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Hybrid Thermal Control Testing of a Cryogenic Propellant Tank

Author
Plachta, David W.
Published
August 1999.
Physical Description
1 electronic document
Online Version

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Summary
This report presents the experimental results of a hybrid thermal control system, one that integrates a passive system (multi-layer insulation) with an active system (a mechanical cyrocooler) applied to cryogenic propellant storage. These experiments were performed on a 1.39 m diameter spherical propellant tank filled with LH2 while installed in an evacuated chamber. The tank heat transfer to the cryocooler was accomplished with a condenser installed in the ullage of the tank and mated to the second stage of the cooler, and by conduction, through copper leaves mated to the first stage of the cooler. The first hybrid system test was performed with both the condenser and the leaves, a configuration that had excess capacity to remove the heat entering the tank; the second test was performed with only the condenser, with a capacity closely matched to the tank heating rate. In both of these tests, the goal of zero boil-off was achieved.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19990081126.
NASA/TM-1999-209389.
NAS 1.15:209389.
E-11818.
1999 Cryogenic Engineering; 12-16 Jul. 1999; Montreal, Quebec; Canada.
International Cryogenic Materials; 12-16 Jul. 1999; Montreal, Quebec; Canada.
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No Copyright.
View MARC record | catkey: 15642460