The electrical power subsystem design for the high energy solar physics spacecraft concepts
This paper discusses the Electrical Power Subsystem (EPS) requirements, architecture, design description, performance analysis, and heritage of the components for two spacecraft concepts for the High Energy Solar Physics (HESP) Mission. It summarizes the mission requirements and the spacecraft subsystems and instrument power requirements, and it describes the EPS architecture for both options. A trade study performed on the selection of the solar cells - body mounted versus deployed panels - and the optimum number of panels is also presented. Solar cell manufacturing losses, array manufacturing losses, and the radiation and temperature effects on the GaAs/Ge and Si solar cells were considered part of the trade study and are included in this paper. Solar cell characteristics, cell circuit description, and the solar array area design are presented, as is battery sizing analysis performed based on the power requirements during launch and initial spacecraft operations. This paper discusses Earth occultation periods and the battery power requirements during this period as well as shunt control, battery conditioning, and bus regulation schemes. Design margins, redundancy philosophy, and predicted on-orbit battery and solar cell performance are summarized. Finally, the heritage of the components and technology risk assessment are provided. 5 refs.
- OSTI ID:
- 6310447
- Report Number(s):
- AIAA-Paper--93-1190; CONF-9302142--
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
140501 -- Solar Energy Conversion-- Photovoltaic Conversion
140600* -- Solar Energy-- Photovoltaic Power Systems
DESIGN
DIRECT ENERGY CONVERTERS
ELECTRONIC EQUIPMENT
ENERGY SYSTEMS
EQUIPMENT
GALLIUM ARSENIDE SOLAR CELLS
PHOTOELECTRIC CELLS
PHOTOVOLTAIC CELLS
POWER SUPPLIES
POWER SYSTEMS
RADIATION EFFECTS
SOLAR CELLS
SOLAR EQUIPMENT
SPACECRAFT POWER SUPPLIES
TEMPERATURE DEPENDENCE