液体推进剂运载火箭爆炸热过程特性试验研究

推进技术 ›› 1996, Vol. 17 ›› Issue (5): 18-22.

液体推进剂运载火箭爆炸热过程特性试验研究

王振国,鄢小清,刘昆,张育林

国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系

发布日期:2021-08-15

AN EXPERIMENTAL STUDY ON HEAT PROCESSES PROPERTES OF LIQUID PROPELLANT ROCKET EXPLOSION

Dept.of Aerospace Technology,National Univ.of Defense Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defense Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defense Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defense Technology,Changsha,410073

Published:2021-08-15

摘要/Abstract

摘要： 详细描述了液体火箭推进剂（Ｎ２Ｏ４／ＵＤＭＨ）爆炸试验装置及其爆炸热过程特性测量。通过５０ｋｇ、１００ｋｇ、３００ｋｇ三种不同推进剂总质量的爆炸试验，得到了推进剂爆炸火球内部温度场、辐射温度场、辐射热流场和火球直径等热过程特性参数。还分析了热过程特性参数随推进剂总质量、时间和空间位置的变化规律。

关键词: 液体火箭推进剂;推进剂爆炸;爆炸性能;热辐射;温度分布

Abstract: est facility,measurement methods of heat process and measurement system for liquid propellant (N2O4/UDMH) explosion are described.Explosive tests of propellant with three kinds oftotal mass, 50kg,100kg and 300kg,are carried out.Heat process property parameters of explosivefireball Such as internal temperature field, radiant temperature field, radiant heat flux density andfireball diameter are measrued.The effect of total propellant mass,time and location on the heatprocess property parameters are also analysed.

Key words: Liquid rocket propellant;Propellant explosion;Explosion Property;Thermalradiation;Temperature distribution

王振国,鄢小清,刘昆,张育林. 液体推进剂运载火箭爆炸热过程特性试验研究[J]. 推进技术, 1996, 17(5): 18-22.