from the sun. The thermal energy stored in the thermal storage system is eliminated by a forced cooling system to the radiator and the pressure energy is eliminated by purging a working fluid through a non-propulsive vent valve. The most preferable shut-down procedure is carried out in accordance with each shut-down situation. Nominal shut-down and non-emergency shut-down are performed so that the system can restart easily and so no working fluid is vented. In case of emergency shut-down and complete shut-down for system retrieval by Shuttle, all the stored energy is eliminated so the system cannot restart. Table III shows the control procedures for emergency shutdown. Conclusions We have proposed a space experiment using a solar thermodynamic power generation system (3 kWe) with a Stirling cycle engine in the second mission of the SFU in 1994. Conceptual design of the flight model for the space experiment is now in progress. We can utilize several useful technologies on the Stirling engine accumulated by the many projects which have been carried out for terrestrial use in Japan. We have to design the Stirling engine taking into consideration both the space environment and the space operation acceptable by SFU and the launch and recovery system. Lubrication, vibration and cooling of the Stirling engine and safe operation are especially important items to be considered. A protomodel of the Stirling engine was integrated in 1987 and tested from 1988. REFERENCE [1] Abe, Y. (1986) Review on Space Solar Dynamic Power System and Thermal Energy Storage, Bui. Electrotech. Lab., 50, 12, pp. 41-62.
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