Standard electrical power systems for unmanned spacecraft
American Institute of Aeronautics and Astronautics
American Institute of Aeronautics and Astronautics, Mar 31, 2007 - Science - 62 pages
This document, when followed in its entirety, will yield a robust EPS design suitable for very high-reliability space missions. This document specifies general design practices and sets minimum verification and validation requirements for power systems of unmanned spacecraft. The focus of the document is on earth orbiting satellites using traditional photovoltaic/battery power, but does not exclude other primary power generation and storage methods. This document does not address specific launch vehicle requirements however much of the design philosophy used here is applicable to launch vehicle power systems.
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AlAA and/or battery battery charge battery voltage Bode Plot circuit Conducted Susceptibility connectors damage deadband degradation discharge distribution point document eclipse electrical connectors electrical power electronics energy balance energy balance analysis energy storage EPS components EPS design EPS shall provide equipment essential loads factor Failure Modes fault protection fault-clearing flight frequency function fuse ground loops handling hardware harness heater impedance interface launch vehicle limited load current load group Load Margin lunar eclipse main bus maximum DOD minimum Multipoint Ground NOTE Nyquist Plot orbital revolution performance phase margin PMAD power budget power bus power distribution power margin power systems procuring authority radiation recharge reconditioning redundancy ripple safe-hold satellite simulation solar array solar cell space vehicle spacecraft specified spikes Stability standard Subnetwork subsystem surge telemetry temperature test strings thermal transfer orbit transient under-voltage Verification Vp-p VRS Architectures wiring worst-case