Method and a system for diagnosing an aircraft from measurements performed on the aircraft
First Claim
1. A method of diagnosing an aircraft by analyzing at least one spectrum (V{right arrow over (te)}st, V{right arrow over (te)}st1, V{right arrow over (te)}st2) obtained from measurements made on the aircraft, in particular from vibration measurements, the method comprising the following successive operations:
- synchronizing a plurality of measurement time data series;
calculating a mean series of measurement time data from a plurality of synchronized measurement time data series;
transforming from the time domain to the frequency domain in order to obtain the measurement frequency data vector from the mean series of time data;
imputing the frequency data vector(s) corresponding to the spectrum (spectra) for analysis to a calculation module (23) together with at least one first reference spectrum data vector ({right arrow over (VR)}1, {right arrow over (VR)}2, {right arrow over (VR)}3, {right arrow over (VR)}4), the calculation module determining, for each input vector, a plurality of degree-of-membership vectors for the components of the input vector, specifying their respective degrees of membership to a plurality of classes, the calculation module determining a diagnosis value (Diag) as a function of the degree-of-membership vectors, and as a function of the spectrum (spectra) to be analyzed, of the reference spectrum (spectra), and of parameters (am, bm, cm, α
i,j, β
i,j, δ
i,j) determined from at least two reference spectra including said first reference spectrum.
2 Assignments
0 Petitions
Accused Products
Abstract
A method of diagnosing an aircraft by analyzing at least one spectrum obtained from measurements taken on the aircraft, in particular from vibration measurements, in which the spectrum (spectra) to be analyzed is/are input to a calculation module (23) together with at least one first reference spectrum, the calculation module determining a diagnosis value (Diag) as a function of the spectrum (spectra) to be analyzed, of the reference spectrum (spectra), and of parameters determined from at least two reference spectra including the first reference spectrum.
-
Citations
14 Claims
-
1. A method of diagnosing an aircraft by analyzing at least one spectrum (V{right arrow over (te)}st, V{right arrow over (te)}st1, V{right arrow over (te)}st2) obtained from measurements made on the aircraft, in particular from vibration measurements, the method comprising the following successive operations:
-
synchronizing a plurality of measurement time data series; calculating a mean series of measurement time data from a plurality of synchronized measurement time data series; transforming from the time domain to the frequency domain in order to obtain the measurement frequency data vector from the mean series of time data; imputing the frequency data vector(s) corresponding to the spectrum (spectra) for analysis to a calculation module (23) together with at least one first reference spectrum data vector ({right arrow over (VR)}1, {right arrow over (VR)}2, {right arrow over (VR)}3, {right arrow over (VR)}4), the calculation module determining, for each input vector, a plurality of degree-of-membership vectors for the components of the input vector, specifying their respective degrees of membership to a plurality of classes, the calculation module determining a diagnosis value (Diag) as a function of the degree-of-membership vectors, and as a function of the spectrum (spectra) to be analyzed, of the reference spectrum (spectra), and of parameters (am, bm, cm, α
i,j, β
i,j, δ
i,j) determined from at least two reference spectra including said first reference spectrum. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
-
Specification