Presented in this paper are the test results of the engineering test model of integrated cooler experiment. This cooler consists of integrating a small, low-power Stirling cryogenic refrigerator with a small mass of a triple point phase change material (PCM). The advantages of this type of cooler are a closed system; no vibrations during sensor operation; the ability to absorb increased 'spike' heat loads; potentially longer system lifetime; and a lower mass, cost, and power consumption. Experimentation was performed in the laboratory using methanol as the PCM. The goals of the testing were to demonstrate the practical use of new technologies and demonstrate the operation of the total system for simulated sensor scenarios. Presented are the results of the first series of tests.

Flexible thermal links, often important components in the thermal management of cryogenically cooled instruments, are usually made by soldering bundles of copper braid to rigid end pieces. In addition to being time consuming and requiring a highly skilled and well-practised technician, the soldering process has inherent disadvantages. The solder tends to wick around each individual wire in the braids, imposing both additional rigidity and thermal impedance. Solder can also present potential outgassing problems. The authors have developed a simple solderless process for securely attaching a flexible braid to solid end blocks in such a manner as to dramatically reduce thermal impedance at the interface between the braid and the block and also to maintain full flexibility of the braid.

This paper describes the issues associated with thermal management of the Sounding of the Atmosphere using Broadband Emission Radiometer instrument, proposed by NASA LaRC and the Space Dynamics Laboratory at Utah State University. With the instrument subjected to severe mass and power constraints, the TRW miniature pulse tube cooler has been baselined to maintain the focal plane at less than 75 K over a required lifetime of two years. Cooler and electronics heat is to be rejected through the spacecraft bulkhead at 300 K to radiators at approximately 290 K. The optical cavity is to be maintained at 210 K by a separate radiator. Approaches to ensure that heat loads do not exceed cooler capacity, radiator studies, and interfacing the cooler to the sensor and spacecraft are discussed.