Liquid-propellant rocket abort fire model.
暂无分享,去创建一个
During a rocket launch pad abort, a hazardous payload material can be subjected to a severe thermal environment from the resulting fireball. A model has been developed which specifies heat flux from the fireball as a function of time for any initial propellant quantity. This model can be used as a thermal design criterion for hazardous component protection systems. Existing data support the validity of the model.
[1] J. B. Gayle,et al. Size and duration of fireballs from propellant explosions , 1965 .
[2] B. E. Bader,et al. LAUNCH HAZARDS ASSESSMENT PROGRAM. REPORT ON ATLAS/CENTAUR ABORT , 1965 .
[3] J. Turner,et al. The dynamics of spheroidal masses of buoyant fluid , 1964, Journal of Fluid Mechanics.
[4] H. Wagner,et al. Carbon formation in premixed flames , 1967 .