Space mechanism gear part lubrication technology evaluation device and test method thereof

Abstract

The invention discloses a space mechanism gear part lubrication technology evaluation device and a test method thereof, the evaluation device adopts a power closed layout, and comprises a vacuum tank and a test device installed in the vacuum tank; the test device comprises a driving motor, a first straight gear box, a first planetary reducer, a torque sensor, a second straight gear box, a second planetary reducer and a torsional spring loader. The driving motor is in transmission connection with the input end of the straight gear box I; the first straight gear box, the first planetary reducer, the torque sensor, the second straight gear box, the second planetary reducer, the torsional spring loader and the first straight gear box are sequentially in transmission connection to form a transmission closed loop. The torsional spring loader is used for setting loading torque; the torque sensor is used for monitoring loading torque and rotating speed. The evaluation device can simultaneously carry out vacuum environment tests of two groups of straight gears and two groups of planetary gears under equivalent contact stress, and is used for lubricating scheme optimization, comprehensive performance evaluation and service life tests of typical transmission parts.

Description

Technical Field

[0001] This invention belongs to the field of vacuum testing technology for transmission components of space mechanisms, specifically relating to a device for evaluating the lubrication technology of gear components in space mechanisms and its testing method. Background Technology

[0002] Spur gear transmission pairs and planetary gear transmission pairs are widely used in various space mechanisms such as camera focusing mechanisms, antenna deployment mechanisms, and scanning mechanisms. It is often necessary to carry out space lubrication scheme optimization, transmission comprehensive performance evaluation and life test work according to the usage requirements of these mechanisms.

[0003] However, conducting tests directly on the entire space mechanism has drawbacks such as high testing costs and long testing cycles. Therefore, it is necessary to develop testing devices with short testing cycles and low costs, tailored to the usage requirements of typical transmission components in the space mechanism. Summary of the Invention

[0004] This invention provides a lubrication technology evaluation device and test method for gear components in space mechanisms. The evaluation device and test method can simultaneously conduct vacuum environment tests on two sets of spur gears and two sets of planetary gears under equivalent contact stress, targeting the usage requirements of spur gears and planetary gears in space mechanisms. This is used for the optimization of lubrication schemes, comprehensive performance evaluation and life test of these typical transmission components, and can shorten the test time and reduce the test cost.

[0005] To achieve the above objectives, the present invention adopts the following specific technical solution: First, the present invention provides a lubrication technology evaluation device for gear components of space mechanisms. The evaluation device adopts a power-enclosed layout and includes a vacuum tank and a testing device. The test apparatus is installed inside the vacuum chamber and is used to simulate the transmission component test of a space mechanism in a vacuum and high / low temperature alternating environment. The test apparatus includes a drive motor, a spur gearbox I, a planetary reducer I, a torque sensor, a spur gearbox II, a planetary reducer II, and a torsion spring loader; The drive motor is connected to the input end of the first spur gearbox; the first spur gearbox, the first planetary reducer, the torque sensor, the second spur gearbox, the second planetary reducer, the torsion spring loader, and the first spur gearbox are connected in sequence to form a transmission closed loop; The torsion spring loader is used to set the loading torque to achieve torque loading on the planetary reducer, the spur gearbox, the spur gearbox, and the planetary reducer. The torque sensor is used to monitor the applied torque and rotational speed.

[0006] Furthermore, the drive motor, the first spur gearbox, the first planetary reducer, the torque sensor, the second spur gearbox, the second planetary reducer, the torsion spring loader, and the first spur gearbox are connected by a coupling.

[0007] Furthermore, the planetary reducer one, the spur gearbox one, the spur gearbox two, and the planetary reducer two employ different lubrication schemes.

[0008] Furthermore, a harmonic reducer or an RV reducer can be used instead of the planetary reducer.

[0009] Furthermore, based on the input speed and output torque of the first planetary reducer obtained from the space mechanism, the contact stress of the spur gear transmission pairs in the first and second spur gearboxes, and the contact stress between each gear pair in the second planetary reducer, the parameters of each gear pair in the first, second, and second planetary reducers under the equivalent contact stress are calculated, and the torque load required to be applied by the torsion spring loader is calculated.

