Metal Hydride Energy Source for HALE Aircraft Propulsion

Busek Co. Inc. and the Applied Research Laboratory (ARL) of Pennsylvania State University propose to develop a metal hydride based power system for High Altitude Long Endurance (HALE) aircraft. This system will produce mechanical or electrical energy that can be used to drive a propeller. In Phase I, we selected the most promising propellant combination and designed a system around it. We estimate a specific fuel consumption of approximately 0.35 kg/kW-h. Taking into account uncertainties, our near term performance goal will be 0.50 kg/kW-h. In the first year of Phase II, we will develop the system architecture, conduct combustion experiments, and design a heat exchanger. We will then design and build a subscale, proof-of-concept system, and test it at Busek and ARL. In the second year of Phase II, we will design, build, and test a combustor on the scale of one that would be found in an actual HALE aircraft. Integrated testing at Busek and ARL will include a turbine and alternator. We will then design, at the preliminary level, a full-scale flight system.