K. Fujii, H. Matsushita, Y. Miyazawa

A synthesis method to obtain gust load alleviation control laws which also provide flutter margin augmentation is presented. A scaled transport aircraft model, utilizing high aspect-ratio wings with aeroelastic similarity, was designed and constructed for wind tunnel tests. The models fuselage and tail were constructed to be rigid, and it was equipped with ailerons and an elevator. A mathematical model was derived in a state space form and was tuned to be consistent with ground vibration and wind tunnel test results. A linear quadratic Gaussian (LQG) optimal control synthesis method incorporating order reduction was then applied to this math model. The minimized cost function was equivalent to the models kinetic energy, and was effective for both gust load alleviation and flutter suppression. Control laws were subsequently obtained which can be applied not only for gust load alleviation, but also for flutter suppression. Several derived control laws were subsequently verified in wind tunnel tests.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 7 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.474-480; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991