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Response Characteristics of a Linear Rotorcraft Vibration Model (1982)

Kunz, Donald L.

In: CASI

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Publication Date: 2019-07-13

Description: A fully coupled vibration model, consisting of a rotor with only flapping degrees of freedom plus pylon and fuselage pitching motion, was used in a parametric study undertaken to investigate the response characteristics of a simplified helicopter. Among the parameters studied were uncoupled body frequency, blade stiffness, hinge offset, advance ratio, and mast height. Results from the harmonic balance solution of the equations of motion show how each of these quantities affects the response of the model. The results also indicate that there is a potential for reducing vibration response through the judicious definition of the design parameters.

Keywords: Aircraft Stability and Control

Type: AIAA Paper 81-0616R , Dynamics Specialists Conference; Apr 09, 1981 - Apr 10, 1981; Atlanta, GA; United States|Journal of Aircraft; 19; 4; 297-303

Format: text

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