To extend knowledge of metallicsolid combustion in solid propellant rockets, metal additive behavior during actual propellant burning was investigated; alumina size distributions were obtained for coarse and fine oxidizer composite propellant burning in nitrogen atmosphere over pressure range from atmospheric to 500 psi; amount of additive agglomeration was higher for coarse oxidizer propellant and decreased with increasing pressure to 0.3 power over range from atmospheric to 250 psi; experimental findings of critical aluminum diameter required for agglomeration were in agreement with calculated data.
Alumina size distributions from high-pressure composite solid-propellant combustion
AIAA J
AIAA Journal ; 2 , n 10 ; p 1754-1760
1964
7 pages
Article (Journal)
English
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