A power electronics unit for an aircraft and a method of determining the integrity of a power electronics unit are provided. The power electronics unit comprises an electric machine controller; a heatsink arranged to conduct heat from the electric machine controller; a housing comprising a sealed internal volume enclosing the electric machine controller and heatsink; a dielectric liquid partially filling the internal volume to cover the electric machine controller; a gas pocket within the internal volume; a pressure sensor arranged to measure a pressure of gas within the gas pocket; a temperature sensor arranged to measure a temperature within the internal volume; and a controller. The controller is configured to receive signals from the pressure sensor and temperature sensor, determine a pressure and temperature from the received signals and provide an output signal dependent on the determined temperature and pressure.

A converter station for the transmission of electrical power has a diode rectifier with a DC terminal and an AC terminal. At least one transformer is connected to the AC terminal. In order to render the converter station as compact as possible, the diode rectifier is arranged in an insulating material.

An electrical feed-through, such as a PCB connector, involves at least one positioning protrusion protruding from a main body, and may further include multiple positioning protrusions protruding in respective directions from the main body. A data storage device employing such a feed-through comprises an enclosure base with which the feed-through is coupled, where the base comprises an annular recessed surface surrounding an aperture that is encompassed by the feed-through and is at a first level, and at least one recessed positioning surface at a higher level than the first level and extending in a direction away from the annular recessed surface. The positioning protrusion of the electrical feed-through physically mates with the recessed positioning surface of the base, such that the position of the feed-through is vertically constrained by the recessed positioning surface.

An electrical feed-through, such as a PCB connector, involves at least one positioning protrusion protruding from a main body, and may further include multiple positioning protrusions protruding in respective directions from the main body. A data storage device employing such a feed-through includes an enclosure base with which the feed-through is coupled. The base includes an annular recessed surface surrounding an aperture that is encompassed by the feed-through and is at a first level, and at least one recessed positioning surface at a higher level than the first level, and extending in a direction away from the annular recessed surface. The positioning protrusion of the electrical feed-through contacts the recessed positioning surface of the base, such that the position of the feed-through is constrained by the recessed positioning surface.

Tamper-proof electronic packages and fabrication methods are provided including an enclosure enclosing, at least in part, at least one electronic component within a secure volume, a two-phase dielectric fluid within the secure volume, and a tamper-respondent detector. The tamper-respondent detector monitors, at least in part, temperature and pressure of the two-phase dielectric fluid. In operation, the two-phase dielectric fluid deviates from an established saturation line of the two-phase dielectric fluid within the secure volume with an intrusion event into the secure volume, and the tamper-respondent detector detects, from the monitoring of the temperature and pressure of the two-phase dielectric fluid, the deviation from the established saturation line, and thereby occurrence of the intrusion event.

An enclosure for an electronic system that is configured to act as a heat exchanger to remove heat from a cooling liquid that is circulated through the electronic system for cooling the electronic components thereof which are submerged in the cooling liquid in direct contact therewith. The enclosure uses an arrangement of a combination of external fins on one or more walls and fluid passages formed in one or more of the walls through which the cooling liquid is circulated for cooling. The fluid passages and the external fins are preferably formed on the same wall. The fins and the fluid passages can be formed on any number of walls of the enclosure.

A heat exchanging arrangement for a subsea electronic system, the heat exchanging arrangement including a wall section; a corrugation formed in the wall section, the corrugation having two generally opposing internal corrugation surfaces; and at least one heat exchanging element forced against at least one of the internal corrugation surfaces. A subsea electronic system including a heat exchanging arrangement is also provided.

A method for estimating the remaining useful life of a pressure compensator of a subsea arrangement, the method including determining displacement data related to displacements of the pressure compensator during a time period; and estimating the remaining useful life of the pressure compensator in relation to a failure mode of the pressure compensator based on the determined displacement data of the pressure compensator. A system including a subsea arrangement and a control system, a computer program product, and a computer program, are also provided.

An enclosure for an electronic system that is configured to act as a heat exchanger to remove heat from a cooling liquid that is circulated through the electronic system for cooling the electronic components thereof which are submerged in the cooling liquid in direct contact therewith. The enclosure uses an arrangement of a combination of external fins on one or more walls and fluid passages formed in one or more of the walls through which the cooling liquid is circulated for cooling. The fluid passages and the external fins are preferably formed on the same wall. The fins and the fluid passages can be formed on any number of walls of the enclosure.

A power electronics unit for an aircraft and a method of determining the integrity of a power electronics unit are provided. The power electronics unit comprises an electric machine controller; a heatsink arranged to conduct heat from the electric machine controller; a housing comprising a sealed internal volume enclosing the electric machine controller and heatsink; a dielectric liquid partially filling the internal volume to cover the electric machine controller; a gas pocket within the internal volume; a pressure sensor arranged to measure a pressure of gas within the gas pocket; a temperature sensor arranged to measure a temperature within the internal volume; and a controller. The controller is configured to receive signals from the pressure sensor and temperature sensor, determine a pressure and temperature from the received signals and provide an output signal dependent on the determined temperature and pressure.