Available at: http://digitalcommons.calpoly.edu/theses/913
Date of Award
MS in Aerospace Engineering
This thesis describes the passive thermal design of NASA’s Multiple Payload Ejector (MPE) using optical coatings and insulation blankets, thermal analysis performed on the MPE in worst case hot and cold orbits as well as thermal vacuum chamber simulation, the results of the MPE system level qualification thermal vacuum test, and the correlation of data between the modeling analysis and the thermal vacuum test. Initial conditions, environments, and model construction are discussed along with the Thermal Desktop predictions for worst case flight conditions and thermal balance. The temperature data from the thermal vacuum test is compared with the predictions from Thermal Desktop, and the model will be updated for heat generation and conduction values if needed.
The scope of this document is limited to a “2-Stack” MPE configuration. After analyzing the MPE thermal vacuum test data and comparing it to the thermal model, MPE demonstrates all avionics hardware to have a 20°C margin over worst case hot and cold flight predictions. Therefore from a thermal perspective, the MPE is fully qualified for flight.