Performance of the Spacelab Astro-1 mission heat pipe radiatorThis paper describes the design and performance of the Astro Integrated Radiator System (IRS). The system was recently ground tested and proven successful in rejecting approximately 400 watts of heat. The radiator was constructed from an aluminum panel configured to form two orthogonal planes. Heat pipes were adhesively bonded and riveted to the radiator to isothermalize the surface. The IRS was subjected to a full thermal vacuum test to validate the thermal math model and to qualify the radiator for space flight. The thermal performance met prescribed temperature limits with margins at both extremes, and no mechanical failures occurred.
Document ID
19860038800
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Humphries, W. R. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Hamner, R. M. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Stallings, R. D. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Cotton, J. A. (Teledyne Brown Engineering Huntsville, AL, United States)