Active flutter suppression control laws were designed, implemented, and tested on an aeroelastically-scaled wind-tunnel model in the NASA Langley Transonic Dynamics Tunnel. One of the control laws was successful in stabilizing the model while the dynamic pressure was increased to 24 percent greater than the measured open-loop flutter boundary. Other accomplishments included the design, implementation, and successful operation of a one-of-a-kind digital controller, the design and use of two simulation methods to support the project, and the development and successful use of a methodology for online controller performance evaluation.
Digital-flutter-suppression-system investigations for the active flexible wing wind-tunnel model
AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference ; 1990 ; Long Beach, CA, United States
1990-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch