CN114229051B - Thermal vacuum test device for knob function assessment of space station cabin external electric tool - Google Patents
Thermal vacuum test device for knob function assessment of space station cabin external electric tool Download PDFInfo
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- CN114229051B CN114229051B CN202210085588.XA CN202210085588A CN114229051B CN 114229051 B CN114229051 B CN 114229051B CN 202210085588 A CN202210085588 A CN 202210085588A CN 114229051 B CN114229051 B CN 114229051B
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- electric tool
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
- B64G2007/005—Space simulation vacuum chambers
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- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The application discloses a thermal vacuum test device for knob function assessment of an electric tool outside a space station cabin, which comprises a test piece, an execution system and a support system; the actuating system consists of a motor, a moment sensor and an actuating mechanism, wherein the actuating mechanism is connected with the moment sensor through a first diaphragm coupler. According to the application, through the design of the motor, the torque sensor and the actuating mechanism, the operation process of an astronaut is effectively simulated, the vacuum grease lubrication motor and the sensor are used, the device can operate in a vacuum environment, the gland is connected with the transmission shaft by adopting a universal joint, the torsion process of the astronaut can be simulated to the maximum extent, the design of the plectrum behind the gland and the design of the micro-switch signal feedback can effectively convert in-place signals into electric signals and output the electric signals to the motor, and the overoperation is effectively avoided.
Description
Technical Field
The application relates to the technical field of spacecraft thermal vacuum tests, in particular to a thermal vacuum test device for knob function assessment of an external electric tool of a space station cabin.
Background
The space station cabin outer tool is one of the most important maintenance tools used for the maintenance activities of spacecrafts, and is mainly used for screwing and unscrewing fixing screws of equipment when the spacecrafts disassemble and assemble the equipment outside the cabin. The rear end of the out-cabin electric tool is provided with a switch knob. When an astronaut needs to use the off-cabin electric tool, the switch knob is required to be turned to the right 60 degrees to the on gear, so that the off-cabin electric tool is in a starting state; when the device is used, the switch knob is required to be left-rotated for 60 degrees to an off gear, so that the off-cabin electric tool is in a shutdown state. In order to ensure the accuracy of the rotation operation of the astronaut and the working reliability of the off-board electric tool, the actual vacuum thermal environment on the ground is required to be simulated, and the switch knob of the off-board electric tool can be verified to work normally in the vacuum thermal environment and meet the service life of 15 years on the track.
The temperature of the outdoor electric tool can be between minus 60 ℃ and plus 60 ℃ when the astronaut is in a vacuum environment during on-orbit operation, and how to simulate the action of the real astronaut rotating the switch knob in the space environment simulation room, so as to verify the reliability of the outdoor electric tool switch knob, and the problem which needs to be solved in the ground thermal vacuum test is solved.
Disclosure of Invention
The application aims at: in order to solve the problems, a thermal vacuum test device for checking the knob function of an external space station tool is provided.
In order to achieve the above purpose, the present application adopts the following technical scheme:
the thermal vacuum test device for knob function assessment of the space station cabin external electric tool comprises a test piece, an execution system and a support system;
the executing system consists of a motor, a moment sensor and an executing mechanism, wherein the executing mechanism is connected with the moment sensor through a first diaphragm coupler, and the moment sensor is connected with the motor through a second diaphragm coupler;
the support system comprises a test piece support, a micro switch support, an upper shaft sleeve, a lower shaft sleeve, a shaft support, a sensor support, a motor support and a rear support, and is used for fixing the test piece and the component parts of the execution system.
Preferably, the actuating mechanism comprises a gland, a universal joint, a transmission shaft, a first micro-switch and a second micro-switch, wherein the gland is pressed on a switch knob of the electric tool outside the cabin through a shaping design, a mounting hole is formed above the gland and is connected with the transmission shaft through the universal joint, and the transmission shaft is connected with the torque sensor through a second diaphragm coupler.
Preferably, the rear end of the gland is provided with a moving plectrum.
Preferably, the motor and the torque sensor are both lubricated by vacuum grease.
