| Heat Transfer Between a Missile's Combustion Chamber and the Warhead |
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| 作者姓名： | 赵永涛 张奇 白春华 闫华 |
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| 作者单位： | State Key Laboratory of Explosion and Safety Science，Beijing Institute of Technology，State Key Laboratory of Explosion and Safety Science，Beijing Institute of Technology，State Key Laboratory of Explosion and Safety Science，Beijing Institute of Technology，State Key Laboratory of Explosion and Safety Science，Beijing Institute of Technology Beijing100081，China，Beijing100081，China，Beijing100081，China，Beijing100081，China |
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| 摘 要： | Thecombustionofpropellantacceleratesawar headduringtheprocessoflaunchingofthewarhead .Theheatcomingfromthecombustionnotonlypro pelsthewarheadbutitisalsotransferredtothechargewithinthewarhead.Tothepropellantcharge,spacebetweenthecombustionchamberandthewarheadneedstobewelldisposedininsulation ,andthedesignofheatinsulationstructureisveryim portantforsecurelaunching .Thusfarrelevantstud iesconcentratelargelyontheaspectsoftheouterspaceengine,andmostanalysesaregivenonthetem peraturedistributionofthe…
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| 收稿时间： | 2002/8/26 0:00:00 |
Heat Transfer Between a Missile's Combustion Chamber and the Warhead |
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| ZHAO Yong tao,ZHANG Qi,BAI Chun hua and YAN Hua.Heat Transfer Between a Missile''''s Combustion Chamber and the Warhead[J].Journal of Beijing Institute of Technology,2003,12(3):282-285. |
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| Authors: | ZHAO Yong tao ZHANG Qi BAI Chun hua and YAN Hua |
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| Affiliation: | State Key Laboratory of Explosion and Safety Science, Beijing Institute of Technology, Beijing100081, China;State Key Laboratory of Explosion and Safety Science, Beijing Institute of Technology, Beijing100081, China;State Key Laboratory of Explosion and Safety Science, Beijing Institute of Technology, Beijing100081, China;State Key Laboratory of Explosion and Safety Science, Beijing Institute of Technology, Beijing100081, China |
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| Abstract: | Under higher temperatures the charge within a warhead will be subjected to physical and chemical changes, which will influence the security of the warhead launching process. In this paper the problem is studied adopting finite difference method for the case of a rocket-powered missile. Temperature distribution tables are given through quadrature experiments, and the results fit the actual measured values very well. The results also show that to ensure the launching security of rocket-powered missiles having warhead charge critical temperature close to about 60 ℃, the designer can select appropriate heat insulation structural parameters. |
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| Keywords: | rocket powered missile warhead heat transfer finite difference method |
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