Limit Cycle Oscillations of a Complete Aircraft
نویسندگان
چکیده
This paper presents results for the aeroelastic stability and LCO behavior for a complete aircraft. Comparison are presented between the results predicted by a cantilevered wing model, an untrimmed aircraft model (no gravity or drag) and a trimmed aircraft model. It is seen that the stability behavior is predicted accurately only if the correct trim loads are applied to the wing. The LCO behavior of the untrimmed aircraft was similar to that of the cantilevered wing. On the other hand, the LCO behavior of the trimmed aircraft configuration was complicated due to the presence of flight dynamic instabilities.
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