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.

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.

A clamping assembly for supporting a tubular object accessing a through-hole in a panel includes a clamp and a retainer configured to be positioned at least partially around the tubular object on a first side and a second side, respectively, of the through-hole. The clamp and retainer respectively include at least one clamp lock mechanism and at least one retainer lock mechanism configured to move between a respective open position and a respective closed position. The clamp includes at least one clamp hook configured to engage with the at least one retainer hole in the retainer in a snap-fit relation when the clamp and the retainer are in the respective closed position at the first side and second side, respectively, of the through-hole. A method of supporting a tubular object and an aircraft having the clamping assembly are also disclosed.

A measurement device for measurement of liquid contained in a tank, particularly a fuel tank on an aircraft or boat. The device has a first pressure sensor for mounting outside the tank, on a liquid outlet pipe connected to the tank to measure the pressure of liquid in the outlet pipe. A second pressure sensor measures the pressure in the ullage space above liquid in the tank. A venturi flow meter mounted in the outlet pipe measures liquid flow through the outlet pipe. The device also includes an accelerometer. The quantity of liquid in the tank can be calculated in response to measured values received from the pressure sensors, the accelerometer and the venturi.

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.

An aircraft fluid line coupling assembly includes: an inner tube; an outer tube assembly having an outer tube, the inner tube extending into the outer tube, and having first connector element of a twist-to-connect joint disposed on a front end of the outer tube; a retention member having second connector element of the twist-to-connect joint, the first and the second connector elements being detachably mated to releasably interconnect the retention member and the outer tube with each other, the retention member being arranged outwardly around a longitudinal portion the inner tube so as to prevent detachment of the inner tube from the outer tube when the twist-to-connect joint is in a connected position, and so as to allow detachment of the inner tube from the outer tube when the twist-to-connect joint is in an unconnected position; and a locking mechanism for locking the twist-to-connect joint.

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 apparatus comprising a sleeve that comprises a tubular portion, a receiving portion, and a coupling portion. The tubular portion has an outer diameter that is substantially equal to an inner diameter of a flexible hose such that the tubular portion is capable of being inserted within the flexible hose. The receiving portion extends outward from the tubular portion to thereby define a channel between the receiving portion and the tubular portion for receiving an end portion of a flexible hose. The coupling portion is for coupling the sleeve, and thereby, the flexible hose, to a component.