By virtue of their inherent parallel redundancy, heat pipes (HP) are logical elemental building blocks for the construction of spacecraft radiators. In pumped loop space radiators, a micrometeoroid puncture of a cooling-fluid carrying tube would cause eventual loss of cooling fluid, thus leading to failure of the radiator. In contrast, space radiators composed of a large number of heat pipes would be relatively immune to puncture from micrometeoroids or small space debris because loss of an individual heat pipe, whose function is completely independent of that of its neighbors, would result only in the loss of that small fraction of total radiating area represented by the punctured heat pipe’s radiating surface. Thus, overall radiator reliability can be significantly enhanced, even with lower wall thickness of its heat pipe elements, which also would reduce radiator mass.
Increased survivability coupled with reduced mass is of strategic importance in spacecraft power system radiators, since past studies of power systems with either solar or nuclear heat sources have shown (Juhasz and Jones, 1986, Brandhorst et al., 1991) that radiator weight accounts for a significant portion of overall spacecraft launch mass. This is especially true for dynamic energy conversion systems utilizing the Brayton or Stirling thermodynamic cycles, since these systems have relatively low mean effective heat rejection temperatures. Thus, application of graphite-carbon composite technology to space radiator heat pipes will lead to even greater savings in the total Earth-to-orbit mass that needs to be launched for a given mission, and thereby contribute to the “low-cost access to space” initiative, which is a goal to be implemented during the early decades of the 21st century.