Fundamental relations between characteristic velocity, exhaust gas velocity, number of stages, propellant weight ratio, structural factor, takeoff to payload weight ratio, and thrust ratio, are determined and represented in preliminary design diagrams; summary of various rocket propulsion systems is followed by theory of ideal nozzle and influence parameters determining exhaust velocities in real nozzles; basic equations for evaluating rocket engines are compiled and analyzed. (See also n 25 Sept (I) 1964 p 1227-33)
Space carrier vehicles, rocket engines, propellants
Traegerraketen, Triebwerke, Treibstoffe
VDI -- Zeitschrift ; 106 , n 29
1964
11 pages
Aufsatz (Zeitschrift)
Deutsch
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Engineering Index Backfile | 1960
Online Contents | 1996
|Applicability of solid propellants to high-performance rocket vehicles
Engineering Index Backfile | 1962
|NTRS | 1967
|