Abstract
The structural analysis and design of the Douglas Aircraft S‐IV second stage of the C‐1 configuration of the Saturn space exploration vehicle arc discussed; the S‐IV employs four Pratt & Whitney LR‐119 engines burning liquid hydrogen. Design criteria, structural analysis, manufacturing considerations and ground handling problems are placed in perspective in relation to design of the system. The solutions of two problems which proved important (free‐standing capability of an unpressurized large thin shell, and separation of two cyrogenic fluids at different temperatures by a common bulkhead) are presented.
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