Heat source isolation and automatic temperature control system based on multi-satellite parallel thermal vacuum test
A thermal vacuum test and heat source technology, applied in the field of medium and large satellite thermal vacuum tests, can solve problems affecting the effectiveness of multi-satellite tests, test cycle, multi-satellite heat source interference and synchronous temperature control, etc., to reduce test costs and shorten development cycles , the effect of workload reduction
Active Publication Date: 2022-03-04
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology
[0005] In view of the high power, high heat consumption, and multi-working conditions of mass-produced satellites to carry out multi-satellite parallel thermal vacuum tests, there is currently no relevant technical solution to solve technical problems such as multi-satellite heat source interference and synchronous temperature control in multi-satellite parallel tests, which affect To multi-star test effectiveness, test cycle, etc.
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[0046] S1, such as image 3 As shown, the roof of a batch of satellites is divided into various isothermal regions;
[0047] In the satellite thermal vacuum test, the lamp array is used as the external heat flow simulation device. The infrared lamp array can control the current of each lamp, and the lamp array can control the current of each heating zone, thereby realizing the control of the external heat flow of the satellite. According to each isothermal area divided by the deck, establish a one-to-one correspondence relationship between the isothermal area and the corresponding numbers of heating devices such as infrared lamp arrays and infrared cages, as the heat flow device outside the area. Table 1 shows the lights corresponding to each isothermal area.
[0048]
[0049] S2. Start the control temperature and limit current test according to 90% of the test temperature in each isothermal area and 120% of the corresponding lamp current limit in each isothermal area; aft...
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The invention relates to a heat source isolation and automatic temperature control system based on a multi-satellite parallel thermal vacuum test, belonging to the field of medium and large satellite thermal vacuum tests; including a container, a slide rail, a multi-satellite support structure, a horizontal adjustment structure, a first satellite support, a second Satellite support, the first satellite, the second satellite, the low-temperature heat insulation device, the first light array and the second light array; the slide rail is horizontally arranged at the bottom of the container; the horizontal adjustment structure is slidingly matched with the slide rail; the multi-satellite support structure is arranged horizontally Adjust the upper surface of the structure; the first satellite bracket and the second satellite bracket are installed on the upper surface of the multi-satellite support structure; and a low-temperature heat insulation device is arranged between the two satellite brackets; the first satellite is installed on the first satellite bracket; The two satellites are installed on the second satellite bracket; the first lamp array is arranged above the first satellite; the second lamp array is arranged above the second satellite; the present invention realizes the multi-satellite parallel thermal vacuum test of mass-produced satellites, shortens The satellite development cycle is shortened, and the cost of development and testing is reduced.
Description
technical field [0001] The invention belongs to the field of thermal vacuum tests for medium and large satellites, and relates to a heat source isolation and automatic temperature control system based on multi-satellite parallel thermal vacuum tests. Background technique [0002] The document "GJB1027A-2005 Test Requirements for Vehicles, Upper Stages, and Spacecraft" requires that the spacecraft must complete the thermal vacuum test of the whole device before it leaves the factory to verify that the function and performance of the spacecraft meet the requirements under the specified pressure and temperature cycle stress. , to expose the potential quality, workmanship and material defects of the spacecraft. [0003] In the construction of space infrastructure such as low-orbit mobile communication satellite systems, navigation satellite systems, and earth observation satellite systems, multi-satellite parallel development methods will be used to carry out AIT development to ...
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IPC IPC(8): B64G7/00G05D23/32
CPCB64G7/00G05D23/32
Inventor 朱剑涛杜卓林张旭嵇景全王金刚郝文宇武向军柴智渊
Owner BEIJING INST OF SPACECRAFT SYST ENG