Conceptual Design of a Solar Dynamic Power Generation System for a Space Experiment NOBUHIRO TANATSUGU & YUTAKA MOMOSE Summary This paper presents an outline of a conceptual design of a small solar power generation system for a space experiment using a Stirling engine as a thermodynamic power converter. This system produces 3 kWe of rated electric power continuously in low Earth orbit. This power plant has the following two features. (1) It employs a thermal energy storage system on the hot side of a Stirling engine in order to work continuously in the course of eclipse as well as insolation. Latent heat of molten LiF is utilized for thermal energy storage. (2) The Stirling engine consists of one displacer driven by an electric motor and two free power pistons moving in the opposite direction from each other. This leads to a reduction of weight, size and vibration. A preliminary study of the LiF unit and the linear induction generator have been almost completed. A protomodel of the Stirling engine generator was integrated in 1987 and tested from 1988. Experiment in orbit is scheduled for 1994 using the Space Flyer Unit. Introduction The Japanese Experiment Module (JEM) attached to the US space station and the unmanned Space Flyer Unit (SFU) are planned to be in operation by the mid-1990s. In such space activities, a larger amount of electric power will be required for both housekeeping and miscellaneous experiments. In a large power generation plant, more benefits come from a Solar Dynamic Power System due to its higher conversion efficiency. The higher conversion efficiency of the power plant in utilizing solar energy can reduce the area of the solar collector and therefore the orbital decay due to atmospheric drag, especially in low earth orbit. This saves reboost propellant for the space station. When more than 100 kWe is required, nuclear power plants should also be considered. The Institute of Space and Astronautical Science has a plan to experiment with a solar dynamic power system in space on the SFU. In this mission the electric power produced is supplied to the MPD thruster and the SFU is boosted to an orbit about 100 km higher. The electric power requirement for the MPD thruster experiment is 3 kWe at 330 V ac and 60 Hz in continuous operation. Nobuhiro Tanatsugu, Associate Professor, Institute of Space and Astronautical Science, 4-6-1, Komaba Meguro-Ku, Tokyo 153, Japan. Yutaka Momose, Aisin Seiki Co. Ltd, 2nd R&D Center, 80, Kowari, Minaminakane-cho, Nishio-City, Aichi Pref., Japan. A version of this paper was presented at the sixth ISAS Space Energy Symposium, 12-13 March 1987.
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