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 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 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 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: A method and apparatus for operating a power system architecture including an electrical power storage system, a power distribution bus selectively connected with the electrical power storage device, a hydraulic pump selectively connected with the electrical power storage device and a controller module communicatively connected with the electrical power storage system and the hydraulic pump.

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 power source for an aircraft including a solid oxide fuel cell and a proton exchange membrane 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 proton exchange membrane 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 proton exchange membrane fuel cell.

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 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: 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: A method and apparatus for operating a power system architecture including an electrical power storage system, a power distribution bus selectively connected with the electrical power storage device, a hydraulic pump selectively connected with the electrical power storage device and a controller module communicatively connected with the electrical power storage system and the hydraulic pump.

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: An electrical generator provides an output at a main stator winding which is excited by a main rotor winding. The main rotor winding is connected via a rectifier to a main exciter rotor winding which is excited by a main exciter field winding. A control circuit controls excitation of the main exciter field winding so as to stabilise the generator output voltage. The control circuit includes a detector for detecting excessive generator output voltage and a transistor switch for connecting a resistor in the current recirculation path of the main exciter field winding so as to prevent transient over-voltages caused by sudden load reductions.