A test bench for testing a membrane of a transmission shaft of a drone

Abstract

A kind of test test bench for unmanned aerial vehicle transmission shaft diaphragm, it is related to the performance test field of unmanned aerial vehicle transmission shaft diaphragm, including test bench and the drive electric spindle in test bench from left to right sequentially connected, torque closed loop component and driven electric spindle;Torque closed loop component includes transmission shaft A, two sets of test diaphragm, two sets of accompanying test diaphragm, dynamic torque sensor and transmission shaft B, transmission shaft A is fixedly connected with drive electric spindle, transmission shaft B is fixedly connected with driven electric spindle;The stepped shaft section of transmission shaft A is equipped with the loading flange connected by expansion sleeve, one set of test diaphragm is fixedly connected on the right end surface of loading flange;Another set of test diaphragm is fixedly connected on the left end surface of the adapter flange on transmission shaft B;The utility model is simple and compact, can satisfy the test of high rotational speed, different torque and flexible misalignment adjustment requirement simultaneously.

Description

Technical Field

[0001] This utility model relates to the field of performance testing technology for diaphragms of drone drive shafts, and in particular to a test bench for diaphragms of drone drive shafts. Background Technology

[0002] As a key component in the transmission system of UAVs, the drive shaft diaphragm mainly serves to connect the power output end with the actuator, transmit torque, and compensate for installation deviations. Its working environment is characterized by high speed, variable load, and frequent vibration. During long-term service, it is extremely prone to fatigue failure, which can lead to transmission system failure. Therefore, conducting accurate and comprehensive fatigue performance testing on the UAV drive shaft diaphragm is a crucial step in ensuring the reliability of the UAV transmission system.

[0003] Existing diaphragm fatigue testing benches generally suffer from limited functionality. Traditional fatigue testing benches can only apply a single load (such as pure torque or pure axial force) or a single motion state (such as low-speed uniform motion), and cannot simultaneously accommodate the combined application of high speed, variable torque, and misalignment. This results in a significant difference between the test conditions and the actual working environment of the diaphragm, making it difficult for the test results to accurately reflect the true fatigue performance of the diaphragm. While some commercially available testing equipment can meet the requirements of high-speed loading, they have significant functional limitations: either the range of loading torque is limited, failing to cover the maximum torque value that the diaphragm coupling of the UAV transmission may withstand in actual operation; or the adjustment range of loading offset is limited, making it difficult to simulate misalignment conditions under different installation errors. Furthermore, the few customized devices that can simultaneously meet the requirements of high speed, different torques, and flexible misalignment adjustment have complex loading methods, typically requiring the integration of multiple independent power drive units, torque detection units, and misalignment adjustment mechanisms. This results in a cumbersome overall structure, high manufacturing costs, and significantly increased maintenance difficulty and costs, making it difficult to achieve large-scale application in industrial production. Therefore, proposing a diaphragm fatigue testing device that is compact, cost-controllable, and capable of simultaneously achieving high-speed loading, torque application, and simulation of multiple types of misalignment has become an urgent technical problem to be solved in this field. Utility Model Content

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a test bench for diaphragms of unmanned aerial vehicle drive shafts.

[0005] The technical solution adopted in this utility model is: A test bench for a drive shaft diaphragm of an unmanned aerial vehicle (UAV) includes a test bench base and a drive electric spindle, a torque closed-loop assembly, and a driven electric spindle connected sequentially from left to right on the test bench base. The torque closed-loop assembly includes a drive shaft A, two sets of test diaphragms, two sets of auxiliary test diaphragms, a dynamic torque sensor, and a drive shaft B. The drive shaft A is fixedly connected to the drive electric spindle, and the drive shaft B is fixedly connected to the driven electric spindle. A loading flange is provided on the stepped section of the drive shaft A via an expansion sleeve, and one set of test diaphragms is fixedly connected to the right end face of the loading flange; from left to right, a transition flange, a dynamic torque sensor and a fixed flange are connected on the drive shaft B, with an expansion sleeve between the fixed flange and the drive shaft B, and another set of test diaphragms is fixedly connected to the left end face of the transition flange. A set of test diaphragms is fixed at the flange end of the right end of drive shaft A and the flange end of the left end of drive shaft B. An inner cylinder of the fixture is fixedly connected between the two sets of test diaphragms. An outer cylinder of the fixture is connected between the two sets of test diaphragms, and the outer cylinder of the fixture is located outside the inner cylinder of the fixture.

