Test firings of rockets were made to study effects of propellant composition, pressure, and engine size on exhaust oxide particle size, and on composition of solid exhaust products; results of work and those by others were analyzed to better understand aluminum combustion and oxide condensation processes in rocket motors; combustion of aluminum was found to occur in vapor phase, and was essentially complete in engines studied although some combustion took place in nozzle; results indicate that condensation of oxide vapor can be described by first-order chemical kinetics; further particle growth by agglomeration appears likely.
Performance of solid propellants containing metal additives
AIAA J
AIAA Journal ; 3 , n 2
1965
8 pages
Aufsatz (Zeitschrift)
Englisch
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Solid Propellants Containing Activated Aluminum
British Library Conference Proceedings | 2006
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