Equations useful in design studies are derived for determining optimum weight distribution for 2-stage tandem rockets for case of different structural factors and propellant specific impulses in each stage; minimization of gross weight for given required burn-out velocity and payload is criterion of optimization used; example included.
On optimization of two-stage rockets
Jet Propulsion
Jet Propulsion ; 27 , n 4
1957
2 pages
Article (Journal)
English
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Optimization of Two-Stage Rockets
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