A spacecraft cooling system for a charged coupled deviceThis paper describes the thermal analysis, design, and testing of a dedicated cooling system for a Spartan spacecraft payload. A simple reliable design that requires minimum power consumption and minimum weight was developed. The payload has a CCD detector that must be maintained at a temperature of approximately -40 C or colder. The cooling system consists of a fin radiator, dual redundant heat pipes, and a thermal electric device (TED). The system was analytically modeled through the use of the Simplified Shuttle Payload Thermal Analyzer (SSPTA) computer program. A thermal test of the system simulating flight conditions was conducted to correlate the computer model and verify performance specifications.
Document ID
19870051484
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Walker, Mary S. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Tulkoff, Philip (Swales and Associates Beltsville, MD, United States)