Model for Aeroelastic Response to Gust Excitation

J.D. Quenzer, A. Zongolowicz, K.A. Hinson, B. Barzgaran, E. Livne, M. Mesbahi, K. Morgansen

AIAA Scitech 2019 Forum

A wind tunnel test-bed is designed to support studies of active control of a flexible aircraft to a gust excitation. Design selection, manufacturing, and verification tests are detailed herein. The test-bed has a modular design which allows for straight forward modification of structural dynamics as desired; the nominal configuration is a half-span aircraft model with three control surfaces. The test-bed has one rigid-body mode and one structural mode within the actuator bandwidth. Wind tunnel testing is completed to verify dynamic characteristics and to validate the suitability of the apparatus for gust alleviation control law research.

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