The design, fabrication, and assembly of six large-scale ablative thrust chambers, utilizing the compression-molded, building block concept is described in this volume. The chambers were designed for evaluation and demonstration of the feasibility for in-space use, at chamber pressures of 40 to 300 psia and thrust equivalents of 5,100 to 38,000 lb for durations up to 20 min. Materials were evaluated in 36 subscale engine tests. (Author)
Ablative Thrust Chamber Feasibility
1963
113 pages
Report
Keine Angabe
Englisch
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|Thrust improvement with ablative insert nozzle extension
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|Design of ablative thrust chambers and their materials
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