A series of tests involving the combustion of solid and liquid rocket propellants used to fuel the Titan II, Titan IV and Delta II launch vehicles was performed. The purpose of these tests was to obtain chemical combustion data to support modeling of launch vehicle accidents. Propellants tested were Aerozine-5O, dinitrogen tetroxide, RP- 1, liquid oxygen, PBAN, and Castor IVA. Tests were conducted in a 150-liter stainless steel combustion chamber in air at nominal pressure (0.8 atmospheres at Denver barometric conditions). Measurements of the chamber gas temperature and internal pressure were taken and gas samples were withdrawn and analyzed for combustion gases, unreacted propellants, unreacted oxygen and organic vapors. A witness plate was used to collect condensed residues. Results from these tests suggest different chemical fates of these propellants than those predicted by theory alone.


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    Liquid-Propellant Rocket Abort Fire Model

    B. E. Bader / A. B. Donaldson / H. C. Hardee | NTIS | 1970


    Liquid-propellant rocket abort fire model.

    BADER, B. E. / DONALDSON, A. B. / HARDEE, H. C. | AIAA | 1971


    Orion Launch Abort Acoustics

    Cadieux, Francois / Barad, Michael / Jensen, James et al. | NTRS | 2019