CN113125333B - High-low temperature box for spacecraft structure stability test - Google Patents
High-low temperature box for spacecraft structure stability test Download PDFInfo
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- CN113125333B CN113125333B CN202110405883.4A CN202110405883A CN113125333B CN 113125333 B CN113125333 B CN 113125333B CN 202110405883 A CN202110405883 A CN 202110405883A CN 113125333 B CN113125333 B CN 113125333B
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Abstract
The application provides a high-low temperature box for a spacecraft structure stability test, which comprises a box body and a temperature control host arranged outside the box body; the box body comprises a temperature control cabin and observation cabins connected to two ends of the temperature control cabin; a temperature control plate is arranged in the temperature control cabin; the temperature control plate is connected with the temperature control host through a temperature control medium pipeline and is used for adjusting the temperature in the temperature control cabin; and a transparent observation window is arranged on the observation cabin. The device has a simple structure and is convenient to operate, and the high-temperature and low-temperature pose of the detected product in the box body can be monitored by arranging the transparent observation window on the observation cabin and placing pose monitoring equipment outside the box body when in use; the length of the test box body can be adjusted by connecting different numbers of lengthened cabins between the observation cabin and the temperature control cabin, so that the test box body can accommodate tested products with different length sizes.
Description
Technical Field
The application relates to the technical field of spacecraft specialized testing, in particular to a high-low temperature box for a spacecraft structural stability test.
Background
The temperature of the side of the spacecraft, which faces the sun, is up to 180 ℃ when the spacecraft is in orbit running in a complex environment with alternating cold and hot, and the temperature of the side, which faces away from the sun, is 180 ℃ below zero. When developing a spacecraft on the ground, a high-low temperature environment needs to be simulated to verify whether the structure of the spacecraft is deformed.
At present, the conventional method is to heat the spacecraft locally by a heating plate under the normal pressure condition of a laboratory, heat different positions to a certain temperature according to different test matrixes, and monitor the deformation of the structure by adopting pose monitoring equipment in the heating or cooling process, which is shown in digital photogrammetry of normal pressure thermal deformation of a satellite structural member (optical precision engineering, 2012,20 (12)), but cannot monitor the deformation at low temperature under normal pressure. Another common method is to place the spacecraft to be tested in a large low-temperature vacuum container, the vacuum container can reach-180 ℃ at low temperature, and the designated parts on the spacecraft can be subjected to heat radiation and temperature rise according to the requirement, and the high temperature can reach 180 ℃. Meanwhile, the pose monitoring equipment is packaged into a protective tank with a glass window, the monitoring equipment and the protective tank are placed into a low-temperature vacuum container together to monitor the structural deformation of the spacecraft, the satellite antenna deformation photogrammetry technology (optical technology, 201339 (4)) under the vacuum low-temperature environment is known, and the method is complex and is not easy to operate the pose monitoring equipment.
Disclosure of Invention
The purpose of the application is to provide a high-low temperature box for spacecraft structure stability test aiming at the problems.
The application provides a high-low temperature box for a spacecraft structure stability test, which comprises a box body and a temperature control host arranged outside the box body; the box body comprises a temperature control cabin and observation cabins connected to two ends of the temperature control cabin; a temperature control plate is arranged in the temperature control cabin; the temperature control plate is connected with the temperature control host through a temperature control medium pipeline and is used for adjusting the temperature in the temperature control cabin; and a transparent observation window is arranged on the observation cabin.
According to the technical scheme provided by certain embodiments of the application, at least one lengthened cabin is detachably connected between the observation cabin and the temperature control cabin.
According to the technical scheme provided by certain embodiments of the application, the observation cabin is connected with the lengthened cabin and the lengthened cabin is connected with the temperature control cabin through flanges.
According to the technical scheme provided by certain embodiments of the application, the flange is provided with a sealing rubber ring.
According to the technical scheme provided by certain embodiments of the application, the temperature control plate is connected with a plurality of metal wires; the free end of the metal wire is provided with a heat conduction patch.
According to the technical scheme provided by certain embodiments of the application, a temperature sensor is further arranged in the temperature control cabin; the temperature sensor is connected with a temperature monitoring device positioned outside the box body and used for monitoring the temperature in the temperature control cabin; the temperature monitoring device is connected with the temperature control host.
According to the technical scheme provided by certain embodiments of the application, a vacuum pump is further arranged outside the box body; the vacuum pump is communicated with the temperature control cabin through a pipeline.
Compared with the prior art, the beneficial effect of this application: the high-low temperature box for the spacecraft structure stability test is simple in structure and convenient to operate, when the high-low temperature box is used, a spacecraft product to be tested is placed in the box body of the high-low temperature box, and the temperature control host outside the box body is used for controlling the temperature control board inside the box body to be heated or cooled, so that the high-low temperature control of the product to be tested can be realized; the transparent observation window is arranged on the observation cabin, so that the pose monitoring equipment is placed outside the box body when in use, and the high-temperature pose and the low-temperature pose of the tested product in the box body can be monitored through the transparent observation window; the length of the test box body can be adjusted by connecting different numbers of lengthened cabins between the observation cabin and the temperature control cabin, so that the test box body can accommodate tested products with different length sizes.
