Equations useful in design studies are derived for determining the optimum weight distribution for two-stage tandem rockets for the case of different structural factors and propellant specific impulses in each stage. Minimization of gross weight for a given required burnout velocity and payload is the criterion of optimization used. For illustrative purposes an example is included in which the optimum distribution is found for a hypothetical chemically-boosted atomic rocket. (Author)
Optimization of Two-Stage Rockets
1957
2 pages
Report
Keine Angabe
Englisch
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