[0006] The test bench for the diaphragm of the drive shaft of the unmanned aerial vehicle has a drive electric spindle and a driven electric spindle, which are respectively fixed on the upper two sides of the test bench base by bearing seats.

[0007] The test bench for the diaphragm of the drive shaft of the unmanned aerial vehicle has multiple expansion bolts evenly spaced on the circumferential surface of the expansion sleeve.

[0008] The test bench for the diaphragm of the drive shaft of the UAV is described above. The dynamic torque sensor is fixed on the test bench base by the sensor base. The left flange of the dynamic torque sensor is fixedly connected to the adapter flange by bolts, and the right flange is fixedly connected to the fixed flange by bolts.

[0009] The test bench for the diaphragm of the drive shaft of the UAV has a groove on the outer circular surface of the loading flange, and a lever arm is engaged in the groove.

[0010] The test bench for the diaphragm of the UAV drive shaft has a triangular loading flange with connection holes A at its three vertices. The test diaphragm has a hexagonal structure with bolt holes at its six vertices. The three connection holes A on the loading flange correspond to three bolt holes on a set of test diaphragms on the left side and are fixedly connected by a bolt and nut assembly. The other three bolt holes on the test diaphragm are fixedly connected to the flange holes at the left end of the tooling outer cylinder by a bolt and nut assembly.

[0011] The test bench for the diaphragm of the UAV drive shaft has three protrusions that extend evenly along the outer circumference of the adapter flange. The connection holes B on the three protrusions correspond to three bolt holes on a set of test diaphragms on the right side and are fixedly connected by a bolt and nut assembly. The other three bolt holes on the test diaphragm are fixedly connected to the flange holes on the right end of the tooling outer cylinder by a bolt and nut assembly.

[0012] The test bench for the diaphragm of the UAV drive shaft has three bolt holes extending from the outer circumference of the flange end of the right end of drive shaft A and the flange end of the left end of drive shaft B. These bolt holes correspond to the three bolt holes of the two sets of test diaphragms and are fixed by bolt and nut assemblies. The remaining bolt holes on the two sets of test diaphragms are fixedly connected to the flange holes at the left and right ends of the tooling inner cylinder by bolt and nut assemblies.

[0013] The test bench for the diaphragm of the UAV drive shaft has the same structure as the test diaphragm.

[0014] Due to the adoption of the technical solution described above, this utility model has the following advantages: The test bench for diaphragms of UAV drive shafts described in this utility model connects drive shaft A to the loading flange and drive shaft B to the fixed flange via expansion sleeves and bolts. The driven electric spindle's bearing is raised, and torque is generated by twisting the lever arm on the loading flange at a certain angle. The expansion sleeve is then locked to maintain the torque. The motor rotates at high speed while applying torque, completing high-speed rotational fatigue and strength tests with angular torque loading. By adjusting the tightness of the two test diaphragms fixed to the loading flange and the transition flange, high-speed rotational fatigue and strength tests with angular and axial offset torque loading are completed. This utility model has a simple and compact structure, is easy to use, and can simultaneously meet the requirements of high speed, different torques, and flexible misalignment adjustment. It also has low manufacturing cost and simple maintenance. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall design of this utility model.

[0016] Figure 2 This is a front structural diagram of the loading flange of this utility model.

[0017] Figure 3 This is a schematic diagram of the front structure of the test membrane of this utility model.