Preferably, the test piece is fixed on the installation surface inside the space environment simulator through a test piece support, the first micro switch and the second micro switch are both fixed on the installation surface inside the space environment simulator through micro switch supports, the transmission shaft is connected with the shaft support through an upper shaft sleeve and a lower shaft sleeve, the shaft support is fixed on the installation surface inside the space environment simulator, the torque sensor and the motor are respectively fixed on the rear support through a sensor support and a motor support, and the rear support is fixed on the installation surface inside the space environment simulator.
Preferably, a connecting rod design is adopted between the lower shaft sleeve and the shaft support, and the lower shaft sleeve and the shaft support are fixed through screws.
Preferably, the motor, the torque sensor, the first micro switch and the second micro switch are connected with an industrial personal computer outside the space environment simulator through cables.
In summary, due to the adoption of the technical scheme, the beneficial effects of the application are as follows:
according to the application, through the design of the motor, the torque sensor and the actuating mechanism, the operation process of an astronaut is effectively simulated, the vacuum grease lubrication motor and the sensor are used, the device can operate in a vacuum environment, the gland is connected with the transmission shaft by adopting a universal joint, the torsion process of the astronaut can be simulated to the maximum extent, the design of the plectrum behind the gland and the design of the micro-switch signal feedback can effectively convert in-place signals into electric signals and output the electric signals to the motor, and the overoperation is effectively avoided.
Drawings
Fig. 1 shows a schematic structural diagram of a thermal vacuum test device for knob function assessment of an electric tool outside a space station cabin according to an embodiment of the present application;
fig. 2 shows a schematic structural diagram of a test piece of the thermal vacuum test device provided according to an embodiment of the present application.
Legend description:
1. a test piece; 2. a gland; 3. a universal joint; 4. a transmission shaft; 5. a first diaphragm coupling; 6. a torque sensor; 7. a second diaphragm coupling; 8. a motor; 9. a moving plectrum; 10. a first microswitch; 11. a second microswitch; 12. a test piece holder; 13. a microswitch bracket; 14. an upper shaft sleeve; 15. a lower shaft sleeve; 16. a shaft support; 17. a sensor holder; 18. a motor bracket; 19. and a rear support.
Detailed Description
The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
Referring to fig. 1-2, the present application provides a technical solution:
the thermal vacuum test device for the knob function assessment of the space station cabin external electric tool comprises a test piece 1, an execution system and a support system, wherein the test piece 1 and the execution system are fixed in a space environment simulator through the support system, and the action of a spacecraft rotary cabin external electric tool switch knob is simulated under the thermal vacuum thermal environment and is used for assessing the functional performance and the service life of the switch knob;
the executing system consists of a motor 8, a torque sensor 6 and an executing mechanism, wherein the motor 8 can output torque as power of a rotary switch to simulate the operation of an astronaut; the torque sensor 6 can measure the torque of the rotary switch knob and monitor whether the knob is jammed; the actuating mechanism can simulate the action of a rotating switch knob of an astronaut, the actuating mechanism is connected with the moment sensor 6 through the first diaphragm coupler 5, and the moment sensor 6 is connected with the motor 8 through the second diaphragm coupler 7;
the support system comprises a test piece support 12, a microswitch support 13, an upper shaft sleeve 14, a lower shaft sleeve 15, a shaft support 16, a sensor support 17, a motor support 18 and a rear support 19, and is used for fixing the test piece 1 and the component parts of the execution system.
Specifically, as shown in fig. 1 and 2, the actuating mechanism comprises a gland 2, a universal joint 3, a transmission shaft 4, a first micro-switch 10 and a second micro-switch 11, wherein the gland 2 is pressed on a switch knob of an off-cabin electric tool through a shaping design, a mounting hole is designed above the gland 2 and is connected with the transmission shaft 4 through the universal joint 3, the transmission shaft 4 is connected with the moment sensor 6 through a second diaphragm coupler 7, and the universal joint 3 is adopted between the gland 2 and the transmission shaft 4, so that the on-orbit actual operation process of an astronaut can be simulated to the greatest extent, and meanwhile, the requirement on the mounting precision is reduced.
