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space vehicle launching base
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  相似匹配句对
     Space is the vehicle of culture.
     空间是文化的载体。
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     vehicle;
     整车建模;
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     T-SPACE
     ■-空间
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     Space Operations Vehicle,SOV
     空间作战飞行器正悄悄走来
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     SPACE
     空间
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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...

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.

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。

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...

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

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。该理论计算模型可为载人航天器逃逸系统工程设计和航天靶场建设提供有价值的理论分析数据

 
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