixedly arranged on the high-low temperature box. Because the measuring device assembly is rotatably connected with the motor device assembly through the transfer shaft assembly penetrating through the high-low temperature box, the testing motor can be rotatably installed on the motor device assembly, when the testing motor needs to perform high-temperature or low-temperature testing in the high-low temperature box, the temperature of the high-low temperature box cannot influence the testing data result of the torque and speed sensor, and the problems that the distance between the torque and speed sensor and the motor is close, and the testing data result of the torque and speed sensor can be influenced by the temperature of the motor in a high-temperature or low-temperature environment are solved.
Description
Technical Field
The utility model relates to a high low temperature motor test system of aircraft belongs to the motor and detects technical field.
Background
On aircrafts such as aerospace and the like, motors are sometimes required to be installed to realize automatic operation. In order to meet the requirements of the working environment, the data of the rotating speed, the torque, the power and the like of the motor need to be tested.
In a motor test bed test system with Chinese patent publication No. CN109932653A, the disclosed technology is that an output shaft of a motor is connected with a torque and rotating speed sensor through a coupler, the torque and rotating speed sensor is connected with an eddy current brake through the coupler, and the eddy current brake is connected with a magnetic powder brake through a jaw clutch; the magnetic powder brake system further comprises a load controller heat dissipation system, wherein the load controller heat dissipation system comprises a second heat dissipation water tank, a submersible pump and a switch valve, the submersible pump is arranged in the second heat dissipation water tank, the switch valve is arranged at the output end of the submersible pump, and the switch valve is respectively arranged on the outer sides of the eddy current brake and the magnetic powder brake through pipelines; although the test of the rotating speed and the torque data of the motor can be carried out, the torque rotating speed sensor is close to the motor, the motor needs to be in a high-temperature or low-temperature environment, and the temperature can influence the test data result of the torque rotating speed sensor.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides an aircraft high low temperature motor test method.
The utility model also provides an aircraft high low temperature motor test system.
The utility model discloses a following technical scheme can realize.
The utility model provides a pair of high low temperature motor test system of aircraft.
The utility model discloses a following technical scheme can realize.
The utility model provides a pair of high low temperature motor test system of aircraft, include:
a motor arrangement assembly;
the measuring device assembly can apply load and can test torque and rotating speed;
the temperature of the high-low temperature box can be adjusted, the motor device assembly is arranged in the high-low temperature box and is rotatably connected with the measuring device assembly through the adapter shaft assembly, and the adapter shaft assembly penetrates through the high-low temperature box and is fixedly arranged on the high-low temperature box and tightly supported by the motor device assembly.
The measuring device assembly includes a magnetic particle brake applying a load; and a dynamic torque sensor rotatably connected with the magnetic powder brake.
The measuring device assembly further comprises a base A;
a bracket A arranged on the base A;
an adapter plate A which can move up and down and is arranged on the bracket A is fixed with a magnetic powder brake;
install the support on base A, the support interval is located support A side, and dynamic torque sensor fixed mounting is on the support.
The output end of the dynamic torque sensor is rotatably connected with the magnetic powder brake through the flexible coupler A.
The measuring device assembly further comprises a fixing plate A fixed on the base A, the bottom of the fixing plate A is connected with the base A in a reinforcing mode through a rib plate A, the fixing plate A is located on the side edge of the input end of the dynamic torque sensor, and a through hole is formed in the fixing plate A and corresponds to the input end of the dynamic torque sensor.
The switching shaft assembly comprises a switching shaft, one end of the switching shaft is rotatably connected with the input end of the dynamic torque sensor, and the other end of the switching shaft is rotatably connected with the motor device assembly;
the two ends of the adapting shaft penetrate through the shaft sleeve and are rotatably arranged in the shaft sleeve;
and a fixed threaded sleeve which is in interference pre-tightening sleeve joint with a shaft hole at one end of the shaft sleeve, and a through hole is arranged outside the fixed threaded sleeve and is installed with the high-low temperature box.
The outer sides of the two ends of the transfer shaft penetrate through the bearing A and the bearing B respectively and are rotatably arranged in the shaft sleeve.
And a check ring for axially positioning the bearing A is sleeved outside the adapter shaft between the fixed threaded sleeve and the bearing A.
The motor device assembly comprises a base B;
a bracket B arranged on the base B;
the adapter plate B can move up and down to adjust the position and is arranged on the bracket B, and the test motor is fixedly arranged on the adapter plate B;
the fixing plate B is fixed on the base B, and a through hole for the through connection of the adapter shaft is formed in the fixing plate B;
and the flexible coupling B is positioned between the adapter plate B and the fixed plate B, one end of the flexible coupling B is rotatably connected with the adapter shaft, the other end of the adapter shaft is rotatably connected with the motor device assembly, the flexible coupling B is rotatably connected with the dynamic torque sensor through the adapter shaft, and the other end of the shaft sleeve is tightly abutted to one end of the flexible coupling B in the through hole of the fixed plate B.
