Abstract: A method for detecting a hardware configuration of a device intended to be carried aboard an aircraft turbomachine and controlled by a two-channel protection calculator (8), comprising a power supply able to supply the device, a first measuring box (16) able to measure a first voltage Vs1 at the output of the device and a second measuring box (18) capable of measuring a second voltage Vs2 at the output of the device: a) Send a control voltage to the input of the equipment Vc; b) Measure the first voltage Vs1 and the second voltage Vs2; c) Infer the hardware configuration of the device from the values of the first and second voltages measured Vs1 and Vs2.

Abstract: The invention relates to a method for detecting a hardware configuration of an on-board device in an aircraft, capable of receiving as input a setpoint current (Ic), and of producing as output a response current (I), the method comprising the following steps: a) Send, to the input of the device, a setpoint current (Ic) at a given time (t0); b) Measure one or more values of the response current (I) at the output of the device in a measurement-time interval defined between two instants (t1 and t2) after the initial instant (t0); c) Infer the hardware configuration of the device, doing so from one or more values of the response current (I) measured.

Abstract: The invention relates to a method for detecting a hardware configuration of an on-board device in an aircraft, capable of receiving as input a setpoint current (Ic), and of producing as output a response current (I), the method comprising the following steps: a) Send, to the input of the device, a setpoint current (Ic) at a given time (t0); b) Measure one or more values of the response current (I) at the output of the device in a measurement-time interval defined between two instants (t1 and t2) after the initial instant (t0); c) Infer the hardware configuration of the device, doing so from one or more values of the response current (I) measured.

Abstract: A method for detecting a hardware configuration of a device intended to be carried aboard an aircraft turbomachine and controlled by a two-channel protection calculator (8), comprising a power supply able to supply the device, a first measuring box (16) able to measure a first voltage Vs1 at the output of the device and a second measuring box (18) capable of measuring a second voltage Vs2 at the output of the device: a) Send a control voltage to the input of the equipment Vc; b) Measure the first voltage Vs1 and the second voltage Vs2; c) Infer the hardware configuration of the device from the values of the first and second voltages measured Vs1 and Vs2.

Abstract: Electrical harness for a turbomachine, comprising a first termination connected to an apparatus (3) capable of emitting an electrical signal, and a second termination connected to a signal processing apparatus (4), characterised in that it comprises an electronic circuit for filtering the signal, said circuit comprising at least one electronic component associated with an operating temperature threshold, and one thermally triggered electrical interruption means connected in series or in parallel with said electronic component, said electrical interruption means being capable of changing from an open state in which a current cannot flow through it, to a closed state in which a current can flow through it, or reciprocally from a closed state to an open state, from a tripping temperature lower than or equal to the operating temperature threshold of said electronic component.

Abstract: A method for measuring rotation speed of an aircraft engine shaft includes: acquisition of an alternating rotation speed detection signal across terminals of a phonic wheel sensor, conversion of the alternating signal into a square signal; comparison of a plurality of previously-stored square signal period samples to lower and upper period limits, to determine valid samples of a value included between the terminals; if the number of valid samples is greater than a first threshold, determination on the basis of the valid samples of a desired period of the square signal; and at least on the condition that the number of valid samples is less than the first threshold, computation of a plurality of sums of samples, and computation of the average of a set comprising a number of valid period samples and a number of sums from among the plurality of sums of at least two samples.

Abstract: A method for measuring rotation speed of an aircraft engine shaft includes: acquisition of an alternating rotation speed detection signal across terminals of a phonic wheel sensor, conversion of the alternating signal into a square signal; comparison of a plurality of previously-stored square signal period samples to lower and upper period limits, to determine valid samples of a value included between the terminals; if the number of valid samples is greater than a first threshold, determination on the basis of the valid samples of a desired period of the square signal; and at least on the condition that the number of valid samples is less than the first threshold, computation of a plurality of sums of samples, and computation of the average of a set comprising a number of valid period samples and a number of sums from among the plurality of sums of at least two samples.

Abstract: Electrical harness for a turbomachine, comprising a first termination connected to an apparatus (3) capable of emitting an electrical signal, and a second termination connected to a signal processing apparatus (4), characterised in that it comprises an electronic circuit for filtering the signal, said circuit comprising at least one electronic component associated with an operating temperature threshold, and one thermally triggered electrical interruption means connected in series or in parallel with said electronic component, said electrical interruption means being capable of changing from an open state in which a current cannot flow through it, to a closed state in which a current can flow through it, or reciprocally from a closed state to an open state, from a tripping temperature lower than or equal to the operating temperature threshold of said electronic component.