Abstract:
Thermal modeling is an important part of spacecraft design, especially where critical components have narrow
operating temperature limits. For the Naval Postgraduate School’s NPSAT1 spacecraft, the lithium ion battery is the
spacecraft component with the smallest temperature range of 0°C to 45°C during operation. Thermal analysis results,
however, can only provide adequate results if there is sufficient fidelity in thermal modeling. Arguably, the values used
in defining thermal coupling for components are the most difficult to estimate because of the many variables that
define them. This document describes the work performed by the authors starting in the 2012 winter quarter as part of
the SS3900 directed study course. The objectives of the study were to determine an adequate thermal model of the
NPSAT1 battery as a lumped capacitance model, and an appropriate value of thermal resistance between the battery
and its mounting surface for three thermal interfaces: metal-to-metal (bolted interface), Kapton®, and Chotherm®
1671. These objectives were performed through testing in a thermal-vacuum chamber with controlled boundary
conditions. Modeling and simulation using the NX I-DEAS Thermal Model Generator software was performed to
duplicate the test results in simulation. Agreement between the simulations and testing was achieved with differences
ranging between +4°C and -8°C for the metal-to-metal interface, to as low as +2°C to -1°C using an elastomeric
thermal interface material (Chotherm® 1671). The test-validated thermal model can then be incorporated into the
larger NPSAT1 thermal model tospecifically evaluate battery temperatures for various flight operations.
