Patent ID: 7363120

Claim:
A method of adjusting at least one defective main or anti-torque rotor ( 6 , 10 ) of a particular rotorcraft, comprising the steps of: using a neural network that represents relationships between firstly accelerations representative of a vibration generated on at least a portion of a reference rotorcraft and secondly rotor defects and adjustment parameters, wherein each adjustment parameter is with respect to adjusting an element that affects the generated vibration; determining any defects of said rotor, wherein each one of said determined defects relates to a corresponding element that generated the vibration; determining an adjustment value α for at least one of said adjustment parameters by minimizing the following relationship: ∑ c ⁢ ⁢ λ c ⁢ ∑ a ⁢ ⁢ λ a ⁢ ( ∑ h = 1 B - 2 ⁢ ⁢ ( λ h ⁢  R c , a , h ⁡ ( α ) + γ c , a , h  2 ) + λ B - 1 (  R c , a , B - 1 ⁡ ( α ) + γ c , a , B - 1  2  γ c , a , B  ) 2 ) in which: γ c , γ a , γ h , and γ B−1 are weighting coefficients depending respectively on the stage of flight c, an accelerometer a, harmonics h, and the number of blades B of the rotor minus one; R c,a,h is an output cell of the neural network corresponding to the harmonic h, the accelerometer a, and the stage of flight c; R c,a,B−1 is an output cell of the neural network corresponding to the harmonic B−1, the accelerometer a, and the stage of flight c; γ c,a,h is an acceleration signal at the frequency h measured by the accelerometer a for the stage of flight c; γ c,a,B is an acceleration signal at the frequency B measured by the accelerometer a for the stage of flight c; and γ c,a,B−1 is an acceleration signal at the frequency (B−1) measured by the accelerometer a for the stage of flight c; and based on the determined adjustment value, making an adjustment of at least one element to reduce the generated vibration.