Patent ID: 7225062

Claim:
A device for indicating the vibration level of a helicopter including a rotor, in order to produce first and second vibration levels derived from respective first and second acceleration signals, the device comprising: first analysis means for resolving said first acceleration signal delivered by one or more sensors measuring vibration directed along the axis of the rotor into a plurality of axial analysis signals, each occupying a respective first identified frequency band; a first memory having recorded therein a plurality of axial weighting coefficients, each corresponding to one of said first identified frequency bands; a control circuit summing second powers of said axial analysis signals weighted by said axial weighting coefficients, thereby producing said first vibration level, second analysis means for resolving said second acceleration signal into a plurality of radial analysis signals, each occupying a respective second identified frequency band, said second acceleration signal being delivered by one or more sensors measuring vibration directed perpendicularly to the axis of the rotor; a second memory recording a plurality of radial weighting coefficients, each corresponding to one of said second identified frequency bands; and a second control circuit summing second powers of said radial analysis signals weighted by said radial weighting coefficients in order to produce said second vibration level.