A test method completed by using an aircraft high-low temperature motor test system comprises the following steps: the test motor is arranged in the high-low temperature box through the motor device assembly, and the motor device assembly is rotatably connected with the measuring device assembly through a transfer shaft assembly penetrating through the high-low temperature box;
the dynamic torque sensor tests the torque and the rotating speed by adjusting the temperature of the high-low temperature box and applying load by the magnetic powder brake.
The beneficial effects of the utility model reside in that: because the measuring device assembly is rotatably connected with the motor device assembly through the adapter shaft assembly penetrating through the high-low temperature box, the testing motor can be rotatably installed on the motor device assembly, when the testing motor needs to perform high-temperature or low-temperature testing in the high-low temperature box, the temperature of the high-low temperature box can not influence the testing data result of the torque and rotation speed sensor, and the problems that the distance between the torque and rotation speed sensor and the motor is close, and the testing data result of the torque and rotation speed sensor can be influenced by the temperature of the motor in a high-temperature or low-temperature environment are solved.
Drawings
Fig. 1 is a schematic structural diagram of the present invention;
fig. 2 is a schematic structural diagram of the measuring device assembly of the present invention;
FIG. 3 is a schematic structural view of the adaptor shaft assembly of the present invention;
fig. 4 is a schematic structural view of the motor device assembly of the present invention;
in the figure: 1-measuring device components; 11-base a; 12-scaffold a; 13-a support; 14-Rib A; 15-fixing plate A; 16-a dynamic torque sensor; 17-flexible coupling a; 18-interposer a; 19-satisfy magnetic powder brake; 2-transfer shaft assembly; 21-fixing threaded sleeves; 22-a retaining ring; 23-bearing a; 24-a shaft sleeve; 25-a transfer shaft; 26-bearing B; 3-the electromechanical device assembly; 31-base B; 32-scaffold B; 33-a rib plate; 34-fixing plate B; 35-flexible coupling B; 36-interposer B; 4-high and low temperature box; 5-testing the motor.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
As shown in fig. 1-4.
The application discloses high low temperature motor test system of aircraft includes:
when in use, the motor device component 3 for testing the motor 5 is arranged in the high-low temperature box 4;
the measuring device assembly 1 can apply load to the test motor 5 and can test the output torque and the rotating speed of the test motor 5;
high low temperature box 4 that can temperature regulation height, motor device subassembly 3 are installed in high low temperature box 4, and motor device subassembly 3 is through change shaft subassembly 2 and measuring device subassembly 1 swivelling joint, and change shaft subassembly 2 runs through fixed mounting on high low temperature box 4 and obtains motor device subassembly 3 and support tightly.
Because measuring device subassembly 1 is through running through change shaft subassembly 2 and the rotatable coupling of motor device subassembly 3 on high low temperature case 4, test motor 5 is rotatable to be installed with motor device subassembly 3, when test motor 5 need carry out high temperature or low temperature test in high low temperature case 4, the temperature of high low temperature case 4 can not influence torque speed sensor test data result, has solved torque speed sensor and motor distance and has been close to, and the motor needs under high temperature or low temperature environment, has the problem that the temperature can influence torque speed sensor test data result.
The measuring device assembly 1 comprises a base A11 for providing a stress base, and a T-shaped groove is formed in the base A11;
the bracket A12 is fixedly arranged on a T-shaped groove of the base A11 through bolts and nuts, and a strip-shaped through hole is formed in the bracket A12;
an adapter plate A18 which can move up and down and is arranged on the strip-shaped through hole of the bracket A12 through a bolt and a nut, a magnetic powder brake 19 is fixed on the adapter plate A18, and the magnetic powder brake 19 applies load; the installation of the magnetic powder brake 19 with different ranges can be realized by replacing the adapter plate A18, so that the measurement requirements of different test motors 5 on different ranges are met, the adapter plate A18 can move up and down through the strip-shaped hole of the support A12, and the requirement of the magnetic powder brake 19 and the dynamic torque sensor 16 on the concentricity of the shafts is met;
the dynamic torque sensor 16 is fixedly arranged on the support 13, tests torque and rotating speed, and the output end of the dynamic torque sensor 16 is rotatably connected with the magnetic powder brake 19 through a flexible coupling A17;
the fixing plate A15 is welded and fixed on the base A11, the bottom of the fixing plate A15 is in reinforced connection with the base A11 through a ribbed plate A14, the fixing plate A15 is located on the side edge of the input end of the dynamic torque sensor 16, and a through hole is formed in the fixing plate A15 and corresponds to the input end of the dynamic torque sensor 16.
