Flight test results of an active flutter suppression system installed on a remotely piloted research vehicleFlight flutter test results of the first aeroelastic research wing of NASA's Drones for Aerodynamic and Structural Testing (DAST) program are presented. The implementation of the flutter suppression system and the flight test operation are described. The conduct of the flutter testing and the near-real time damping estimation algorithm are also described in detail. Flight data was obtained at Mach numbers up to 0.91 and was of high quality. Response to fast frequency sweep excitation provided reliable damping estimates and the open-loop flutter boundary was well defined. Evidence of angle-of-attack effects upon damping at high transonic Mach numbers is also presented. While the flutter suppression system provided augmented damping at speeds below the flutter boundary, an error in the implementation of the system gain caused the system to be less stable than predicted and the vehicle encountered system-on flutter on the third flight.
Document ID
19810045103
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Edwards, J. W. (NASA Langley Research Center Hampton, Va., United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 81-0655
Meeting Information
Meeting: Conference on Structures, Structural Dynamics and Materials