Heat source isolation and automatic temperature control system based on multi-satellite parallel thermal vacuum test
A technology of thermal vacuum test and heat source, applied in the field of thermal vacuum test of medium and large satellites, can solve the problems of multi-satellite heat sources interfering with synchronous temperature control, affecting the effectiveness and test cycle of multi-satellite experiments, and reducing the workload of test personnel and reducing the test period. The effect of cost reduction and test heating time reduction
Active Publication Date: 2020-09-29
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 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 cabin, a one-to-one correspondence between the isothermal area and the corresponding infrared lamp array and infrared cage heating device number is established as the heat flow device outside the area. The corresponding light numbers according to each isothermal area are shown in Table 1.
[0048]
[0049] S2. Start the temperature control and current limit test according to 90% of the test temperature of each isothermal area and 120% of the lamp current limit corresponding to each isothermal area; after 2-3h, enter S...
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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, and belongs to the field of medium and large satellite thermal vacuum tests. The system comprises a container, a sliding rail, a multi-satellite supporting structure, a horizontal adjusting structure, a first satellite support, a second satellite support, a first satellite, a second satellite, a low-temperature heat insulation device, a first lamp array and a second lamp array. A slide rail is horizontally arranged at a bottom of the container; a horizontal adjusting structure is in sliding fit with the sliding rail; the multi-satellite supporting structure is arranged on an upper surface of the horizontal adjusting structure; the first satellite support and the second satellite support are installed on the upper surface of the multi-satellite supporting structure; a low-temperature heat insulation device is arranged between the two satellite supports; the first satellite is mounted on the first satellite support; the second satellite is mounted on the second satellite support; the first lamp array is arranged above the first satellite;and the second lamp array is arranged above the second satellite. In the invention, the multi-satellite parallel thermal vacuum test of batch satellites is realized, a satellite development period isshortened, and development test cost is reduced.
Description
Technical field [0001] The invention belongs to the field of thermal vacuum test of medium and large satellites, and relates to a heat source isolation and automatic temperature control system based on a multi-satellite parallel thermal vacuum test. Background technique [0002] The document "GJB1027A-2005 Carrier, Upper Stage and Spacecraft Test Requirements" requires that the spacecraft must complete the thermal vacuum test of the whole device before it leaves the factory to verify the function and performance of the spacecraft under the specified pressure and temperature cyclic stress. , Exposing potential defects in the quality, workmanship and materials 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, AIT development will be carried out in a multi-satellite parallel development method to achieve rapid networking and launch of th...
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Login to View More 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