Effects of propellant rocket motor aluminum content, chamber pressure, nozzle exit diameter, and lift-off acceleration were evaluated with respect to degradation of protective coatings applied to flame deflectors and umbilical masts; most promising materials were evaluated during scale-model firings; data and scaling factors were correlated with full-scale effects data compiled from launch histories of Titan IIIC; it was found that deflector erosion was not proportional to aluminum content of propellant, and that erosion was influenced by manner in which aluminum affected burning characteristics of propellant.
Effects of exhausts from aluminized solid propellants on launch facilities
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 7
1967
7 pages
Aufsatz (Zeitschrift)
Englisch
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Combustion of Aluminized Solid Propellants
AIAA | 2000
|Microstructure Effects in Aluminized Solid Rocket Propellants
Online Contents | 2010
|