The currently used micrometric Al powders (30-50 μm nominal size) were replaced by nanometric powders (0.1-0.2 μm) in order to investigate the effects of aluminum particle size on burning rate and agglomeration processes at the burning surface of solid rocket propellants. Burning rate increases (up to 100%) were observed, different aluminum agglomeration modified the flame structure, and the condensed combustion products featured different aluminum oxidation histories. The condensed combustion products were investigated by EM (Electron Microscopy), and XPS (X-ray Photoelectron Spectroscopy) to characterize their morphology, size, and chemical composition. Results obtained point out that the high reactivity of nano aluminum powders offers an efficient way to increase rocket propellant performance.
Nano Propellants for Space Propulsion
GALFETTI, LUCIANO;DE LUCA, LUIGI;
2004-01-01
Abstract
The currently used micrometric Al powders (30-50 μm nominal size) were replaced by nanometric powders (0.1-0.2 μm) in order to investigate the effects of aluminum particle size on burning rate and agglomeration processes at the burning surface of solid rocket propellants. Burning rate increases (up to 100%) were observed, different aluminum agglomeration modified the flame structure, and the condensed combustion products featured different aluminum oxidation histories. The condensed combustion products were investigated by EM (Electron Microscopy), and XPS (X-ray Photoelectron Spectroscopy) to characterize their morphology, size, and chemical composition. Results obtained point out that the high reactivity of nano aluminum powders offers an efficient way to increase rocket propellant performance.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
