ABSTRACT
This chapter presents spacecraft electrical power systems for interplanetary and deep space missions. Being in much harsher environments, they impose very different design requirements that must be considered very early in the overall spacecraft design. Significantly different power system architecture and design approaches are required for such missions as compared to those in Earth orbit. Low sun intensity and very cold temperatures are typical in missions far away from the sun, and very high sun intensity and very high temperatures are typical in near-sun missions. Environments on the Moon, Mars, Jupiter, and Saturn are reviewed. The radioisotope thermoelectric generator, a prime candidate for electrical power in most missions to the outer planets, is presented. The performance of Li-ion battery and power electronics components at cold temperatures is reviewed.
