Design of a candidate flutter suppression control law for DAST ARW-2A control law is developed to suppress symmetric flutter for a mathematical model of an aeroelastic research vehicle. An implementable control law is attained by including modified LQG (linear quadratic Gaussian) design techniques, controller order reduction, and gain scheduling. An alternate (complementary) design approach is illustrated for one flight condition wherein nongradient-based constrained optimization techniques are applied to maximize controller robustness.
Document ID
19830065907
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Adams, W. M., Jr. (NASA Langley Research Center Hampton, VA, United States)
Tiffany, S. H. (NASA Langley Research Center Hampton, VA, United States)