Specifically, as shown in fig. 1, the rear end of the gland 2 is provided with a moving plectrum 9, and when the switch knob rotates left and right, the moving plectrum 9 is driven to swing left and right; in the initial state, the switch knob is in an off gear, and the movable pulling sheet 9 presses the first micro switch 10; when the left hand gear rotates 60 degrees to the right hand gear, the moving poking plate 9 presses the second micro switch 11, in-place signals can be effectively converted into electric signals to be output to the motor 8, and overoperation is effectively avoided.
Specifically, as shown in fig. 1, the motor 8 and the torque sensor 6 are lubricated by vacuum grease, and can be used in a vacuum environment.
Specifically, as shown in fig. 1, the test piece 1 is fixed on the installation surface inside the space environment simulator through the test piece bracket 12, the first micro switch 10 and the second micro switch 11 are both fixed on the installation surface inside the space environment simulator through the micro switch bracket 13, the transmission shaft 4 is connected with the shaft support 16 through the upper shaft sleeve 14 and the lower shaft sleeve 15, the shaft support 16 is fixed on the installation surface inside the space environment simulator, the torque sensor 6 and the motor 8 are respectively fixed on the rear support 19 through the sensor bracket 17 and the motor bracket 18, and the rear support 19 is fixed on the installation surface inside the space environment simulator.
Specifically, as shown in fig. 1, a connecting rod design is adopted between the lower shaft sleeve 15 and the shaft support 16, and the connecting rod is fixed through screws, so that the requirement on installation precision is reduced, and the assembly is convenient.
Specifically, as shown in fig. 1, the motor 8, the torque sensor 6, the first micro switch 10 and the second micro switch 11 are connected with an industrial personal computer outside the space environment simulator through cables, so that automatic control is realized during test.
In summary, in the thermal vacuum test device for checking the knob function of the electric tool outside the cabin of the space station provided by the embodiment, during the thermal vacuum test, the device shown in fig. 1 is installed in the space environment simulator, the vacuum is pumped, after the temperature of the test piece 1 is controlled to be +60 ℃, the motor 8 is rotated to the right, the driving shaft 4 is used for driving the gland 2 to drive the switch knob of the electric tool outside the cabin to rotate to the right, so that the switch knob reaches the "on" level, and at this time, the movement pulling sheet 9 behind the gland 2 is rotated to the left to press the second micro switch 11, and a signal is fed back to the motor 8; after receiving the moving position signal of the second micro switch 11, the motor 8 starts to turn left, and the motor 8 is brought to the gland 2 through the transmission shaft 4, so that the switch knob of the out-of-cabin electric tool is driven to turn right, and the switch knob is enabled to reach the 'off' gear, at the moment, the moving pulling piece 9 behind the gland 2 turns right, the first micro switch 10 is pressed, the in-place signal is fed back to the motor 8, and after receiving the signal, the motor 8 turns left; thus, a complete switching operation is completed.
The previous description of the embodiments is provided to enable any person skilled in the art to make or use the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (4)
1. The thermal vacuum test device for knob function assessment of the space station cabin external electric tool is characterized by comprising a test piece (1), an execution system and a support system;
the executing system consists of a motor (8), a moment sensor (6) and an executing mechanism, wherein the executing mechanism is connected with the moment sensor (6) through a first diaphragm coupler (5), and the moment sensor (6) is connected with the motor (8) through a second diaphragm coupler (7);
the support system comprises a test piece support (12), a micro-switch support (13), an upper shaft sleeve (14), a lower shaft sleeve (15), a shaft support (16), a sensor support (17), a motor support (18) and a rear support (19) and is used for fixing the test piece (1) and the component parts of the execution system;
the actuating mechanism consists of a gland (2), a universal joint (3), a transmission shaft (4), a first micro switch (10) and a second micro switch (11), wherein the gland (2) is pressed on a switch knob of an off-cabin electric tool through a shaping design, a mounting hole is formed above the gland (2) and is connected with the transmission shaft (4) through the universal joint (3), and the transmission shaft (4) is connected with a moment sensor (6) through a second diaphragm coupler (7);
the rear end of the gland (2) is provided with a moving plectrum (9);
the test piece (1) is fixed on the installation surface inside the space environment simulator through a test piece support (12), the first micro switch (10) and the second micro switch (11) are both fixed on the installation surface inside the space environment simulator through a micro switch support (13), the transmission shaft (4) is connected with the shaft support (16) through an upper shaft sleeve (14) and a lower shaft sleeve (15), the shaft support (16) is fixed on the installation surface inside the space environment simulator, the torque sensor (6) and the motor (8) are respectively fixed on the rear support (19) through a sensor support (17) and a motor support (18), and the rear support (19) is fixed on the installation surface inside the space environment simulator.
