Paper discusses capability of nuclear pulse propulsion in performing manned missions to Mars and other planets using single-stage vehicle; data on 10-m-diam nuclear pulse propulsion module design is summarized and complete exploration vehicle employing module described; specific impulse of propulsion module is 2500 sec, its dry weight 200,000 lb; mission versatility of single vehicle design is emphasized; for minimal Mars landing mission, comparable to those proposed for less-capable multistages propulsion systems, earth-orbit departure weight of 640,000 lb is indicated; Mars mission capability supported by single launch, using Saturn first stage, is also described.
Manned planetary exploration capability using nuclear pulse propulsion
Canaveral Council Tech Soc
Proceedings of the 2nd Canaveral Council Technical Society on Space Congress ; 1965 Propulsion systems
1965
23 pages
Conference paper
English
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