Abstract
Weight and consumed space of the fuel cell systems are one of the most important factors limiting its utilization in electric airplanes. Possibilities of its implementation in electric airplane are frequently discussed issues. Power – mass relationship depending on installed power of the fuel cell shows, that the power/mass ratio is unsatisfactory, when powering electric motor directly from fuel cell. Configuration with high-power small-capacity battery and relatively small fuel cell is more profitable. Some calculations were done for functional prototype of the small airplane VUT 051 RAY, its take-off weight is about 600 kg and its max. power is 55 kW. There are some practical measurements on the Ballard fuel cell system presented in this paper, which can documents disputableness of its usage in airplane. Hydrogen management (hydrogen tank, cooling system, armatures etc.) still represents outstanding issue due to high volumes and weight of the whole fuel cell system. Current progress in the field of the Li-Ion accumulators, generally decreases importance of hydrogen-drive systems and focuses more attention to simply accumulator powered airplane.
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