Abstract: A solid state storage system includes a pressure-sealed storage unit defining an interior and having an outlet, an upper manifold and a lower manifold separated by a dividing plane having a set of ports, a set of chambers, and a solid state storage, wherein at least some gas is supplied to the outlet.

Abstract: A solid hydrogen reaction system and method of liberating hydrogen gas includes the utilization of a reactor having a body that defines a reaction chamber, having a first narrow end and a second wider end such that the reactor has an increasing cross-sectional area from the first end toward the second end, for facilitating a reaction to liberate hydrogen gas stored in a hydrogen storage solid located within the reaction chamber.

Abstract: A battery pack for carrying one or more battery cells in the battery pack can include a chassis defining a body for holding the battery cells. The chassis can include a set of vertical battery cell holders adapted to hold the battery cells. A set of horizontal passages can be provided in the chassis between the set of vertical battery cell holders. A cap assembly can be provided at one end of the battery cells and within the body providing venting for the battery cells through the battery cell holders.

Abstract: A hydrogen storage system includes a pressure-sealed storage unit defining an interior and having an outlet, an upper manifold and a lower manifold separated by a dividing plane having a set of ports, a set of chambers, and a hydrogen storage, wherein at least some hydrogen gas is supplied to the outlet.

Abstract: In one aspect, there is disclosed a cell stack which can include cell modules connected in series to generate a stack operating voltage. The cell modules can include a battery cell in series with a series switch and include a shunt switch connected in parallel to the battery cell and the series switch. A stack monitor circuit can have a series control coupled to the series switch, a shunt control coupled to the shunt switch, and a battery cell monitor coupled to the battery cell for measuring a cell parameter from each cell module. Based on the measured cell parameter, the stack monitor circuit can select at least one cell module either to contribute to the stack operating voltage by closing the series switch and opening the shunt switch or to bypass the stack operating voltage by the opening the series switch and closing the shunt switch.

Abstract: A hydrogen storage system includes a pressure-sealed sleeve defining an interior and having an outlet, a shaft extending through the interior of the sleeve, a set of porous chambers arranged axially along and concentric to the shaft, and a hydrogen storage, wherein at least some hydrogen gas is supplied to the outlet.

Abstract: A method and system (60) for generating emergency power includes a hydrogen storage system (62) configured to supply hydrogen gas, an air delivery system (64) configured to supply air at a predetermined temperature, and a fuel cell system (66) coupled with the hydrogen storage system and the air delivery system and configured to generate power at a power output from a chemical reaction involving the hydrogen gas and the air at the predetermined temperature.

Abstract: An auxiliary power unit and a method for providing electricity to an aircraft with the auxiliary power unit where the auxiliary power unit includes a turbine with a compressor and an output shaft. A combustor coupled to the turbine and to a fuel source, and a solid oxide fuel cell coupled to the combustor, the compressor and to the fuel source.

Abstract: Systems and methods for providing power to one or more loads on an aircraft are provided. A power system for an aircraft can include a first fuel cell configured to provide base power to one or more loads on the aircraft. The power system can further include a second fuel cell configured to provide peak power to the one or more loads on the aircraft. The peak power can be a power exceeding the base power. The power system can further include an energy storage device configured to provide transient power to the one or more loads on the aircraft. The transient power can be a power exceeding the peak power. The power system can further include a controller configured to control delivery of power from the first fuel cell, the second fuel cell, and the energy storage device to the one or more loads on the aircraft.

Abstract: A system for aircraft power distribution (100) includes a source of energy (112) to deliver an input power; a bus contactor (122); a set of switches (130) connected between the bus contactor and a set of essential and non-essential devices (132); a current analysis component (315) to determine a power level drawn from the source of current by the set of essential and non-essential devices (132); a variation reduction component (317) to determine an energization schedule of the set of essential and non-essential devices (132) based on reducing temporal variation in the input power drawn from the source of energy (112) to the bus contactor (122); and a switch control component (319) configured to adjust the set of switches (130) according to the energization schedule. If too much power is drawn, the set of switches (130) will be configured such as not to exceed the maximum power rating of the source (112).

Abstract: In one aspect, there is disclosed a taxi vehicle comprising a chassis having a coupler to connect to a coupling location of a craft and a set of wheels with at least one electric motor coupled to the set of wheels. The taxi vehicle can include a fuel cell coupled to the at least one electric motor and a battery coupled to the fuel cell. The battery can be configured to supply peak power demand to the at least one electric motor to start moving the craft. The battery can receive charging from the fuel cell when not supplying peak power demand while the fuel cell supplies power to the at least one electric motor to continue moving the craft.

Abstract: A power source for an aircraft including a solid oxide fuel cell and a solid oxide fuel cell along with a solid oxide fuel cell multi-power source. At least one battery is electrically coupled to the solid oxide fuel cell, the solid oxide fuel cell, and an aircraft distribution network to supply electricity to the aircraft and also for becoming recharged by the solid oxide fuel cell and the solid oxide fuel cell.

Abstract: A solid hydrogen reaction system and method of liberating hydrogen gas includes the utilization of a reactor having a body that defines a reaction chamber, having a first narrow end and a second wider end such that the reactor has an increasing cross-sectional area from the first end toward the second end, for facilitating a reaction to liberate hydrogen gas stored in a hydrogen storage solid located within the reaction chamber.