Power Contingency/Margin Methodology and Operational Envelope Analysis for PlanarSats

This paper presents a systematic, power-driven systems engineering approach for PlanarSats and the broader class of atto-, and femto-satellites, which are fundamentally constrained by extreme miniaturization and limited surface area for power generation. We reviewed existing space agency standards (NASA, ESA, JAXA) and the AIAA framework, identifying key limitations of current margin and contingency practices for highly miniaturized satellites. Based on these insights, we introduce an extended, log-linear methodology for determining phase- and class-appropriate power contingencies. The study defines power subcategories relevant to highly miniaturized platforms and demonstrates, through both historical and conceptual mission analyses, how application of these contingency values enables robust, reliable sizing of power systems. Detailed case studies show the direct relationship between power requirements, available surface area, and operational envelope, and provide practical methods for balancing requirement-driven and constraint-driven design. The results highlight that allocating surface area between solar arrays and electronics requires careful trade-offs. Additionally, the analysis demonstrates that using phase-aware margin management is essential for reducing risk and avoiding under-designed systems. This approach is intended to help designers optimize PlanarSat missions for reliability and efficiency under severe physical constraints. It also aims to provide a foundation for future advancements in highly miniaturized satellite architectures.