[0010] In addition, the present invention also provides a test method using the above-mentioned evaluation device for lubrication technology of gear components in space mechanisms, the test method comprising the following steps: Step 1: Use spur gearbox 1, spur gearbox 2, and planetary reducer 2 as speed increasers and design the transmission ratio. Select planetary reducer 1, which is the same as the one used in the space mechanism, so that the output speed of the motor is the same as the speed after the speed change through planetary reducer 1, spur gearbox 2, planetary reducer 2, and spur gearbox 1, forming a closed loop. Step 2: Design the meshing parameters of the gears in spur gearbox 1 and spur gearbox 2 so that the contact stress on the gear tooth surface reaches the predetermined contact stress. Step 3: Lubricate the gears in planetary reducer 1, planetary reducer 2, spur gearbox 1, and spur gearbox 2. Step 4: Connect the drive motor, spur gearbox 1, planetary reducer 1, torque sensor, spur gearbox 2, planetary reducer 2 and torsion spring loader through couplings to form a test device, and adjust the torsion spring loader so that the torque sensor reading is a predetermined value, and lock each coupling. Step 5: Turn on the drive motor and adjust its output speed to the predetermined speed to complete the debugging. Step 6: Place the test device into the vacuum chamber, evacuate the vacuum chamber to form a vacuum chamber inside, and control the temperature inside the vacuum chamber to the test temperature. After the temperature stabilizes, turn on the drive motor to carry out the test. Step 7: After the required gear meshing life of the space mechanism is reached, stop the test, open the vacuum tank, take out the test device, disassemble the spur gearbox 1, spur gearbox 2, planetary reducer 1 and planetary reducer 2, compare and evaluate the advantages and disadvantages of the lubrication schemes, and select the optimal lubrication scheme to lubricate the gear transmission pairs in the space mechanism.

[0011] Furthermore, in step three, the lubrication treatment methods for the gears in planetary reducer one, planetary reducer two, spur gearbox one, and spur gearbox two can be selected from alternative lubrication technologies and their matching schemes that need to be compared and evaluated.

[0012] Compared with the prior art, the technical solution of the present invention has the following beneficial effects: 1. In response to the usage requirements of spur gears and planetary gears in space mechanisms, the space mechanism gear component lubrication technology evaluation device of the present invention can simultaneously conduct vacuum environment tests on two sets of spur gears and two sets of planetary gears under equivalent contact stress, ensuring that the contact stress of each tested component is consistent with the actual requirements, realizing typical transmission component tests under equivalent contact stress, and conducting lubrication scheme optimization, comprehensive performance evaluation and life test of space mechanism gear transmission pairs. It does not require testing the entire space mechanism, and has the advantages of being simple and easy to implement, shortening test time and reducing test costs.

[0013] 2. The space mechanism gear component lubrication technology evaluation device of the present invention adopts a power closed layout, which is simple in structure and highly reliable; the contact stress of the gear test piece in each gearbox can be changed by adjusting the gear meshing width, and the adjustment method of meshing width is relatively simple.

[0014] 3. The test principle and scheme of the space mechanism gear component lubrication technology evaluation device and test method of the present invention can replace the planetary reducer with other gear transmission components such as harmonic reducer or RV reducer, so as to realize the test tasks of more types of typical transmission components. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the principle of the lubrication technology evaluation device for gear components in space mechanisms according to the present invention; Figure label: 1-Vacuum tank, 2-Drive motor, 3-Spur gearbox I, 4-Planetary reducer I, 5-Torque sensor, 6-Spur gearbox II, 7-Planetary reducer II, 8-Torsion spring loader, 9-Coupling. Detailed Implementation

[0016] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0017] In the description of this invention, it should be understood that the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances. Furthermore, in the description of this invention, unless otherwise stated, "multiple" refers to two or more. "And / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. The character " / " generally indicates that the preceding and following related objects have an "or" relationship.

[0018] Example 1 This embodiment provides a device for evaluating the lubrication technology of gear components in space mechanisms, such as... Figure 1 As shown, the evaluation device adopts a power-enclosed layout, including a vacuum tank 1 and a test device; the test device is installed inside the vacuum tank 1 and is used to simulate the transmission component test of the space mechanism in a vacuum and high and low temperature alternating environment.

[0019] Vacuum container 1 has a vacuum chamber, which provides a vacuum environment for the test apparatus and also provides the required test temperature. The vacuum container 1 simulates the testing of transmission components of a space mechanism under vacuum and alternating high and low temperature environments.