The transfer shaft assembly 2 comprises a transfer shaft 25, one end of the transfer shaft 25 is rotatably connected with the input end of the dynamic torque sensor 16, and the other end of the transfer shaft 25 is rotatably connected with the motor device assembly 3;
the outer sides of two ends of the transfer shaft 25 of the shaft sleeve 24 penetrate through the bearing A23 and the bearing B26 respectively and are rotatably arranged in the shaft sleeve 24;
the fixed threaded sleeve 21 is in interference pre-tightening sleeve connection with a shaft hole at one end of the shaft sleeve 24, and a through hole is formed in the outer side of the fixed threaded sleeve 21 and used for fixing and installing a screw or a bolt and the high and low temperature box 4; the shaft sleeve 24 is provided with a bearing B26 section which is positioned in the high-low temperature box 4, so that the change-over shaft assembly 2 penetrates through and is fixedly arranged on the high-low temperature box 4.
A retainer ring 22 for axially positioning the bearing A23 is sleeved outside the adapter shaft 25 between the fixed screw sleeve 21 and the bearing A23.
The motor device component 3 comprises a base B31 which is arranged in the high-low temperature box 4 and provides a stress base, and a T-shaped groove is formed in the base B31;
a bracket B32 fixedly arranged on the T-shaped groove of the base B31 through bolts and nuts, and the bracket B32 is provided with a strip-shaped through hole;
the adapter plate B36 is arranged on the strip-shaped through hole of the bracket B32 and can move up and down through a bolt and a nut to adjust the position, and the fixed shell of the test motor 5 is fixedly arranged on the adapter plate B36; the position of the adapter plate B36 is adjusted up and down on the strip-shaped through hole of the bracket B32, the coaxiality requirement of the test motor 5 is met, and the test requirements of test motors 5 of different specifications can be met by replacing the adapter plate B36;
a fixing plate B34 fixed on the base B31 near the side of the switching shaft assembly 2, wherein the fixing plate B34 is connected with the side of the bottom of the base B31 through a rib plate 33 in a reinforcing manner, and a through hole for the switching shaft 25 to penetrate through is arranged on the fixing plate B34;
the flexible coupling B35 is positioned between the adapter plate B36 and the fixed plate B34, one end of the flexible coupling B35 is rotatably connected with the adapter shaft 25, the other end of the adapter shaft 25 is rotatably connected with the motor device assembly 3, the flexible coupling B35 is rotatably connected with the dynamic torque sensor 16 through the adapter shaft 25, the other end of the shaft sleeve 24 is tightly abutted against one end of the flexible coupling B35 in the through hole of the fixed plate B34, the motor device assembly 3 is rotatably connected with the measuring device assembly 1 through the adapter shaft assembly 2, and the other end of the flexible coupling B35 is rotatably connected with the rotating shaft of the testing motor 5.
After the screw sleeve 21 with the shaft hole in interference fit at one end of the shaft sleeve 24 is fixedly installed on the high and low temperature box 4 through a bolt or a screw, the other end of the shaft sleeve 24 abuts against one end of a flexible coupling B35 of the motor device assembly 3 in the through hole of the fixing plate B34, so that the friction force generated by the interference fit pre-tightening force of the screw sleeve 21 and the shaft sleeve 24 bears the gravity of the measuring device assembly 1 and the motor device assembly 3 under the supporting effect of a bearing A23 and a bearing B26 through the transfer shaft 25.
The application provides a high low temperature motor test method of aircraft, has used foretell high low temperature motor test system of aircraft, includes the step: the testing motor 5 is arranged in the high and low temperature box 4 through the motor device component 3, and the motor device component 3 is rotatably connected with the measuring device component 1 through the adapter shaft component 2 penetrating through the high and low temperature box 4;
through adjusting the temperature of the high-low temperature box 4, the magnetic powder brake 19 applies load, and the dynamic torque sensor 16 tests torque and rotating speed, so that the test motor 5 can test rotating speed and torque data in the high-low temperature box 4 capable of adjusting the temperature at high and low temperature under high or low temperature environment, the problem that the rotating speed and torque data of the motor of the aircraft cannot be tested in the high and low temperature environment is solved, and the condition that the motor test data obtained in the normal temperature environment is inaccurate is avoided.
Claims (9)
1. An aircraft high and low temperature motor test system, comprising:
a motor arrangement assembly (3);
the measuring device assembly (1), the measuring device assembly (1) can apply load and can test torque and rotating speed;
high low temperature box (4) of ability temperature regulation height, motor device subassembly (3) are installed in high low temperature box (4), and motor device subassembly (3) are through switching axle subassembly (2) and measuring device subassembly (1) rotatable coupling, and fixed mounting is run through on high low temperature box (4) in switching axle subassembly (2).
