Performance Characterization of the Ball Aerospace 35/60K Protoflight Spacecraft Cryocooler

Abstract

This paper outlines results from the preliminary characterization of the Ball Aerospace 35/60K Protoflight Spacecraft Cryocooler performed at the Air Force Research Laboratory (AFRL) Space Vehicles Directorate. The cooler was developed under joint sponsorship by NASA Goddard Space Flight Center and AFRL for space based infrared sensing applications. This cryocooler is a unique, three stage Stirling cycle protoflight cryocooler unit capable of simultaneously lifting 0.4 W at 35 K and 0.6 W at 60 K. The physical characteristics and component details of the cooler are included in this report. The thermodynamic performance of the cryocooler is presented in terms of the effect ofvariable heat loads on the cold end, mid-stage, and upper stage temperatures. Based on the acquired data, performance models are presented using two-variable regression methods.