Use of cryogenic fuel tanks for the cooling of power electronics circuits to improve cooling capabilities for power electronics in vehicles or an aircraft. The power electronics circuit can be cooled via a cryogenic cooling loop by the fuel directly, or the fuel is used to cool a separated coolant tank. A control valve controls the coolant flow within the cryogenic cooling loop based on an electrical property of the power switching element of the power electronics circuit and or based on the way the power switching elements are electrically connected together. The control valve can control the coolant flow such that a junction temperature is achieved which minimizes the drain-source resistance.

An isolator for an aircraft fuel tank configured to separate an electrically conductive internal panel of the fuel tank from an electrically conductive pipe that passes through the panel. The isolator includes: a plurality of first attachment points for attaching the isolator to the panel, a plurality of second attachment points for attaching the isolator to the pipe, and an aperture defined by an outer wall and extending from a first side of the isolator to a second side of the isolator. The aperture is configured to receive the pipe in use, wherein the isolator is formed of a non-electrically conductive material.

An isolator for an aircraft fuel tank configured to separate an electrically conductive internal panel of the fuel tank from an electrically conductive pipe that passes through the panel. The isolator includes: a plurality of first attachment points for attaching the isolator to the panel, a plurality of second attachment points for attaching the isolator to the pipe, and an aperture defined by an outer wall and extending from a first side of the isolator to a second side of the isolator. The aperture is configured to receive the pipe in use, wherein the isolator is formed of a non-electrically conductive material.

A shrouded pipe formed from inner and outer pipe sections, the inner pipe section having an outwardly projecting flange joining the outer pipe section, and the outer pipe section having an inwardly projecting flange joining the inner pipe section, an annular volume between the inner and outer pipe sections providing a secondary fluid path. The flanges control axial position of the inner pipe section. By providing one flange which extends radially outwardly and one which extends radially inwardly, assembly is possible of the shrouded pipe by inserting the inner pipe section into the outer pipe section, without modification of the outer pipe section or inner pipe section. The first and second flanges ensure no unwanted contact between the inner and outer pipe sections and, therefore, prevent damage to the primary fluid path. The first and second flanges ensure good load distribution between the inner and outer pipe sections.

A powerplant and a generator of an external auxiliary power unit (APU) are located within a nacelle that is mountable to a hardpoint of an aircraft via an associated a hardpoint attachment interface that provides for releasably coupling the external APU thereto, and provides for coupling a fuel supply of the aircraft to run the powerplant, and coupling electrical power from the external APU either to, or external of, the aircraft. The external auxiliary power unit (APU) incorporates a particulate filter in series with the inlet air flow to the powerplant.

Systems, devices, and methods are provided for a power delivery and drive system. A power delivery system can include an engine governing unit configured to deliver electrical power to a first electrical component. The power delivery system can include a smart engine electrically connected to the engine governing unit, the smart engine configured to deliver electrical power to the engine governing unit. The system can include a smart fuel tank operably connected to the smart engine and engine governing unit. And the system can include a battery operably connected to the engine governing unit, the smart battery configured to deliver electrical power to the engine governing unit.

A wing assembly with at least two ribs is disclosed. Each rib defines a rib plane and has a peripheral edge. A fluid pipe extends through each rib plane and is disposed external to the peripheral edge of each rib. The fluid pipe is coupled to each rib.

A wing assembly with at least two ribs is disclosed. Each rib defines a rib plane and has a peripheral edge. A fluid pipe extends through each rib plane and is disposed external to the peripheral edge of each rib. The fluid pipe is coupled to each rib.

Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.