COMPLEX PROCESS OF ACTIVELY CONTROLLING AN AIRPLANE WING VIBRATIONS UPON TURBULENCE, BASED ON AN EMERGENT METHODOLOGY OF MATHEMATICAL MODEL IDENTIFICATION

The invention relates to a process for controlling airplane wing vibrations upon turbulence. According to the invention, the process determines a mathematical model of the wing, comprising the following sequence of operations: input of a temporal signal to a servo-actuator having the data of an approximate Dirac impulse within the frequency band [0 Hz; 50 Hz], which covers the range of interest of the first two frequencies of the wing; record of the temporal signal in movement provided by an accelerometer mounted onto the wing; the frequency experimental calculation associated to the transfer function, defined by the attenuation-frequency and phase-frequency characteristics; identification, within the frequency range, of an optimal approximation of the experimental response by rational transfer functions; identification, within the time range, of the matrix set which the active control laws implemented in the intelligent wing system operate with.