Secondary Power Generating System for a Manned Logistic Spacecraft

Abstract

The results of a study of secondary power generating systems for a twelve-man logistic spacecraft are presented for orbital space flights of 24 hours and launch dates during the post 1968 time period. Power systems are evaluated on the basis of performance, weight, radiator area and availability. The secondary power systems considered were fuel cells, batteries, Stirling engines, internal combustion engines and turbines. The power generating systems are evaluated for a nominal 1-1/2 kwe continuous load during orbital space flight to establish the various system trends. The peak power requirement for aerodynamic control was established at 14 kwe during entry.