[0020] The test apparatus includes a drive motor 2, a spur gearbox 3, a planetary reducer 4, a torque sensor 5, a second spur gearbox 6, a second planetary reducer 7, and a torsion spring loader 8. The drive motor 2 is connected to the input end of the spur gearbox 3 for inputting torque. The spur gearbox 3, planetary reducer 4, torque sensor 5, second spur gearbox 6, second planetary reducer 7, torsion spring loader 8, and spur gearbox 3 are sequentially connected by a coupling 9 to form a closed-loop transmission system, used to simulate the transmission component testing of a space mechanism under vacuum and alternating high and low temperature environments.

[0021] The torsion spring loader 8 is used to set the loading torque to apply torque to planetary reducer 4, spur gearbox 3, spur gearbox 6, and planetary reducer 7. During the test, the loading torque of the torsion spring loader 8 is set according to actual needs to apply torque to the test specimens planetary reducer 4, spur gearbox 3, spur gearbox 6, and planetary reducer 7 in the entire test apparatus.

[0022] Torque sensor 5 is used to monitor the loading torque and rotational speed. The test loading torque and test rotational speed are monitored through torque sensor 5.

[0023] Planetary reducer 4, spur gearbox 3, spur gearbox 6, and planetary reducer 7 employ different lubrication schemes. When lubricating the gears in planetary reducer 4, spur gearbox 3, spur gearbox 6, and planetary reducer 7, the lubrication method can be selected from alternative lubrication technologies and their compatibility schemes that require comparative evaluation. The gear transmission pairs in planetary reducer 4, spur gearbox 3, spur gearbox 6, and planetary reducer 7 can choose the same or different lubrication schemes, such as solid lubrication, grease lubrication, and solid-liquid composite lubrication. To facilitate comparison of the advantages and disadvantages of lubrication schemes, different lubrication schemes can be selected simultaneously for the spur gear pairs in spur gearbox 3 and spur gearbox 6; similarly, different lubrication schemes can be selected simultaneously for the planetary gear pairs in planetary reducer 4 and planetary reducer 7.

[0024] When calculating the loading torque, planetary reducer 4 is selected as the same planetary reducer as the space mechanism. Based on the input speed and output torque of planetary reducer 4 obtained from the space mechanism, the contact stress of the spur gear transmission pairs in spur gearbox 3 and spur gearbox 6, and the contact stress between each gear pair in planetary reducer 7, the parameters of each gear pair in spur gearbox 3, spur gearbox 6, and planetary reducer 7 under equivalent contact stress are calculated, and the torque load required to be applied by torsion spring loader 8 is calculated.

[0025] In addition to planetary reducers, the above-mentioned evaluation device can also evaluate harmonic reducers or RV reducers, that is, replace the above-mentioned planetary reducer 4 with a harmonic reducer or RV reducer.

[0026] Example 2 This embodiment provides a test method using the above-described evaluation device for lubrication technology of gear components in spatial mechanisms. The test method includes the following steps: Step 1: Use spur gearbox 3, spur gearbox 6, and planetary reducer 7 as speed increasers and design the transmission ratio. Select planetary reducer 4, which is the same as the space mechanism, so that the output speed of the motor is the same as the speed after the speed change through planetary reducer 4, spur gearbox 6, planetary reducer 7, and spur gearbox 3, forming a closed loop. Step 2: Design the meshing parameters of the gears in spur gearbox 3 and spur gearbox 6 so that the contact stress on the gear tooth surface reaches the predetermined contact stress. Step 3: Lubricate the gears in planetary reducer 4, planetary reducer 7, spur gearbox 3, and spur gearbox 6. The lubrication method for the gears in planetary reducer 4, planetary reducer 7, spur gearbox 3, and spur gearbox 6 can be selected from alternative lubrication technologies and their matching schemes that need to be compared and evaluated, such as solid lubrication, grease lubrication, solid-liquid composite lubrication, etc.

