ZHENG Mao-fan, JIANG Hao-cheng, ZHANG Tian-ping, et al. TEST AND ANALYSIS OF THE THERMAL CHARACTERISTIC FOR ION THRUSTER[J]. VACUUM AND CRYOGENICS, 2011, 17(2): 96-100. DOI: 10.3969/j.issn.1006-7086.2011.02.001
Citation:
ZHENG Mao-fan, JIANG Hao-cheng, ZHANG Tian-ping, et al. TEST AND ANALYSIS OF THE THERMAL CHARACTERISTIC FOR ION THRUSTER[J]. VACUUM AND CRYOGENICS, 2011, 17(2): 96-100. DOI: 10.3969/j.issn.1006-7086.2011.02.001
ZHENG Mao-fan, JIANG Hao-cheng, ZHANG Tian-ping, et al. TEST AND ANALYSIS OF THE THERMAL CHARACTERISTIC FOR ION THRUSTER[J]. VACUUM AND CRYOGENICS, 2011, 17(2): 96-100. DOI: 10.3969/j.issn.1006-7086.2011.02.001
Citation:
ZHENG Mao-fan, JIANG Hao-cheng, ZHANG Tian-ping, et al. TEST AND ANALYSIS OF THE THERMAL CHARACTERISTIC FOR ION THRUSTER[J]. VACUUM AND CRYOGENICS, 2011, 17(2): 96-100. DOI: 10.3969/j.issn.1006-7086.2011.02.001
TEST AND ANALYSIS OF THE THERMAL CHARACTERISTIC FOR ION THRUSTER
The thermal characteristic was tested and analyzed for the operating ion thruster.The result indicating: Heat was mostly transferred to ambience through conduction and radiation in the operating ion thruster.Less heat was transferred to spacecraft by fix flange,so it did not influence spacecraft.Radiant heat was mostly transferred to space,and did not influence spacecraft too.
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