Thermal analysis of PANSAT batteries and electrical power subsystem

The thermal design of a spacecraft ensures proper heat transfer so all components and subsystems remain within prescribed temperature limits during all aspects of the spacecraft's mission. This thesis develops a point to-point heat flow model of the Electrical Power Subsystem (EPS) and its associated housing for the Petite Amateur Navy Satellite (PANSAT). This analysis was performed to identify physical locations in the EPS where temperatures may exceed the limits established to protect sensitive electronic components, and to define the expected environment of the batteries. The Integrated Thermal Analysis System (ITAS) and a Steady State Thermal Analyzer and Model Builder were used to perform steady state and transient analyses on the EPS: analysis of the batteries was performed using ITAS only. The simulated transient temperatures within the EPS housing remained within limits, but the batteries exceeded specifications. It is suggested that a passive thermal control technique be adapted for the batteries and its design be experimentally validated before flight

Department dc:contributor.department

Astronautical Engineering

Grantor dc:publisher

Monterey, California. Naval Postgraduate School

Year dc:date.issued

1994

Author dc:creator

• Patterson, Sheila A.

Advisor dc:contributor.advisor

• Ross, I.M.

Language dc:language.iso

en_US

Handle dc:identifier.uri

https://hdl.handle.net/10945/28605

OAI identifier oai:identifier

oai:calhoun.nps.edu:10945/28605