液体推进剂运载火箭爆炸热过程特性理论研究

推进技术 ›› 1996, Vol. 17 ›› Issue (6): 52-57.

液体推进剂运载火箭爆炸热过程特性理论研究

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

THEORETICAL STUDY ON THERMAL PROCESSES PROPERTIES IN LIQUID PROPELLANT ROCKET EXPLOSION

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

Published:2021-08-15

摘要/Abstract

摘要： 建立了液体推进剂爆炸火球成长过程和火球辐射传热理论模型，研究了火球尺寸变化、火球持续时间、火球内部温度、火球辐射传递过程等方面的变化规律，理论预测结果与试验测量结果吻合。还讨论了火球升离地面的临界条件、高空环境对火球直径的影响和火球随风漂移等三方面的问题。

关键词: 液体推进剂;运载火箭;推进剂爆炸;爆炸效应;数学模型;辐射传热

Abstract: theoretical model of fireball growth and heat radiation transfer in liquid propellant launch vehicle explosion is presented. Fireball diameter, duration time, internal temperature and radiating transfer process are studied. Theoretical predicting has good agreement with experiment results. Critical conditions of fireball lift-off, effects of high altitude environment and fireball gliding are also analysised.

Key words: Liquid propellant;Launch vehicle;Propellant explosion;Explosion effect;Mathematical model;Radiating heat transfer

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理论研究[J]. 推进技术, 1996, 17(6): 52-57.