[0027] Step 4: Connect drive motor 2, spur gearbox 3, planetary reducer 4, torque sensor 5, spur gearbox 6, planetary reducer 7 and torsion spring loader 8 through coupling 9 to form a test device, and adjust torsion spring loader 8 so that the torque sensor 5 shows a predetermined value, and lock each coupling 9. Step 5: Turn on drive motor 2 and adjust its output speed to the predetermined speed to complete the debugging; Step 6: Place the test device into vacuum chamber 1, evacuate vacuum chamber 1 to form a vacuum chamber inside, and control the temperature inside the vacuum chamber to the test temperature. After the temperature stabilizes, turn on drive motor 2 to conduct the test. Step 7: After the required gear meshing life of the space mechanism is reached, stop the test, open vacuum tank 1, take out the test device, disassemble spur gearbox 3, spur gearbox 6, planetary reducer 4 and planetary reducer 7, compare and evaluate the advantages and disadvantages of the lubrication schemes, and select the optimal lubrication scheme to lubricate the gear transmission pairs in the space mechanism.

[0028] Example 3 This embodiment uses a complex space mechanism as an example to illustrate the specific process of conducting tests using the aforementioned space mechanism gear component lubrication technology evaluation device and test method.

[0029] This space mechanism includes multiple planetary reducers and spur gear transmission pairs. Planetary reducer 4 has a reduction ratio of 100:1, an input speed of 300 rpm, and an output torque of 15 Nm. Planetary reducer 7 has a reduction ratio of 25:1, an output torque of 7.5 Nm, and a spur gear tooth surface contact stress of 300 MPa. According to the test method and evaluation device of this invention, the specific test implementation steps are as follows: Step one: Design the transmission ratio of spur gearbox 3 and spur gearbox 6 to be 1:2, and the transmission ratio of planetary reducer 7 to be 1:25, so that spur gearbox 3, spur gearbox 6, and planetary reducer 7 are all used as speed increasers. Planetary reducer 4, the same as that used in this space mechanism, is selected. The output speed of drive motor 2 is 300 rpm. Figure 1As shown, after passing through planetary reducer 4, the speed is reduced to 3 rpm. After passing through spur gearbox 6 (transmission ratio 1:2) to increase the speed to 6 rpm, and then through planetary reducer 7 (transmission ratio 1:25) to increase the speed to 150 rpm, the speed is finally increased back to 300 rpm after passing through spur gearbox 3, forming a closed loop.

[0030] Step 2: Design the gear meshing parameters in spur gearbox 3 and spur gearbox 6, including module, number of teeth, meshing tooth width, etc., so that the contact stress on the gear tooth surface is 300MPa.

[0031] Step 3: Lubricate the gears in planetary reducer 4, planetary reducer 7, spur gearbox 3, and spur gearbox 6. The lubrication method can be selected from the alternative lubrication technologies and their matching schemes that need to be compared and evaluated. The same or different lubrication schemes can be selected for the four gear transmission pairs, such as solid lubrication, grease lubrication, solid-liquid composite lubrication, etc.

[0032] Step four, according to Figure 1 Connect all components, adjust the torsion spring loader 8 so that the torque sensor 5 reads 15 Nm, and lock all couplings 9.

[0033] Step 5: Turn on drive motor 2 and adjust its output speed to 300 rpm to complete the debugging of the test device.

[0034] Step 6: Place the test device into vacuum chamber 1, evacuate vacuum chamber 1 and control the temperature inside the vacuum chamber to the test temperature as required. After the device temperature stabilizes, turn on drive motor 2 to conduct the test.

[0035] Step 7: Stop the test when the test time reaches the required gear meshing life of the space mechanism, open the vacuum tank 1, take out the test device, disassemble the spur gearbox 3, spur gearbox 6, planetary reducer 4 and planetary reducer 7, compare and evaluate the advantages and disadvantages of the lubrication schemes, and select the optimal lubrication scheme as the lubrication method for the planetary reducer and spur gear transmission pair in the space mechanism.

[0036] The principle of the aforementioned evaluation device and test method for lubrication technology of gear components in space mechanisms is as follows: Based on the actual needs of the space mechanism, the input speed and output torque of planetary reducer 4, the contact stress of the spur gear transmission pair, and the contact stress between each gear pair in the planetary gear are obtained. Based on these parameters, the transmission ratio and meshing tooth width of spur gearbox 3, spur gearbox 6, and planetary reducer 7 under equivalent contact stress can be designed and calculated, and the torque load applied by the torsion spring loader 8 can be calculated. Therefore, using the above evaluation device can ensure that the contact stress of each tested component is consistent with the actual requirements, and typical transmission pair tests can be carried out under equivalent contact stress. Vacuum environment tests of two sets of spur gears and two sets of planetary gears can be carried out simultaneously for the optimization of lubrication schemes and life tests of these typical transmission components, thereby shortening the test time and reducing the test cost.

