A software power model for a spin-stabilized LEO spacecraft utilizing V/T charge control

Author

Jackson, Bill

Author_Institution

Ball Aerosp. & Technol. Corp., Boulder, CO, USA

Volume

3

fYear

1996

fDate

3-10 Feb 1996

Firstpage

219

Abstract

A software power model has been developed which characterizes the performance of the electrical power subsystem of a spin-stabilized LEO spacecraft which uses an eight-level V/T controller to perform the charge control function. The model accurately simulates the operational performance of the solar array and power control unit, the charge/discharge characteristics of the batteries, and the time-varying nature of various electrical loads. The end result is a prediction of battery state-of-charge as a function of time for a specified period of operations. This allows mission planners to perform operational trades relating to payload usage, and enables more efficient payload tasking without endangering vehicle health

Keywords

CAD; aerospace computing; aerospace control; power control; power system analysis computing; solar cell arrays; solar cells; space vehicle power plants; V/T charge control; battery state-of-charge; charge control function; eight-level V/T controller; energy losses; operational trades; payload tasking; pin-stabilized LEO spacecraft; software power model; spin-stabilized LEO spacecraft; Aerospace simulation; Automatic control; Batteries; Business; Low earth orbit satellites; Payloads; Power control; Space technology; Space vehicles; Sun;

fLanguage

English

Publisher

ieee

Conference_Titel

Aerospace Applications Conference, 1996. Proceedings., 1996 IEEE

Conference_Location

Aspen, CO

Print_ISBN

0-7803-3196-6

Type

conf

DOI

10.1109/AERO.1996.496065

Filename

496065