Analysis of the steady state effects of the control surface nonlinearitiesan the performance of a fighter aircraft

Citation
Ag. Sreenatha et Sk. Nayak, Analysis of the steady state effects of the control surface nonlinearitiesan the performance of a fighter aircraft, J VIB CONTR, 6(6), 2000, pp. 923-935
Citations number
6
Language
INGLESE
art.tipo
Article
Categorie Soggetti
Mechanical Engineering
Journal title
JOURNAL OF VIBRATION AND CONTROL
ISSN journal
1077-5463 → ACNP
Volume
6
Issue
6
Year of publication
2000
Pages
923 - 935
Database
ISI
SICI code
1077-5463(200009)6:6<923:AOTSSE>2.0.ZU;2-R
Abstract
The nonlinearities present in the control surface of an aircraft can alter both the stability and performance characteristics. The typical nonlinearit ies generally considered are the "saturation" and the "dead band." The pres ent work shows that these can lead to loss of steady-state accuracy. A simp le formulation in terms of the eigenvalue problem is presented to predict t he steady-state behavior. Analytical and numerical results for a fighter ai rcraft model are presented to demonstrate the utility of the methodology de veloped.