NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
The electrical power subsystem design for the high energy solar physics spacecraft conceptsThis 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.
Document ID
19930047061
Document Type
Conference Paper
Authors
Kulkarni, Milind (McDonnell Douglas Aerospace Seabrook, MD, United States)
Date Acquired
August 16, 2013
Publication Date
February 1, 1993
Subject Category
SPACECRAFT PROPULSION AND POWER
Report/Patent Number
AIAA PAPER 93-1190
Meeting Information
AIAA, AHS, and ASEE, Aerospace Design Conference(Irvine, CA)
Distribution Limits
Public
Copyright
Other