Drawings
Fig. 1 is a schematic structural diagram of a high-low temperature box for a spacecraft structural stability test according to an embodiment of the present disclosure;
fig. 2 is a schematic diagram of an internal structure of a high-low temperature box for a spacecraft structure stability test according to an embodiment of the present application.
The text labels in the figures are expressed as:
1. a temperature control cabin; 2. lengthening the cabin; 3. an observation cabin; 4. a temperature control host; 5. a temperature monitoring device; 6. a vacuum pump; 7. a temperature control plate; 8. a temperature sensor; 9. a transparent viewing window; 10. a flange; 11. a thermally conductive patch; 12. the product to be tested.
Detailed Description
In order that those skilled in the art may better understand the technical solutions of the present application, the following detailed description of the present application is provided by way of example and illustration only, and should not be construed to limit the scope of the present application in any way.
Referring to fig. 1 and 2, the embodiment provides a high-low temperature box for a spacecraft structure stability test, which comprises a box body, wherein the box body can be designed into different shapes such as a cuboid or a cylinder according to the requirement of a tested product; a temperature control host 4 is arranged outside the box body; the box body comprises a temperature control cabin 1 and observation cabins 3 which are detachably connected to two ends of the temperature control cabin 1; a temperature control plate 7 is arranged in the temperature control cabin 1; the temperature control plate 7 is connected with a plurality of metal wires; the free end of the metal wire is provided with a heat conduction patch 11; the heat conducting patch 11 is used for being attached to a tested product 12; the temperature control plate 7 is connected with the temperature control host 4 through a temperature control medium pipeline and is used for adjusting the temperature in the temperature control cabin 1; a transparent observation window 9 is arranged on the observation cabin 3 for observation by pose monitoring equipment; three transparent observation windows 9 are arranged on each observation cabin 3, and the three transparent observation windows 9 are distributed at the end part of the observation cabin 3 and at the upper side and the lower side.
When in use, the heat conducting patch 11 is stuck on the tested product 12, and according to the test requirement, the temperature control host 4 refrigerates or heats the temperature control plate 7 through a temperature control medium in a temperature control medium pipeline, and refrigerates or heats the tested product 12 through a metal wire and the heat conducting patch 11; the high-temperature and low-temperature pose of the detected product 12 in the box body is monitored by placing pose monitoring equipment outside the box body and through the transparent observation window 9.
Furthermore, a plurality of temperature sensors 8 are also arranged in the temperature control cabin 1; the temperature sensor 8 is connected with the temperature monitoring device 5 positioned outside the box body through a cabin penetrating cable and is used for monitoring the temperature in the temperature control cabin 1 in real time; the temperature monitoring device 5 is connected with the temperature control host 4.
When in use, the temperature sensor 8 is stuck on the tested product 12, and the temperature sensor 8 sends a detected temperature signal to the temperature monitoring device 5; the temperature monitoring device 5 sends the temperature signal to the temperature control host 4, and besides, the temperature control host 4 receives the measured temperature, the temperature control host 4 is provided with a test temperature according to test conditions, and the temperature control host 4 controls the flow and speed of the temperature control medium according to the difference between the measured temperature and the test temperature, so that the temperature in the box body is regulated, and the temperature required by the test is met.
Further, a vacuum pump 6 is arranged outside the box body; the vacuum pump 6 is communicated with the temperature control cabin 1 through a pipeline, the vacuum pump 9 is used for vacuumizing the inside of the box body during a test, and after vacuumizing the inside of the box body, frosting of a tested product 12 or the inside of the box body in a refrigerating process can be prevented.
Further, at least one lengthened cabin 2 is detachably connected between the observation cabin 3 and the temperature control cabin 1, and the lengthened cabin 2 is used for increasing the length of the box body of the test box, so that the box body can accommodate tested products with different length sizes, and when in use, whether the lengthened cabin 2 is additionally arranged or not and the number of the lengthened cabins 2 are additionally arranged can be selected according to the sizes of the tested products.
Further, the observation cabin 3 is connected with the lengthened cabin 2 and the lengthened cabin 2 is connected with the temperature control cabin 1 through a flange 10; the flange 10 is arranged to facilitate the disassembly and assembly of the observation cabin 3, the lengthening cabin 2 and the temperature control cabin 1, and simultaneously facilitate the placement and removal of the tested products.
Further, the flange 10 is provided with a sealing rubber ring, so that the box body has good sealing performance.
The method for carrying out structural stability test on the spacecraft product by adopting the high-low temperature box comprises the following steps:
1) On-line inspection: checking whether the connection of the cabin penetrating cable and the temperature control medium pipeline is normal, if so, performing the next step, and if not, performing debugging until normal.
2) Placing a tested product: the product to be measured is placed in a temperature control cabin of the box body, the heat conduction patch and the temperature sensor are adhered to the appointed position on the product to be measured, and the lengthened cabin (if needed) and the observation cabin are sequentially connected through flanges.
3) Vacuumizing: the vacuum pump is started to evacuate the interior of the tank.
