To provide an electrical power unit that provides electrical power to an electrical component on-board an aircraft in an emergency situation.
An electrical power unit provides electrical power to an electrical component 12 on-board an aircraft. The electrical power unit 10 includes a hydrogen generation system 16 configured to be positioned in the aircraft. The hydrogen generation system is further configured to generate hydrogen using a reaction between water and metal. The electrical power unit also includes a fuel cell 14 configured to be positioned in the aircraft. The fuel cell is operatively connected to the hydrogen generation system so that the fuel cell receives hydrogen from the hydrogen generation system. The fuel cell is further configured to generate electrical power from the hydrogen received from the hydrogen generation system and to be electrically connected to the electrical component for supplying the component with electrical power.
| JP5233148 | Solid oxide fuel cell |
| WO/1984/002283 | MEANS AND PROCEDURE FOR REMOVAL OF CARBON DIOXIDE |
| JPH03275501 | FUEL REFORMER |
JAMES ROBERT PRESLEY
RUSSELL STEPHEN DEMUTH
MING YIN
| JP2006306700A | 2006-11-09 | |||
| JP2010188329A | 2010-09-02 |
| WO2012010639A1 | 2012-01-26 |
Hirokazu Ogura
Toshihisa Kurokawa
Takuto Tanaka