タイトル | Cryogenic heat pipe experiment - Flight performance onboard a sounding rocket |
著者(英) | Sherman, A.; Mcintosh, R.; Quadrini, J.; Harwell, W. |
発行日 | 1975-05-01 |
言語 | eng |
内容記述 | Flight data from a 15.8 mm OD, 760 mm long, axial-groove, methane cryogenic heat pipe verified successful priming and operation during six min of zero-g time. The nominal power applied to the evaporator was 60-w for the first 60 sec of zero-g time, 14 w for the next 270 sec, and 25 w for the last 20 sec of flight. The heat pipe condenser was mounted into an aluminum heat sink which was cooled to 103 K at launch and increased in temperature to 128 K by the end of the flight. Ground test data obtained for the flight heat pipe, together with theoretical predictions, indicate a zero-g heat transport capability of 3500 to 4000 w-cm in the 100-125 K temperature range. |
NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
レポートNO | 75A32872 AIAA PAPER 75-729 |
権利 | Copyright |
URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/448017 |
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