2. The aircraft high and low temperature motor test system of claim 1, wherein: the measuring device assembly (1) comprises a magnetic particle brake (19) applying a load; and a dynamic torque sensor (16) rotatably connected to the magnetic particle brake (19).
3. The aircraft high and low temperature motor test system of claim 2, wherein: the measuring device assembly (1) further comprises a base A (11);
a bracket A (12) mounted on the base A (11);
an adapter plate A (18) which can move up and down and is arranged on the bracket A (12), and a magnetic powder brake (19) is fixed on the adapter plate A (18);
install support (13) on base A (11), support (13) interval is located support A (12) side, and dynamic torque sensor (16) fixed mounting is on support (13).
4. The aircraft high and low temperature motor test system of claim 2, wherein: the output end of the dynamic torque sensor (16) is rotatably connected with the magnetic powder brake (19) through a flexible coupling A (17).
5. The aircraft high and low temperature motor test system of claim 2, wherein: the measuring device assembly (1) further comprises a fixing plate A (15) fixed on the base A (11), the bottom of the fixing plate A (15) is connected with the base A (11) in an enhanced mode through a rib plate A (14), the fixing plate A (15) is located on the side edge of the input end of the dynamic torque sensor (16), and a through hole is formed in the fixing plate A (15) and corresponds to the input end of the dynamic torque sensor (16).
6. The aircraft high and low temperature motor test system of claim 1, wherein: the switching shaft assembly (2) comprises a switching shaft (25), one end of the switching shaft (25) is rotatably connected with the input end of the dynamic torque sensor (16), and the other end of the switching shaft (25) is rotatably connected with the motor device assembly (3);
the two ends of the switching shaft (25) penetrate through the shaft sleeve (24) and are rotatably arranged in the shaft sleeve (24);
and the fixed threaded sleeve (21) is in interference pre-tightening sleeve joint with a shaft hole at one end of the shaft sleeve (24), and a through hole is arranged on the outer side of the fixed threaded sleeve (21) and is installed with the high-low temperature box (4).
7. The aircraft high and low temperature motor test system of claim 6, wherein: the outer sides of two ends of the transfer shaft (25) penetrate through the bearing A (23) and the bearing B (26) respectively and are rotatably arranged in the shaft sleeve (24).
8. The aircraft high and low temperature motor test system of claim 6, wherein: and a retainer ring (22) for axially positioning the bearing A (23) is sleeved outside the adapter shaft (25) between the fixed threaded sleeve (21) and the bearing A (23).
9. The aircraft high and low temperature motor test system of claim 1, wherein: the motor arrangement assembly (3) comprises a base B (31);
a bracket B (32) mounted on the base B (31);
an adapter plate B (36) which can move up and down and is arranged on the bracket B (32) at an adjustable position, and a test motor (5) is fixedly arranged on the adapter plate B (36);
a fixing plate B (34) fixed on the base B (31), wherein the fixing plate B (34) is provided with a through hole for the through connection of the adapter shaft (25);
and the flexible coupling B (35) is positioned between the adapter plate B (36) and the fixing plate B (34), one end of the flexible coupling B (35) is rotatably connected with the adapter shaft (25), the flexible coupling B (35) is rotatably connected with the dynamic torque sensor (16) through the adapter shaft (25), and the other end of the shaft sleeve (24) is tightly abutted to one end of the flexible coupling B (35) in the through hole of the fixing plate B (34).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221096436.1U CN217687613U (en) | 2022-05-09 | 2022-05-09 | High low temperature motor test system of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221096436.1U CN217687613U (en) | 2022-05-09 | 2022-05-09 | High low temperature motor test system of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217687613U true CN217687613U (en) | 2022-10-28 |
Family
ID=83737786
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221096436.1U Active CN217687613U (en) | 2022-05-09 | 2022-05-09 | High low temperature motor test system of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217687613U (en) |
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2022
- 2022-05-09 CN CN202221096436.1U patent/CN217687613U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: A Testing System for High and Low Temperature Motors of Aircraft Effective date of registration: 20230504 Granted publication date: 20221028 Pledgee: Bank of Guiyang Limited by Share Ltd. Huaxi branch Pledgor: Guizhou qianhang Electric Co.,Ltd. Registration number: Y2023980039585 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Granted publication date: 20221028 Pledgee: Bank of Guiyang Limited by Share Ltd. Huaxi branch Pledgor: Guizhou qianhang Electric Co.,Ltd. Registration number: Y2023980039585 |