The invention relates to a power production system (200a) for an aircraft and the aircraft. The power production system comprises a fuel cell (202) powering an electric motor and having an anode (202a) and a cathode (202b), a first supply duct (206a) between the anode (202a) and a hydrogen source (204), a compressor (224), a second supply duct (222a) between an inlet of the compressor (224) and anoxygen source (210), a first transfer duct (236) between the outlet of the compressor (224) and the cathode (202b), a valve (282), an upstream duct (280a) between the outlet of the compressor and thevalve (282), a downstream duct (280b) between the valve (282) and an air outlet (252), and a control unit controlling the position of the valve and the flow rate of the compressor. Thus, the power production system provides better control of the air flow supplied to the fuel cell based on the electrical power required to provide the propelled electric motor.

    本发明涉及一种用于飞行器的电力生产系统(200a)和飞行器,所述电力生产系统包括:对电动马达供电且具有阳极(202a)和阴极(202b)的燃料电池(202),在所述阳极(202a)与氢源(204)之间的第一供给管道(206a),压缩机(224),在所述压缩机(224)的入口与氧源(210)之间的第二供给管道(222a),在所述压缩机(224)的出口与所述阴极(202b)之间的第一传递管道(236),阀(282),在所述压缩机的出口与所述阀(282)之间的上游管道(280a),在所述阀(282)与空气出口(252)之间的下游管道(280b),以及控制所述阀的位置和所述压缩机的流量的控制单元。因此,这种电力生产系统基于提供推进的电动马达所需的电功率来提供对供应给燃料电池的空气流的更好的控制。


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    Title :

    Power generation system for aircraft and aircraft


    Author / Creator :

    Type of media :

    Patent


    Type of material :

    Electronic Resource



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