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Ozone decomposition on alumina: Implications for solid rocket motor exhaust
Author(s) -
HanningLee M. A.,
Brady B. B.,
Martin L. R.,
Syage J. A.
Publication year - 1996
Publication title -
geophysical research letters
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 2.007
H-Index - 273
eISSN - 1944-8007
pISSN - 0094-8276
DOI - 10.1029/96gl01808
Subject(s) - solid fuel rocket , ozone , plume , decomposition , ultraviolet , ozone depletion , materials science , rocket (weapon) , analytical chemistry (journal) , environmental science , chemistry , environmental chemistry , propellant , meteorology , aerospace engineering , physics , organic chemistry , optoelectronics , engineering
Rates of ozone decomposition on aluminum oxide (alumina) particles were measured in a flow tube reactor equipped with molecular beam sampling mass spectrometry and ultraviolet absorption spectroscopy, and in a static reaction cell equipped with ultraviolet absorption spectroscopy. Reaction probabilities η are reported for ozone on α‐alumina, γ‐alumina, and Chromatographic alumina (hydroxylated alumina), respectively, over the temperature range −60 to 200°C. This work addresses the potential for stratospheric ozone depletion by launch vehicle solid rocket motor exhaust. Considering best estimates of plume particle size distributions and dispersion rates, we calculate ozone depletion profiles, for direct decomposition on alumina only. The calculated ozone holes are rather narrow. In the worst case, ozone levels are within 5 × 10 −5 of ambient in the center of the plume. A simple analysis of the global impact of alumina particles on ozone decomposition indicates a potential steady‐state daytime depletion of < 2.6 × 10 −8 at present launch rates.