2. The thermal vacuum test device for knob function assessment of a space station external electric tool according to claim 1, wherein the motor (8) and the torque sensor (6) are both lubricated with vacuum grease.
3. The thermal vacuum test device for knob function assessment of space station external electric tool according to claim 1, wherein a connecting rod design is adopted between the lower shaft sleeve (15) and the shaft support (16), and the lower shaft sleeve is fixed through screws.
4. The thermal vacuum test device for knob function assessment of an external space station tool according to claim 1, wherein the motor (8), the torque sensor (6), the first micro switch (10) and the second micro switch (11) are connected with an industrial personal computer outside the space environment simulator through cables.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210085588.XA CN114229051B (en) | 2022-01-25 | 2022-01-25 | Thermal vacuum test device for knob function assessment of space station cabin external electric tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210085588.XA CN114229051B (en) | 2022-01-25 | 2022-01-25 | Thermal vacuum test device for knob function assessment of space station cabin external electric tool |
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| CN114229051A CN114229051A (en) | 2022-03-25 |
| CN114229051B true CN114229051B (en) | 2023-08-15 |
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| CN202210085588.XA Active CN114229051B (en) | 2022-01-25 | 2022-01-25 | Thermal vacuum test device for knob function assessment of space station cabin external electric tool |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101271036A (en) * | 2007-03-20 | 2008-09-24 | 中国航天科技集团公司第五研究院第五一○研究所 | Sun wing hinge moment testing device |
| CN104360267A (en) * | 2014-10-17 | 2015-02-18 | 北京航天益森风洞工程技术有限公司 | Device for measuring load characteristic of motor under vacuum environment |
| US9228917B1 (en) * | 2009-04-17 | 2016-01-05 | Arrowhead Center, Inc. | Six degrees of freedom free-motion test apparatus |
| CN208399141U (en) * | 2018-06-27 | 2019-01-18 | 上海迪由控制***有限公司 | Knob selector multi-function test stand |
| CN113390622A (en) * | 2021-07-19 | 2021-09-14 | 上汽通用五菱汽车股份有限公司 | Electrodynamic type vehicle air conditioner knob endurance test detection device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012009198A2 (en) * | 2010-07-14 | 2012-01-19 | University Of Florida Research Foundation, Inc. | System and method for assessing the performance of an attitude control system for small satellites |
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2022
- 2022-01-25 CN CN202210085588.XA patent/CN114229051B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101271036A (en) * | 2007-03-20 | 2008-09-24 | 中国航天科技集团公司第五研究院第五一○研究所 | Sun wing hinge moment testing device |
| US9228917B1 (en) * | 2009-04-17 | 2016-01-05 | Arrowhead Center, Inc. | Six degrees of freedom free-motion test apparatus |
| CN104360267A (en) * | 2014-10-17 | 2015-02-18 | 北京航天益森风洞工程技术有限公司 | Device for measuring load characteristic of motor under vacuum environment |
| CN208399141U (en) * | 2018-06-27 | 2019-01-18 | 上海迪由控制***有限公司 | Knob selector multi-function test stand |
| CN113390622A (en) * | 2021-07-19 | 2021-09-14 | 上汽通用五菱汽车股份有限公司 | Electrodynamic type vehicle air conditioner knob endurance test detection device |
Non-Patent Citations (1)
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| 何传大.载人航天的热真空试验.中国空间科学技术.1991,(04),全文. * |
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| CN114229051A (en) | 2022-03-25 |
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