[0018] In the diagram: 1. Drive electric spindle; 2. Shaft seat; 3. Expansion bolt; 4. Expansion sleeve; 5. Test diaphragm; 6. Tooling outer cylinder; 7. Tooling inner cylinder; 8. Accompanying diaphragm; 9. Dynamic torque sensor; 10. Driven electric spindle; 11. Test bench; 12. Loading flange; 13. Drive shaft A; 14. Sensor base; 15. Fixed flange; 16. Drive shaft B; 17. Adapter flange; 18. Connecting hole A; 19. Bolt and nut assembly. Detailed Implementation

[0019] The present invention will be further explained below with reference to the accompanying drawings and embodiments. However, this explanation should not be construed as limiting the scope of protection of the present invention. The purpose of disclosing the present invention is to protect all technical improvements within the scope of the present invention.

[0020] Combined with appendix Figure 1-3 The test bench for the diaphragm of the drive shaft of a UAV includes a test bench base 11 and a drive electric spindle 1, a torque closed-loop assembly and a driven electric spindle 10 connected sequentially from left to right on the test bench base 11. The drive electric spindle 1 and the driven electric spindle 10 are respectively fixed on the upper two sides connected to the test bench base 11 by bearing seats 2. The torque closed-loop assembly includes a drive shaft A13, two sets of test diaphragms 5, two sets of auxiliary test diaphragms 8, a dynamic torque sensor 9 and a drive shaft B16. The drive shaft A13 is fixedly connected to the drive electric spindle 1 and the drive shaft B16 is fixedly connected to the driven electric spindle 10. A loading flange 12 is provided on the stepped section of the drive shaft A13 via an expansion sleeve 4. One set of test diaphragms 5 is fixedly connected to the right end face of the loading flange 12. A transition flange 17, a dynamic torque sensor 9, and a fixed flange 15 are connected sequentially from left to right on the drive shaft B16. An expansion sleeve 4 is provided between the fixed flange 15 and the drive shaft B16. Multiple expansion bolts 3 are evenly spaced on the circumferential surface of the expansion sleeve 4. Another set of test diaphragms 5 is fixedly connected to the left end face of the transition flange 17. A set of test diaphragms 8 is fixed at the flange end of the right end of the drive shaft A13 and the flange end of the left end of the drive shaft B16. A tooling inner cylinder 7 is fixedly connected between the two sets of test diaphragms 8. A tooling outer cylinder 6 is connected between the two sets of test diaphragms 5, and the tooling outer cylinder 6 is located outside the tooling inner cylinder 7.

[0021] Specifically, the dynamic torque sensor 9 is fixed on the test bench 11 via the sensor base 14, and the left flange of the dynamic torque sensor 9 is fixedly connected to the adapter flange 17 by bolts, and the right flange is fixedly connected to the fixed flange 15 by bolts.

[0022] Specifically, a slot is provided on the outer circular surface of the loading flange 12, and a force arm is engaged in the slot. The slot and the force arm are used to rotate the rotary transmission shaft A13 on the loading flange 12 by a certain angle to generate torque. The expansion sleeve locks and maintains the torque. The torque is applied while the motor rotates at high speed, thus completing the high-speed rotation fatigue test with torque loading with angular and axial offset.

[0023] Specifically, the loading flange 12 has a triangular structure with connection holes A18 at each of its three vertices. The test diaphragm has a hexagonal structure with bolt holes at each of its six vertices. The three connection holes A18 on the loading flange 12 correspond to three bolt holes on a set of test diaphragms 5 located on the left side, and are fixedly connected by bolt and nut assembly 19. The other three bolt holes on the test diaphragm 5 are fixedly connected to the flange hole at the left end of the tooling outer cylinder 6 by bolt and nut assembly 19.

[0024] Specifically, three protrusions extend evenly along the outer circumference of the adapter flange 17. The connection holes B on the three protrusions correspond to three bolt holes on a set of test diaphragms 5 located on the right side, and are fixedly connected by bolt and nut assembly 19. The other three bolt holes on the test diaphragm 5 are fixedly connected to the flange hole at the right end of the tooling outer cylinder 6 by bolt and nut assembly 19.

