液体推进剂火箭爆炸辐射效应研究  

THE EXPLSION HEAT RADIATION EFFECT INVESTIGATION FOR LIQUID BIPROPELLANT ROCKET

作　　者：陈新华[1] 

机构地区：[1]国防科工委指挥技术学院

出　　处：《宇航学报》1997年第1期80-85,共6页Journal of Astronautics

摘　　要：本文提出了液体双组元推进剂火箭爆炸热辐射效应理论计算模型，并介绍了四氧化二氮／偏二甲肼推进剂爆炸实验研究结果。利用该理论模型计算了液体推进剂火箭爆炸时产生的火球直径，火球温度，火球持续时间，火球漂移，火球辐射热流，高空环境对火球尺寸的影响，火球热辐射破坏危险距离等。理论计算结果与实验测量结果吻合。This paper derelops a theoretical model of the explosion heat radiation effect for Liquid bipropellant rocket, presents the explosion experimant results for the N 2O 4/UDMH propellant By the use of this theoretical model,the fireball diameter,the fireball temperature,the fire ball duration time,the fireball drift,the radiation heat flow of the fireball,the relationship between the fireball size and upper air arrviroment and the dange distance for the heat radiation of the fireball are calculated for the Liquid bipropellant rocket explsions The calculation results agree with the experiment data,which proves that the theoretical model can provide valuable data for the enginerring dasign of escape system of manned space Launch vehicle and for the building of the space vehicle Launching base

关 键 词：液体推进剂 火箭 爆炸 热辐射 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]