In addition, the functional test was carried out on the condition that the temperature of the cell stack was changed covering the range of 80 ± 2 °C, and the temperature of the condenser was changed covering the range of 70.5 ± 1.5 °C. It was noticed in this functional test results that the terminal voltage was stable within the above range of the operating condition except that the terminal voltage dropped at a temperature of the cell stack of 78 °C and a temperature of the condenser of 72 °C. Finally, the results of the intermittent mission duty test during a cumulative time of 86 h showed that the test bed operated satisfactorily, and the terminal voltage was almost stable. The prospect for developing the alkaline-matrix-type fuel cell system is bright. In the future, it will be necessary that a compact flight type fuel cell system be developed after several components are developed in accordance with the decided specifications of the flight-type fuel cell system. 5. REFERENCE 1. Ken Kikuchi et al., Fundamental Study of Fuel Cell System for Space Vehicle, Space Solar Power Review 5(2), 179-188, 1985.
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