The identification of control surface limit cycle oscillations (LCO) is a topic with deep impact on the aircraft development. Recently this subject has received strong demand of studies due to indications of aircraft certification agencies that LCO prediction techniques may be required soon. In this context, in this research the Equivalent Linearization approach is studied to identify LCOs on the flight envelope due to symmetrical and asymmetrical freeplay. It is considered the two degrees of freedom typical section as the aeroelastic model with steady aerodynamic force and aerodynamic. The LCO frequency and amplitude are obtained using a describing function for each freeplay. The proposal includes a detailed discussion on the asymmetrical freeplay which is the more common situation in engineering real application.
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