POWER SYSTEM CHALLENGES FOR SMALL SATELLITE MISSIONS
Craig S. Clark, Alejandro Lopez Mazarias Clyde Space Ltd., 6.01 Kelvin Campus, West of Scotland Science Park, Glasgow G20 0SP Scotland, Email: craig.clark@clyde-space.com

ABSTRACT For the last few decades, the focus of power subsystem development and advancement has revolved around the needs and requirements of large, high power missions, mainly for telecommunications applications. Whereas the challenges to increase efficiency and to reduce mass and volume in these applications are valid, the needs of the small satellite mission have often been over shadowed. The growing number and utility value of small satellites highlights the need for careful and measured consideration for the specific power requirements on small satellite missions. The challenge for mission designers and, in this context, small satellite power system specialists, is to produce an efficient and flexible design that avoids the need for system redesign with each set of mission requirements. This paper sets out the various challenges facing small satellite mission designers and evaluates common power system architectures against an innovative approach to power management for small satellites. 1. INTRODUCTION

power system electronics to be compatible with a multitude of mission profiles and be scalable in power handling capability. In addition, mission designers are consistently vying for a reduction in mass and more flexibility and modularity in the spacecraft make-up. Some spacecraft manufacturers are even investigating plug and play small satellite kits for fast response missions. At Clyde Space, we are developing power systems capable of meeting these demanding requirements but with a focus on cost effectiveness as well as performance. This paper outlines the systems under development at Clyde Space and compares their performance against the current systems used on today’s small satellites. Clyde Space are based in Glasgow, Scotland