液体推进剂爆炸理论与实验研究

建立了自燃液体火箭推进剂爆炸热辐射效应和冲击波特性理论模型，介绍了实验研究的方法，给出了Ｎ２Ｏ４／ＵＤＭＨ液体推进剂爆炸产生的火球直径、火球温度、火球辐射热流、爆炸冲击波超压值等参数计算与实验观测结果，结果表明计算结果与实验观测结果吻合。由Ｎ２Ｏ４／ＵＤＭＨ液体火箭推进剂爆炸产生的火球最大直径Ｄｍａｘ和火球持续时间ｔ０是推进剂总重量Ｗ０的函数，根据实验数据整理的函数关系式:利用该理论模型预测了大型Ｎ２Ｏ４／ＵＤＭＨ组元液体推进剂运载火箭发生爆炸事故产生的上述参数，以及热辐射和冲击波不发生破坏和危害的安全距离。该计算模型可为载人航天器逃逸系统及航天靶场设计提供理论数据。

THEORETICAL AND EXPERIMENTAL STUDIES FOR LIQUID ROCKET PROPELLANT EXPLOSION

This paper develops a theoretical model of the heat radiation effect and the shock wave characteristics for liquid hypergolic rocket bipropellant explosion,as well as the explosion experimental method. The calculated and experimental results of the diameter,duration, temperature,radiation heat flows of the fireball, overpressure of the shock wave are described for N2O4/UDMH liquid propellant explosion. The calculated results agree with the experimental data. The maximun diameter Dmax and the duration time to of the fireball are functions of the total propellant weight. The following equation is derived by least square fit to the data of N2O4/UDMH propellant explosion experiments:Dmax = 3.924W .The application of this theoretical model to predicte the above parameters and the safety distance for large scale N2O4/UDMH liquid propellant rocket explosions proves that the theoretical model can provide valuable data for enginering design of escape system of manned space launch vehicle and for the building of the space vehicle launching base.