4-8. Development of a Deployable Film Type Radiator MASAHITO OGUMA, SHINTARO ENYA, YUICHIRO ASANO, HIROSHI MURAMOTO & NOBUHIRO TANATSUGU Summary A space radiator of novel design using a liquid heat transfer fluid has been constructed. Its form is a long ribbon (1.45 m^OAS m) which, in the inactive state, is coiled up. Upon deployment, it unrolls to full extension under coolant pressure. Since coolant channels remain deflated until deployment, such a radiator takes up less space than the standard ones. Investigating radiator performance, it was estimated to be about l/20th the weight and with l/25th the packaging volume of an ordinary radiator of equivalent heat rejection capability. Experimental measurements confirm numerical simulation results. Introduction The commercial use of space has become of great interest to business in recent years. Already, many plans exist for using the future space station or free flyers to conduct engineering and medical experiments. In Japan, plans exist for using the future space flyer unit (SFU) as well [1]. Given the above background, one can readily predict a rapid increase in the demand for power. One possible solution is a space power plant. Research on dynamic solar power systems indicate they perform with higher efficiency and smaller deployment areas than ordinary solar cell power systems. However, the cooling radiators of such a system will not be similarly smaller. An even worse problem is that, since the necessary radiator surface is proportional to power demands, radiator surfaces of the dynamic systems will be even larger. Although one possibility might be to increase the radiative heat flux through the radiators, it is difficult to do so with radiative temperatures held constant. Research is forced towards developing radiators with large deployment area, light weight and very precise control [2], Another problem is that of flexibility. Any satellite has many different missions to accomplish on each flight, with cooling temperatures differing from mission to mission. This can be accomplished by active regulation of the system, but usually requires scarce energy. Finally, there is a problem of building in redundancy. Parts of a particular subsystem on the satellite can be used as a backup to those of the major systems in case of emergencies. For instance, batteries, motors and cooling systems can often be designed to be swapped in and out. Past missions have not been able to provide backup radiators due to volume and weight constraints. Our proposed radiator can supply all of the above. It is very light and requires a Masahito Oguma & Shintaro Enya, Ishikawajima-Harima Heavy Industries Co., Ltd, Shinnakahara-cho, Isogu-ku, Yokohama 235, Japan; Yuichiro Asano & Hiroshi Muramoto, Showa Aluminum Corporation, lidabashi 3-6-5, Chiyoda-ku, Tokyo 102, Japan; Nobuhiro Tanatsugu, Institute of Space and Astronautical Science, Yoshinodai 3-1-1, Sagamihara-shi, Kanagawa 229, Japan. Paper number IAF-ICOSP89-4-8.
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