Abstract: An aircraft turbomachine calculator including a parallelepiped metal casing including an electronic circuit wherein a control channel and a monitoring channel are integrated. The casing includes a first cavity wherein a first electronic board is provided for managing the control channel and a second cavity, independent of the first cavity, wherein a second electronic board is provided for managing the monitoring channel, these electronic boards being provided in two planes oriented with respect to each other at an angle of 90°.

Abstract: A device protecting an aircraft turbomachine computer against speed measurement errors, including: on a speed regulation channel: a speed sensor of a turbomachine gearbox shaft, a speed measurement circuit, and a speed regulation circuit; on a monitoring channel: a speed sensor of a turbomachine gas generator shaft, a speed measurement circuit, and a turbomachine stop control circuit. Each channel uses dissimilar characteristics eliminating common mode errors. Each speed sensor delivers a pseudo-sine frequency signal. On each channel, speed monitoring circuits compare the frequency signal with a minimum threshold, delivering an error signal when the measured frequency is lower than the minimum threshold. A common speed cross checking circuit detects exceeding a determined deviation between both frequencies, the monitored deviation being higher or lower than a maximum deviation corresponding to loss of a frequency period on either sensor.

Abstract: The invention relates to a starting device for an auxiliary power unit (10), comprising a control unit (32) of the power supply of a starter motor (12), said motor (12) being suitable to be supplied with power by a supply network (16) and configured to drive a revolution of the auxiliary power unit (10), the control unit (32) being suitable to receive an item of information representative of the speed of rotation of the auxiliary power unit (10) and control of the power supply of the starter motor (12) by the control unit (32) being dependent on said item of information representative of the speed of rotation. The device is characterised in that the control unit (32) is suitable to receive an item of information representative of the voltage of the power supply network (16) and in that control of the power supply of the starter motor (12) by the control unit (32) is dependent on said item of information representative of the voltage.

Abstract: A device protecting an aircraft turbomachine computer against speed measurement errors, including: on a speed regulation channel: a speed sensor of a turbomachine gearbox shaft, a speed measurement circuit, and a speed regulation circuit; on a monitoring channel: a speed sensor of a turbomachine gas generator shaft, a speed measurement circuit, and a turbomachine stop control circuit. Each channel uses dissimilar characteristics eliminating common mode errors. Each speed sensor delivers a pseudo-sine frequency signal. On each channel, speed monitoring circuits compare the frequency signal with a minimum threshold, delivering an error signal when the measured frequency is lower than the minimum threshold. A common speed cross checking circuit detects exceeding a determined deviation between both frequencies, the monitored deviation being higher or lower than a maximum deviation corresponding to loss of a frequency period on either sensor.

Abstract: An aircraft turbomachine calculator including a parallelepiped metal casing including an electronic circuit wherein a control channel and a monitoring channel are integrated. The casing includes a first cavity wherein a first electronic board is provided for managing the control channel and a second cavity, independent of the first cavity, wherein a second electronic board is provided for managing the monitoring channel, these electronic boards being provided in two planes oriented with respect to each other at an angle of 90°.