[0037] Obviously, those skilled in the art can make various modifications and variations to the embodiments of the present invention without departing from the spirit and scope of the invention. Therefore, if these modifications and variations fall within the scope of the claims of the present invention and their equivalents, the present invention also intends to include these modifications and variations.

[0038] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A device for evaluating lubrication technology of a space mechanism gear-like component, characterized by, The evaluation device adopts a power closed layout, comprising a vacuum tank and a test device; The test device is installed in the vacuum tank and is used for simulating transmission component test of a space mechanism in a vacuum and high and low temperature alternating environment; The test device comprises a driving motor, a spur gear box one, a planetary reducer one, a torque sensor, a spur gear box two, a planetary reducer two and a torsional spring loader; The driving motor is in transmission connection with an input end of the spur gear box one; the spur gear box one, the planetary reducer one, the torque sensor, the spur gear box two, the planetary reducer two, the torsional spring loader and the spur gear box one are sequentially in transmission connection, forming a transmission closed loop; The torsional spring loader is used for setting a loading torque, so as to realize torque loading of the planetary reducer one, the spur gear box one, the spur gear box two and the planetary reducer two; The torque sensor is used for monitoring a loading torque and a rotating speed.

2. The evaluation device according to claim 1, characterized in that The driving motor, the spur gear box one, the planetary reducer one, the torque sensor, the spur gear box two, the planetary reducer two, the torsional spring loader and the spur gear box one are connected through shaft couplings.

3. The evaluation device according to claim 1, characterized in that The planetary reducer one, the spur gear box one, the spur gear box two and the planetary reducer two adopt different lubrication schemes.

4. The evaluation device according to any one of claims 1 to 3, characterized in that A harmonic reducer or an RV reducer is used to replace the planetary reducer one.

5. The evaluation device according to any one of claims 1 to 3, characterized in that According to a space mechanism, input rotating speed and output torque of the planetary reducer one, contact stress of spur gear transmission pairs in the spur gear box one and the spur gear box two and contact stress between gear pairs in the planetary reducer two are obtained, parameters of gear pairs in the spur gear box one, the spur gear box two and the planetary reducer two under equivalent contact stress are calculated, and torque load required by the torsional spring loader is calculated.

6. A test method using the evaluation apparatus for lubrication technology of space mechanism gear-like components according to any one of claims 1 to 5, characterized by, The method comprises the following steps: In step one, the spur gear box one, the spur gear box two and the planetary reducer two are used as speed increasers, transmission ratios are designed, the same planetary reducer one as the space mechanism is selected, output rotating speed of the motor is the same as rotating speed after speed change through the planetary reducer one, the spur gear box two, the planetary reducer two and the spur gear box one, and a closed loop is formed; In step two, meshing parameters of gears in the spur gear box one and the spur gear box two are designed, so that gear tooth surface contact stress reaches a predetermined contact stress; In step three, gears in the planetary reducer one, the planetary reducer two, the spur gear box one and the spur gear box two are lubricated; In step four, the test device is formed by connecting the driving motor, the spur gear box one, the planetary reducer one, the torque sensor, the spur gear box two, the planetary reducer two and the torsional spring loader through shaft couplings, the torsional spring loader is adjusted so that the torque sensor shows a predetermined value, and the shaft couplings are locked; In step five, the driving motor is started, and output rotating speed thereof is adjusted to a predetermined rotating speed, so that debugging is completed; In step six, the test device is placed in the vacuum tank, the vacuum tank is vacuumized to form a vacuum chamber inside, temperature in the vacuum chamber is controlled to a test temperature, the driving motor is started after temperature is stable, and test is performed. Step seven, stop the test after reaching the required gear meshing life of the space mechanism, open the vacuum tank, take out the test device, disassemble the spur gear box one, spur gear box two, planetary reducer one and planetary reducer two, and compare and evaluate the pros and cons of the lubrication scheme to select the optimal lubrication scheme for the lubrication of the gear transmission pair in the space mechanism.

7. The test method of claim 6, wherein, In step three, the lubrication treatment mode of the gears in the planetary reducer one, the planetary reducer two, the spur gear box one and the spur gear box two can be selected from the alternative lubrication technologies and their compatible schemes that need to be compared and evaluated.

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