Abstract: A monitoring apparatus may include reception logic operable to receive processing characteristic data generated during the processing of the effluent stream; segregation logic operable to segregate the processing characteristic data into contributing processing characteristic data associated with contributing periods which contribute to a condition of the at least one processing tool and non-contributing processing characteristic data associated with non-contributing periods which fail to contribute to the condition; and fault logic operable to utilise the contributing processing characteristic data and to exclude the non-contributing processing characteristic data when determining a status of the condition.

Abstract: The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising at least one synchronous starter-generator (S/G1, S/G2) intended to be coupled to an engine (Engine1) of the aircraft, at least one conversion path comprising a plurality of power converters (CVn, CV?n) associated with switching means suitable for supplying at least one charge (CAC1, CAC2, CAC3, CAC4, P1, P2) from at least one source (S/G1, S/G2, AUX S/G1, AUX S/G2, GPU1, GPU2), and at least one distribution path suitable for supplying electrical charges (CT1n, SW1n, CT2n, SW2n).

Abstract: The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising a synchronous starter-generator (ENG S/G) intended to be coupled to an aircraft engine, a rectifier (R) capable of transforming alternating voltage into direct voltage, an auxiliary synchronous starter-generator (AUX S/G) intended to be coupled to an auxiliary power group, a first, a second and a third power converter (CV1, CV2, CV3) capable of transforming direct voltage into alternating voltage or vice versa, and at least one battery (BATT).

Abstract: A monitoring apparatus may include reception logic operable to receive processing characteristic data generated during the processing of the effluent stream; segregation logic operable to segregate the processing characteristic data into contributing processing characteristic data associated with contributing periods which contribute to a condition of the at least one processing tool and non-contributing processing characteristic data associated with non-contributing periods which fail to contribute to the condition; and fault logic operable to utilise the contributing processing characteristic data and to exclude the non-contributing processing characteristic data when determining a status of the condition.

Abstract: The invention relates to a method for converting alternating current into direct current implemented by a conversion device that comprises a three-phase bridge in which at least one arm is comprised of a first switch and of a second switch mounted in series, with the method comprising a step of regulating the direct voltage output by the conversion device, characterized in that it comprises a transition step which precedes the regulation step, with the transition step comprising the formation of signals for controlling first and second switches capable of limiting the amplitude of the inrush currents when switching the conversion device to the alternative network.

Abstract: The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising a synchronous starter-generator (ENG S/G) intended to be coupled to an aircraft engine, a rectifier (R) capable of transforming alternating voltage into direct voltage, an auxiliary synchronous starter-generator (AUX S/G) intended to be coupled to an auxiliary power group, a first, a second and a third power converter (CV1, CV2, CV3) capable of transforming direct voltage into alternating voltage or vice versa, and at least one battery (BATT).

Abstract: The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising at least one synchronous starter-generator (S/G1, S/G2) intended to be coupled to an engine (Engine1) of the aircraft, at least one conversion path comprising a plurality of power converters (CVn, CV?n) associated with switching means suitable for supplying at least one charge (CAC1, CAC2, CAC3, CAC4, P1, P2) from at least one source (S/G1, S/G2, AUX S/G1, AUX S/G2, GPU1, GPU2), and at least one distribution path suitable for supplying electrical charges (CT1n, SW1n, CT2n, SW2n).

Abstract: The invention relates to a method for converting alternating current into direct current implemented by a conversion device that comprises a three-phase bridge in which at least one arm is comprised of a first switch and of a second switch mounted in series, with the method comprising a step of regulating the direct voltage output by the conversion device, characterised in that it comprises a transition step which precedes the regulation step, with the transition step comprising the formation of signals for controlling first and second switches capable of limiting the amplitude of the inrush currents when switching the conversion device to the alternative network.