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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。
The theoretical model of thermal radiation and shock wave characteristics of spontaneous combustion liquid rocket propellant explosion was established. The experimental research methods were introduced. The effects of fireball diameter, fireball temperature, fireball radiation heat flux, explosion shock wave overpressure Value and other parameters calculated and experimental observations, the results show that the calculated results are consistent with the experimental observations. The maximum diameter of fireball (Dmax) and fireball duration (t0) generated by the explosion of N2O4 / UDMH liquid rocket propellant are a function of the total weight of propellant, W0. According to the experimental data, the function formula is as follows: The N2O4 / UDMH The above parameters resulting from an explosion of a liquid propellant carrier rocket and the safety distance at which heat radiation and shock waves are not destroyed or endanger. The computational model can provide theoretical data for manned spacecraft escape system and spacecraft design.