A method and power distribution system for operating in a low power consumption mode includes a primary power distribution node defining a primary distribution switch having an output and operable in a first conducting mode and a second non-conducting mode, and wherein operating in the second non-conducting mode includes a leakage current through the power distribution switch, at least one enabled electrical load downstream of the primary power distribution node, the at least one enabled electrical load connectable to the primary power distribution node by way of the primary distribution switch, and a primary power distribution node power source configured to supply power to the output of the primary distribution switch when the primary distribution switch is operating in the second non-conducting mode.

A fuel cell to provide a higher power density. The fuel cell can be produced by 3D printing in ceramic and has an improved power density by virtue of its spiral shape. In order to better extract the energy generated by the fuel cell, an interconnector sheet can be fastened positively to fastening knobs of the fuel cell by holding eyes. In addition, the interconnector sheet can be fixed by glass solder.

The invention relates to an electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft engine, the architecture comprises: —a high-voltage DC propulsive electric distribution network (32), —a non-propulsive electric distribution network (56) which is connected to loads of the aircraft, and—an electric distribution network (76) which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

The invention relates to an electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft engine, the architecture comprises: —a high-voltage DC propulsive electric distribution network (32), —a non-propulsive electric distribution network (56) which is connected to loads of the aircraft, and—an electric distribution network (76) which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

A system includes a turbo pump to convert compressed gas into power, a storage tank to store the compressed gas, and a fire suppression control valve having a closed position in which the compressed gas is prevented from flowing to the cargo compartment and an open position in which the compressed gas is ported to the cargo compartment to suppress a fire. The system also includes a pump control valve having a closed position in which the compressed gas is prevented from flowing to the turbo pump and an open position in which the compressed gas is ported to the turbo pump to cause the turbo pump to convert the compressed gas into the power. The system also includes an OBIGGS to convert bleed air from a gas turbine engine into an inert gas to provide low rate discharge (LRD) fire suppression to the cargo compartment.

A system includes a turbo pump to convert compressed gas into power, a storage tank to store the compressed gas, and a fire suppression control valve having a closed position in which the compressed gas is prevented from flowing to the cargo compartment and an open position in which the compressed gas is ported to the cargo compartment to suppress a fire. The system also includes a pump control valve having a closed position in which the compressed gas is prevented from flowing to the turbo pump and an open position in which the compressed gas is ported to the turbo pump to cause the turbo pump to convert the compressed gas into the power. The system also includes an OBIGGS to convert bleed air from a gas turbine engine into an inert gas to provide low rate discharge (LRD) fire suppression to the cargo compartment.

A device for harvesting and storing triboelectric charge generated on an exterior surface of a moving vehicle is provided. It is characterised by comprising; a supercapacitor comprised of nano-carbon-containing electrodes; an ionic liquid electrolyte and at least one ion-permeable porous membrane; at least one first element exposed to aerodynamically-induced frictional forces acting thereon and on which the charge is caused to build up and connected to at least one of the electrodes of one polarity; at least one second element having a lower electrostatic potential than the charge-collecting element and connected to at least one of the electrodes of the other polarity; a voltage modification or impedance conversion circuit arranged between the first and/or second elements and the supercapacitor; means to connect the device to an operative component requiring electrical power and a controller for managing the performance of the device and switching between energy-harvesting and energy-utilisation modes. The device is especially use for deployment in the wing of an aircraft to utilised triboelectric charge generated thereon.

A device for harvesting and storing triboelectric charge generated on an exterior surface of a moving vehicle is provided. It is characterised by comprising; a supercapacitor comprised of nano-carbon-containing electrodes; an ionic liquid electrolyte and at least one ion-permeable porous membrane; at least one first element exposed to aerodynamically-induced frictional forces acting thereon and on which the charge is caused to build up and connected to at least one of the electrodes of one polarity; at least one second element having a lower electrostatic potential than the charge-collecting element and connected to at least one of the electrodes of the other polarity; a voltage modification or impedance conversion circuit arranged between the first and/or second elements and the supercapacitor; means to connect the device to an operative component requiring electrical power and a controller for managing the performance of the device and switching between energy-harvesting and energy-utilisation modes. The device is especially use for deployment in the wing of an aircraft to utilised triboelectric charge generated thereon.

The present disclosure provides a structural member for a vehicle. The structural member comprises a plurality of finned spar members interlocked with one another, wherein each of the finned spar members include a main body, a plurality of web members extending from a flange, a circuit board formed on the main body, and a bus bar formed on the main body, wherein a compartment is formed between adjacent web members, each compartment being sized to receive a battery.

The present disclosure provides a structural member for a vehicle. The structural member comprises a plurality of finned spar members interlocked with one another, wherein each of the finned spar members include a main body, a plurality of web members extending from a flange, a circuit board formed on the main body, and a bus bar formed on the main body, wherein a compartment is formed between adjacent web members, each compartment being sized to receive a battery.