[0025] Specifically, three bolt holes extend from the outer circumference of the flange end on the right end of the drive shaft A13 and the flange end on the left end of the drive shaft B16, respectively, corresponding to the three bolt holes of the two sets of test diaphragms 8, and are fixed by bolt and nut assembly 19. The remaining bolt holes on the two sets of test diaphragms 8 are fixedly connected to the flange holes at the left and right ends of the tooling inner cylinder by bolt and nut assembly 19.

[0026] The test bench for the diaphragm of the UAV drive shaft has the following transmission principle: the output end of the motor is fixedly connected to the drive electric spindle 1. When the motor is turned on, the drive shaft A13 and the expansion sleeve 4 and loading flange 12 outside the drive shaft A13 rotate. Two sets of test diaphragms 5 and tooling outer cylinder 6 are fixedly connected between the loading flange 12 and the transition flange 17. Therefore, the tooling outer cylinder 6 and the transition flange 17 also rotate with the loading flange 12. Two sets of auxiliary test diaphragms 8 and tooling inner cylinder 7 are connected between the flange end of the right end of the drive shaft A13 and the flange end of the left end of the drive shaft B16. Therefore, the two sets of auxiliary test diaphragms 8, tooling inner cylinder 7 and drive shaft B16 rotate with the drive shaft A13.

[0027] The test bench for the diaphragm of the drive shaft of a UAV described in this utility model is used. Both the test diaphragm 5 and the auxiliary diaphragm 8 are flexible diaphragms with identical structures, except that the size of the test diaphragm 5 is larger than that of the auxiliary diaphragm 8. When testing the test diaphragm 5 under high speed, wide torque range, and misalignment adjustment requirements, the bearing seat 2 at the driven electric spindle 10 is raised before being fixed to the test bench base 11. Since both the test diaphragm 5 and the auxiliary diaphragm 8 are flexible diaphragms, an angle is formed between the driven electric spindle 10 and the drive electric spindle 1. The size of the angle is adjusted by raising the bearing seat 2. Under loading conditions... The loading flange 12 is secured in the slot of the loading flange 12. Rotating the loading flange 12 causes it to rotate at a certain angle on the drive shaft A13, generating torque. The expansion sleeve 4 is fixed with the expansion bolt 3 to maintain the torque. The motor is turned on to drive the drive electric spindle 1 to rotate, causing the entire machine except for the test bench 11 and the shaft seat 2 to start rotating. This completes the torque loading rotation test with an angle. By adjusting the angle and the motor speed, the torque can be increased or decreased. Therefore, a high-speed rotation test with torque loading with an angle can be performed to test the fatigue and strength of the diaphragm 5 under high speed torque loading, while also solving the problem of misalignment adjustment requirements.

[0028] When testing the test diaphragm 5 at high speed, wide torque range, and with requirements for misalignment adjustment and axial offset, the bearing seat 2 at the driven electric spindle 10 is raised and then fixed on the test bench 11, forming an offset angle between the driven electric spindle 10 and the drive electric spindle 1. The lever arm is engaged in the slot of the loading flange 12, and the lever arm is rotated to rotate the loading flange 12 on the drive shaft A13 to generate torque. The expansion sleeve 4 is fixed with the expansion bolt 3 to maintain the torque. The bolt and nut assembly 19 is used to adjust the two sets of test diaphragms 5 at the loading flange 12 and the rotation... By adjusting the tightness of the flange 17, the two sets of test diaphragms 5 are compressed to different degrees in the axial direction. The motor is turned on to drive the electric spindle 1 to rotate, so that the whole machine except for the test bench 11 and the shaft seat 2 starts to rotate. This completes the torque loading test with angular and axial offset. By adjusting the angular angle, motor speed, and the degree of compression of the two sets of test diaphragms 5, the torque can be increased or decreased at the same time. Therefore, a high-speed rotational test with torque loading with angular and axial offset can be performed to test the fatigue and strength of the test diaphragm 5 under high speed torque loading.

