Thermal Subsystem

THIS YEAR'S TEAM:

Danetta Duran - Team Lead
Robert Clark - Industry Mentor

Introduction

Spartnik Thermal Control Systems (TCS) will maintain the temperature of all Spartnik's components within acceptable range for the life of the spacecraft. TCS will insure that the design will function with minimum modifications in all possible thermal environments. Futhermore, additional design drivers include data acquisition requirements, launch and ascent environments, and operational conditions.

Temperature variances in variable-angle orbits can be minimized, but not eliminated without resorting to active thermal control methods. These orbits represent the extreme operating envelope of the thermal control system. Although Spartnik is designed with maximum orbital flexibility, some orbits will exceed operating thermal limits.

System Status: March 2001

The Thermal Team has been busy writing the test procedures for Spartnik's system test inside a thermal vacuum chamber. We have calibrated the thermistors to the manufacture's specifications. The TCS team would like to thank NASA Ames FEE testing group for letting us use their testing equipment and helpful advice. For the remainder of the semester, Team TCS will complete the Thermal test procedures, and locate a suitable thermal vacuum chamber.

System Status: November 1999

• 3D models for the thermal analysis have been completed using SINDA/3D, the graphical version of SINDA. Spartnik is to be analysis by merging all models and applying various heat loads.
• Obtaining transient state result using SINDA/3D.
• Thermal vacuum testing for electronic components is underway. This test will be conducted at Lockheed Martin. Operation Order for thermal testing will be documented in Lockheed's format.
• Current projects include painting the interior surface of the bottom plate, once it is built, and completing the 3D model for thermal analysis.