Propulsion systems for deep space exploration that rely on nuclear energy require innovative advancements in radiator technology, both materials and construction technique, to meet the demands associated with high rejection temperatures. A five fold reduction in radiator specific mass is achievable and will be needed to meet the demanding challenge of space exploration. Our development of a carbon‐carbon (C‐C) based radiator design unaffected by long term exposure to high temperature and radiation has wide ranging application, for both small and large power conversion systems. Our results stem from a NASA SBIR program focused on demonstrating thermal performance in a high temperature carbon‐carbon (C‐C) radiator configured with titanium water‐ heat pipes, using approximately 500 K water for the working fluid. However, joining strategy and material choices employed are appropriate for very high temperature alkali fluids. Distinct design advantages of carbon‐carbon material are its low density, unlimited life, and ability to tailor its physical properties through fiber selection, fiber orientation, and special processing. We will report on our experience in joining of titanium to carbonized materials through direct carbonization and brazing. Results of thermal tests at Sandia National Laboratories on a 1 kW thermal radiator will be presented, along with construction progress and testing of a 2.6 m2 sandwich radiator for NASA Glenn.
An Ultra‐Lightweight, High Performance Carbon‐Carbon Space Radiator
SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2007: 11th Conf Thermophys.Applic.in Micrograv.; 24th Symp Space Nucl.Pwr.Propulsion; 5th Conf Hum/Robotic Techn & Vision Space Explor.; 5th Symp Space Coloniz.; 4th Symp New Frontrs & Future Con ; 2007 ; Albuquerque, New Mexico (USA)
AIP Conference Proceedings ; 880 , 1 ; 421-429
30.01.2007
9 pages
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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