Cryocooler load increase due to external contamination of Low-e cryogenic surfaces in space
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The efficiency, of the electronics plays a large part in determining the overall spacecraft power requirements to operate the cooler as well as determining the thermal dissipation characteristics of the various electrical components. The results of all the performance measurements are presented in the paper.
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The design and fabrication of a small, closed-cycle, periodic 10 K sorption cyrocooler laboratory system is described. The cooler is designed to provide cooldown from 60 to <10 K in under 2 minutes, maintain a simulated detector heat load of 100 mW below 10 K for over 10 minutes, and have the ability to be recycled in under 6 hours.
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This paper presents the fundamental equations governing cyocooler mechanical efficiency and launch vibration response in terms of their implications for cooler design.
An overview is presented of ongoing efforts at the Jet Propulsion Laboratory and Goddard Space Flight Center in support of current flight projects, near-term flight instruments, and long-term technology development.
Two continuous opertation 18K/20K sorption coolers are being developed by the Jet Propulsion Laboratory (JPL) as a NASA contribution to the European Space Agency (ESA) Planck mission that is currently planned for a 2007 launch.
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This paper examines the performance trade for the two redundancy approaches with explicit treatment of the effect of operational level on the reliability of the redundant and primary unit.