Technical Paper
Low-Temperature Thermal Control for a Lunar Base
1990-07-01
901242
The lunar environment places some unique demands on a thermal management system designed for manned lunar missions. A principal concern is that for many prime base locations the effective thermal sink temperature is often near or above nominal room temperature (25°C). This is due to the fact that a conventional radiator must look at either, or both, the sun and the hot lunar surface. Direct rejection of waste heat at such temperatures is thus impossible, and some alternative approach is needed to enable a sustained mission. This paper presents three such alternative systems: a heat pump assisted central thermal bus; an innovative, selective field-of-view radiator; and use of the lunar regolith as a heat sink. All of these concepts appear feasible, but each has uncertainties associated with its practicality and weight estimate. The heat pump assisted thermal bus appears to be the most viable concept and is discussed herein in some detail.