An analysis is made of a power supply system design for an orbiting spacecraft. Two designs are developed for a highly reliable solar power supply, both of which encompass redundant components. Reliability estimates are developed. Conclusions are reached on the alternative with the most advantageous performance and reliability characteristics. Details of the improvement in reliability resulting from various techniques in design are given, as are the calculations involved. The number of solar cell modules required to satisfy power-usage requirements at a given reliability level is also developed; this includes consideration of the effects of meteoroid bombardment and Van Allen Radiation.
