Multirate Flutter Suppression System Design For The Benchmark Active Controls Technology Wing Part 2 Nasa Tm 2002 212129 National Aeronautics And Space Administration Dec 2002 PDF Download

Flight flutter-test results of the first aeroelastic research wing (ARW-1) of NASA's drones for aerodynamic and structural testing program are presented. The flight-test operation and the implementation of the active flutter-suppression system are described as well as the software techniques used to obtain real-time damping estimates and the actual flutter testing procedure. Real-time analysis of fast-frequency aileron excitation sweeps provided reliable damping estimates. The open-loop flutter boundary was well defined at two altitudes; a maximum Mach number of 0.91 was obtained. Both open-loop and closed-loop data were of exceptionally high quality. Although the flutter-suppression system provided augmented damping at speeds below the flutter boundary, an error in the implementation of the system resulted in the system being less stable than predicted. The vehicle encountered system-on flutter shortly after crossing the open-loop flutter boundary on the third flight and was lost. The aircraft was rebuilt. Changes made in real-time test techniques are included. Gilyard, G. B. and Edwards, J. W. Armstrong Flight Research Center; Langley Research Center NASA-TM-84901, NAS 1.15:84901 RTOP 505-33-41