4) And (3) temperature adjustment: according to the test requirement, the temperature control host is started, and the temperature control host can automatically control the high temperature and the low temperature according to the test temperature value and the measured temperature of the temperature sensor until the temperature required by the test is met.
5) Monitoring a tested product: the pose detection equipment is placed outside the box body, and the micro deformation of the detected product is monitored in real time through a transparent observation window on an observation cabin of the box body.
6) The box body is restored to the normal temperature and normal pressure state: after the test is finished, the temperature value of the temperature control host is set to be close to the room temperature, and the temperature control host adjusts the temperature in the box body until the temperature returns to the room temperature; the vacuum pump is used for repressing the inside of the box body, so that the atmospheric pressure inside and outside the box body is the same.
7) Taking out the tested product: and (5) detaching the observation cabin and taking out the tested product.
The high-low temperature box for the spacecraft structure stability test is simple in structure and convenient to operate, when the high-low temperature box is used, a spacecraft product to be tested is placed in the box body of the high-low temperature box, and the temperature control host outside the box body is used for controlling the temperature control board inside the box body to be heated or cooled, so that the high-low temperature control of the spacecraft product to be tested is realized; the transparent observation window is arranged on the observation cabin, so that the pose monitoring equipment is placed outside the box body when in use, and the high-temperature pose and the low-temperature pose of the tested product in the box body can be monitored through the transparent observation window; the length of the test box body can be adjusted by connecting different numbers of lengthened cabins between the observation cabin and the temperature control cabin, so that the test box body can accommodate tested products with different length sizes.
Specific examples are set forth herein to illustrate the principles and embodiments of the present application, and the description of the examples above is only intended to assist in understanding the methods of the present application and their core ideas. The foregoing is merely a preferred embodiment of the present application, and it should be noted that, due to the limited nature of text, there is an objectively infinite number of specific structures, and that, to those skilled in the art, several improvements, modifications or changes can be made, and the above technical features can be combined in a suitable manner, without departing from the principles of the present invention; such modifications, variations and combinations, or the direct application of the concepts and aspects of the invention in other applications without modification, are intended to be within the scope of this application.
Claims (4)
1. The high-low temperature box for the spacecraft structure stability test is characterized by comprising a box body and a temperature control host (4) arranged outside the box body; the box body comprises a temperature control cabin (1) and observation cabins (3) connected to two ends of the temperature control cabin (1); a temperature control plate (7) is arranged in the temperature control cabin (1); the temperature control plate (7) is connected with the temperature control host (4) through a temperature control medium pipeline and is used for adjusting the temperature in the temperature control cabin (1); a plurality of metal wires are connected to the temperature control plate (7); the free end of the metal wire is provided with a heat conduction patch (11); the temperature control host (4) is used for refrigerating or heating the temperature control board (7) through a temperature control medium in the temperature control medium pipeline, and refrigerating or heating the tested product (12) through the metal wire and the heat conduction patch (11); a transparent observation window (9) is arranged on the observation cabin (3) for observation by pose monitoring equipment; at least one lengthening cabin (2) is detachably connected between the observation cabin (3) and the temperature control cabin (1); the observation cabin (3) is connected with the lengthened cabin (2) and the lengthened cabin (2) is connected with the temperature control cabin (1) through a flange (10).
2. The high-low temperature box for spacecraft structural stability test according to claim 1, wherein a sealing rubber ring is arranged on the flange (10).
3. The high-low temperature box for the structural stability test of the spacecraft according to claim 1, wherein a temperature sensor (8) is further arranged in the temperature control cabin (1); the temperature sensor (8) is connected with a temperature monitoring device (5) positioned outside the box body and used for monitoring the temperature in the temperature control cabin (1); the temperature monitoring device (5) is connected with the temperature control host (4).
4. The high-low temperature box for spacecraft structural stability test according to claim 1, wherein the exterior of the box body is also provided with a vacuum pump (6); the vacuum pump (6) is communicated with the temperature control cabin (1) through a pipeline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110405883.4A CN113125333B (en) | 2021-04-15 | 2021-04-15 | High-low temperature box for spacecraft structure stability test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110405883.4A CN113125333B (en) | 2021-04-15 | 2021-04-15 | High-low temperature box for spacecraft structure stability test |
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| Publication Number | Publication Date |
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| CN113125333A CN113125333A (en) | 2021-07-16 |
| CN113125333B true CN113125333B (en) | 2023-06-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110405883.4A Active CN113125333B (en) | 2021-04-15 | 2021-04-15 | High-low temperature box for spacecraft structure stability test |
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Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203414861U (en) * | 2013-09-04 | 2014-01-29 | 西南交通大学 | High and low temperature test environment control device used for geotechnical model tests |
| CN105928467B (en) * | 2016-06-01 | 2019-09-10 | 北京卫星环境工程研究所 | Large Spacecraft malformation measures pilot system under vacuum low-temperature environment |
| CN106644801A (en) * | 2016-12-30 | 2017-05-10 | 中国电子科技集团公司第十八研究所 | Dual-working-condition high-low temperature impact testing equipment for aerospace solar cell |
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