ANALYTICAL STUDY TO DETERMINE THE FEASIBILITY OF A RADIANTLY COOLED CRYOSTAT FOR SPACECRAFT.
Final rept. Sep 67-Aug 69,
OKLAHOMA STATE UNIV STILLWATER SCHOOL OF MECHANICAL ENGINEERING
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The feasibility of using a space radiator at cryostat temperatures was examined in this study. This was done considering an IR detector as the object of cooling and was limited to highly reliable, non-moving, non-degrading radiator and system surfaces. A simple flat surface radiator and enclosure was evolved and analyzed. An attempt at experimental evaluation was made but failed due to mechanical problems. The analytical results indicate that the system proposed could be used to passively cool a detector to temperatures around 230 degrees F-128 degrees K in a 300 statute mile circular orbit 175 degrees R-97 degrees K for a 600 satute mile orbit and 165 degrees R-92 degrees K for a 900 statute mile orbit. These temperatures were obtained with common non-degrading aluminized surfaces. Author
- Solid State Physics
- Unmanned Spacecraft