液体推进剂火箭爆炸毒源强度研究  

THE EXPLOSIVE TOXICITY SOURCE INTENSITY RESEARCH FOR LIQUID PROPELLANT ROCKET

作　　者：胡世祥[1] 车著明 佘春东 

机构地区：[1]中国人民解放军总装备部

出　　处：《宇航学报》2000年第4期134-139,共6页Journal of Astronautics

摘　　要：在国内外研究液体推进剂爆炸火球生长规律的基础上[1 4 ,6] ,建立了火箭爆炸事故所形成的火球的生长规律、空气卷入量和N2 O4 富余量的数学模型。利用已有的蒸发理论[5] ,探讨了火箭发射事故毒源强度及其衰减的计算数学模型。文中所建的数学模型 。Based on research of the explosive firedball's growing rule for liquid propellant rocket about domestic and abroad,math's models about the explosive fireball's growing rule and about the quantity of the air being involved in and about the surplus of N 2O 4 is established.In the light of evaporate theory of reference [5] ,math's models about the explosive toxicity source intensity and it's decline is explored.The math's model is essential identical with the fireball photograph and the toxicity source intensity of accident that had happened.

关 键 词：液体推进剂火箭 爆炸事故 火球生成 毒源强度 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]