Piloting sensor device intended for a rotary wing aircraft, comprising - GNSS reception means (11, 12, 13, 14) for constellations of at least two independent GNSS systems (100, 200, 300, 400), said GNSS reception means (11, 12, 13, 14) receiving initial signals from a plurality of satellites (101, 102, 201, 202, 301, 302, 401, 402), - at least one fault detection and exclusion module FDE (21, 22, 31), characterised in that - each fault detection and exclusion module FDE (21, 22, 31, 41) receives at least two input signals and provides an output signal, each output signal comprising a measurement and a state of integrity, - each GNSS reception means (11, 12, 13, 14) comprises a first fault detection and exclusion module FDE1 (21, 22), - each first fault detection and exclusion module FDE1 (21, 22) receives and analyses said initial signals and detects initial signals of integrity and/or incorrect initial signals, - each GNSS reception means (11, 12, 13, 14) provides a measurement and a state of integrity of a first ground speed signal of said aircraft, in a geographical coordinate system, for at least one GNSS system (100, 200, 300, 400), on the basis of said initial signals of integrity and, excluding, if necessary said incorrect initials signals, - said piloting sensor device comprises at least one second fault detection and exclusion module FDE2, each second fault detection and exclusion module FDE2 being in communication with at least two of said GNSS reception means (11, 12, 13, 14) and receiving, analysing and comparing said first ground speed signals provided by said at least two GNSS reception means (11, 12, 13, 14), detecting first ground speed signals of integrity and/or incorrect first ground speed signals, each second fault detection and exclusion module FDE2 then being able to detect and exclude each faulty GNSS system (100, 200, 300, 400) that is providing an incorrect ground speed signal, and to then determine and provide, if necessary, a measurement and a state of integrity of a second ground speed signal of said aircraft from at least two first ground speed signals of integrity. - GNSS reception means (11, 12, 13, 14) for constellations of at least two independent GNSS systems (100, 200, 300, 400), said GNSS reception means (11, 12, 13, 14) receiving initial signals from a plurality of satellites (101, 102, 201, 202, 301, 302, 401, 402), - at least one fault detection and exclusion module FDE (21, 22, 31), - each fault detection and exclusion module FDE (21, 22, 31, 41) receives at least two input signals and provides an output signal, each output signal comprising a measurement and a state of integrity, - each GNSS reception means (11, 12, 13, 14) comprises a first fault detection and exclusion module FDE1 (21, 22), - each first fault detection and exclusion module FDE1 (21, 22) receives and analyses said initial signals and detects initial signals of integrity and/or incorrect initial signals, - each GNSS reception means (11, 12, 13, 14) provides a measurement and a state of integrity of a first ground speed signal of said aircraft, in a geographical coordinate system, for at least one GNSS system (100, 200, 300, 400), on the basis of said initial signals of integrity and, excluding, if necessary said incorrect initials signals, - said piloting sensor device comprises at least one second fault detection and exclusion module FDE2, each second fault detection and exclusion module FDE2 being in communication with at least two of said GNSS reception means (11, 12, 13, 14) and receiving, analysing and comparing said first ground speed signals provided by said at least two GNSS reception means (11, 12, 13, 14), detecting first ground speed signals of integrity and/or incorrect first ground speed signals, each second fault detection and exclusion module FDE2 then being able to detect and exclude each faulty GNSS system (100, 200, 300, 400) that is providing an incorrect ground speed signal, and to then determine and provide, if necessary, a measurement and a state of integrity of a second ground speed signal of said aircraft from at least two first ground speed signals of integrity.