[0029] The parts of this utility model not described in detail are existing technologies.

[0030] The embodiments selected herein for the purpose of disclosing the utility model are currently considered suitable; however, it should be understood that the present invention is intended to include all variations and modifications of the embodiments that fall within the scope of the present concept and utility model.

Claims

1. A test bench for a diaphragm of a UAV drive shaft, comprising a test bench base and a drive electric spindle, a torque closed-loop assembly, and a driven electric spindle connected sequentially from left to right on the test bench base; characterized in that: The torque closed-loop assembly includes a drive shaft A, two sets of test diaphragms, two sets of auxiliary test diaphragms, a dynamic torque sensor, and a drive shaft B. Drive shaft A is fixedly connected to the drive electric spindle, and drive shaft B is fixedly connected to the driven electric spindle. A loading flange connected by an expansion sleeve is provided on the stepped section of drive shaft A, and one set of test diaphragms is fixedly connected to the right end face of the loading flange. From left to right, a transition flange, a dynamic torque sensor, and a fixed flange are connected to drive shaft B in sequence. An expansion sleeve is provided between the fixed flange and drive shaft B, and another set of test diaphragms is fixedly connected to the left end face of the transition flange. A set of auxiliary test diaphragms is fixedly fixed at the flange end of the right end of drive shaft A and the flange end of the left end of drive shaft B. An inner tooling cylinder is fixedly connected between the two sets of auxiliary test diaphragms, and an outer tooling cylinder is connected between the two sets of test diaphragms, with the outer tooling cylinder located outside the inner tooling cylinder.

2. The test bench for the diaphragm of a UAV drive shaft according to claim 1, characterized in that: Both the drive electric spindle and the driven electric spindle are fixed to the upper two sides of the test bench via bearing seats.

3. The test bench for the diaphragm of a UAV drive shaft according to claim 1, characterized in that: Multiple expansion bolts are evenly spaced on the circumferential surface of the expansion sleeve.

4. The test bench for the diaphragm of a UAV drive shaft according to claim 1, characterized in that: The dynamic torque sensor is fixed to the test bench via a sensor base, and the left flange of the dynamic torque sensor is fixedly connected to the adapter flange by bolts, while the right flange is fixedly connected to the fixed flange by bolts.

5. The test bench for a diaphragm of a UAV drive shaft according to claim 1, characterized in that: A groove is provided on the outer circular surface of the loading flange, and a lever is engaged in the groove.

6. The test bench for a diaphragm of a UAV drive shaft according to claim 1, characterized in that: The loading flange has a triangular structure with connection holes A at each of its three vertices. The test diaphragm has a hexagonal structure with bolt holes at each of its six vertices. The three connection holes A on the loading flange correspond to three bolt holes on a set of test diaphragms located on the left side, and are fixedly connected by a bolt and nut assembly. The other three bolt holes on the test diaphragm are fixedly connected to the flange holes at the left end of the tooling outer cylinder by a bolt and nut assembly.

7. The test bench for a diaphragm of a UAV drive shaft according to claim 1, characterized in that: Three protrusions extend evenly along the outer circumference of the adapter flange. The connection holes B on the three protrusions correspond to three bolt holes on a set of test diaphragms on the right side and are fixedly connected by bolt and nut assembly. The other three bolt holes on the test diaphragms are fixedly connected to the flange holes on the right end of the tooling outer cylinder by bolt and nut assembly.

8. The test bench for a diaphragm of a UAV drive shaft according to claim 1, characterized in that: Three bolt holes extend from the outer circumference of the flange end on the right end of drive shaft A and the flange end on the left end of drive shaft B. These holes correspond to the three bolt holes of the two sets of test diaphragms and are fixed by bolt and nut assemblies. The remaining bolt holes on the two sets of test diaphragms are fixedly connected to the flange holes at the left and right ends of the tooling inner cylinder by bolt and nut assemblies.

9. The test bench for a diaphragm of a UAV drive shaft according to claim 1, characterized in that: The test membrane has the same structure as the companion membrane.

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