NASA NTRS · 19720026294
Heat pipe technology for advanced rocket thrust chambers
Abstract
The application of heat pipe technology to the design of rocket engine thrust chambers is discussed. Subjects presented are: (1) evaporator wick development, (2) specific heat pipe designs and test results, (3) injector design, fabrication, and cold flow testing, and (4) preliminary thrust chamber design.
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Rousar, D. C.. 1971-09-15. Heat pipe technology for advanced rocket thrust chambers. https://ntrs.nasa.gov/citations/19720026294
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