A 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 LQC (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.
Design of a Candidate Flutter Suppression Control Law for DAST ARW-2
1984
28 pages
Report
Keine Angabe
Englisch
Design of the flutter suppression system for DAST ARW-IR
NTRS | 1983
|Design of the Flutter Suppression System for Dast Arw-IR
NTIS | 1983
|