flux models in an analysis of the complex geometric configuration. In addition, the analysis will be used to define particle size for verification testing. Some limited test results from hypervelocity testing performed at NASA-JSC are also discussed. (Paper number IAF-ICOSP89-4-7.) 4-8. Development of Deployable Film Type Radiator Masahito Oguma', Shintaro Enya', Yuichiro Asano2, Hiroshi Muramoto2 & Nobuhiro Tanatsugu2 ‘Ishikawajima-Harima Heavy Industries Co. Ltd., Research Institute, 1 Shin-nakahara-cho, Isogo-ku, Yokohama 235, Japan; 2Syowa Aluminum Corp., 6-5 lidabashi, 3-chome, Chiyoda-ku, Tokyo 102, Japan; 'Institute of Space and Astronautical Science, Yoshinodai 3-1-1, Sagamihara- shi, Kanagawa 229, Japan. In this paper, we describe the deployable film type radiator, which is lighter and has a smaller package volume than the ordinary radiator. The space environment is rapidly becoming an object of business. For example, there are many medical or engineering experiment plans using the space station or the free flyer. Considering the above-mentioned background, we can predict the rapid increase of energy used in space and the deployment area of radiators will be increased rapidly too. So, the radiator whose weight and package volume are smaller than ordinary radiators, will be needed. We propose the deployable film type radiator which is lighter and has smaller package volume. The deployable film type radiator which is a liquid fluid type, is deployed in space at the start of cooling the mission devices. The radiator is made by means of roll-bonding, and the radiator's thickness is less than 0.6 mm. The part which will not be bonded, becomes the fluid channel so that we are able to decide the channel formation at will. These characteristics result in the simple optimum channel formation for the radiator. This radiator is thin so that the minimum roll-diameter is about 100 mm. The radiator surface has a coating which reflects sunlight and emits infrared rays, and this coating endures deployment of the radiator. The absorptivity for sunlight is 0.16 and emissivity is 0.8. Comparing this deployable film type radiator with the ordinary liquid fluid or heat pipe radiator, the ordinary radiator is about 20 times as heavy as the deployable film type radiator and needs 25 times the package volume. The cooling system with the deployable film type radiator is composed of a pump, a coolant tank and a radiator. Before cooling the mission devices, there is a coolant in the tank so that coolant freezing is difficult. At the start of cooling, the piston in the tank which is moved by the compressive air, pushes the coolant, and the radiator spreads out. We predict the thermal characteristics by numerical simulation. And we fabricate the radiator whose efficiency is 80% to the design on the thermal experiment. (Paper number IAF-ICOSP89-4-8.) 4-9. Solar Thermal Power Systems for Space and Terrestrial Applications: Similar Research Challenges U. Sprengel' & A. Fritzsche2 ■DLR, Stuttgart, FRG; 'Dornier GmbH, Friedrichshafen, FRG The present state of research restricts the physical and technical variations of energy supply in space to photovoltaic, solar thermal and nuclear systems. Energy storage problems connect the development of solar thermal and photovoltaic, the heat engine that of solar thermal and nuclear energy conversion. A similar keystone function hold the components of thermal energy utilization. Recent progress in efficiency and decrease in cost of electricity of solar thermal plants suggest more than a joint view. Mainly for budgetary reasons there is a strong challenge
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