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SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS

A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 44, ISSUE 8 - April 21, 2006

NASA STAR REPORTS: 04/21/06
Aeronautics

02 Aerodynamics

03 Air Transportation and Safety

04 Aircraft Communication and Navigation

05 Aircraft Design, Testing and Performance

07 Aircraft Propulsion and Power

08 Aircraft Stability and Control

08 AIRCRAFT STABILITY AND CONTROL
Includes flight dynamics, aircraft handling qualities, piloting, flight controls, and autopilots.

For related information see also 05 Aircraft Design, Testing and Performance; and 06 Avionics and Aircraft Instrumentation.


20060010457 NASA Langley Research Center, Hampton, VA, USA

Exploratory Studies in Generalized Predictive Control for Active Gust Load Alleviation

Kvaternik, Raymond G.; Eure, Kenneth W.; Juang, Jer-Nan; April 2006; 106 pp.; In English; Original contains colorillustrationsContract(s)/Grant(s): WU 561581.02.08.07Report No.(s): NASA/TM-2006-214296; L-19224; No Copyright; Avail.: CASI: A06, Hardcopy

The results of numerical simulations aimed at assessing the efficacy of Generalized Predictive Control (GPC) for activegust load alleviation using trailing- and leading-edge control surfaces are presented. The equations underlying the method arepresented and discussed, including system identification, calculation of control law matrices, and calculation of commandsapplied to the control effectors. Both embedded and explicit feedforward paths for inclusion of disturbance effects areaddressed. Results from two types of simulations are shown. The first used a 3-DOF math model of a mass-spring-dashpotsystem subject to user-defined external disturbances. The second used open-loop data from a wind-tunnel test in which a wingmodel was excited by sinusoidal vertical gusts; closed-loop behavior was simulated in post-test calculations. Results obtainedfrom these simulations have been decidedly positive. In particular, results of closed-loop simulations for the wing modelshowed reductions in root moments by factors as high as 1000, depending on whether the excitation is from a constant- orvariable-frequency gust and on the direction of the response.Author

Gust Loads; Wind Tunnel Tests; Adaptive Control; Mathematical Models; Predictions

Source: NASA


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