| タイトル | Space shuttle heat pipe thermal control systems |
| 本文（外部サイト） | http://hdl.handle.net/2060/19740010394 |
| 著者（英） | Alario, J. |
| 著者所属（英） | Grumman Aerospace Corp. |
| 発行日 | 1973-10-01 |
| 言語 | eng |
| 内容記述 | Heat pipe (HP) thermal control systems designed for possible space shuttle applications were built and tested under this program. They are: (1) a HP augmented cold rail, (2) a HP/phase change material (PCM) modular heat sink and (3) a HP radiating panel for compartment temperature control. The HP augmented cold rail is similar to a standard two-passage fluid cold rail except that it contains an integral, centrally located HP throughout its length. The central HP core helps to increase the local power density capability by spreading concentrated heat inputs over the entire rail. The HP/PCM modular heat sink system consists of a diode HP connected in series to a standard HP that has a PCM canister attached to its mid-section. It is designed to connect a heat source to a structural heat sink during normal operation, and to automatically decouple from it and sink to the PCM whenever structural temperatures are too high. The HP radiating panel is designed to conductively couple the panel feeder HPs directly to a fluid line that serves as a source of waste heat. It is a simple strap-on type of system that requires no internal or external line modifications to distribute the heat to a large radiating area. |
| NASA分類 | SPACE VEHICLES |
| レポートNO | 74N18507
NASA-CR-134201
SHM-20 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/195573 |
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