Flutter suppression using active controls based on the concept of aerodynamic energy
National Aeronautics and Space Administration, 1971 - Mathematics - 112 pages
Flutter suppression with dissipated energy reduced to quadratic form for control surfaces.
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THE ENERGY APPROACH TO FLUTTER SUPPRESSION
OPTIMIZATION AT ZERO MACH NUMBER
5 other sections not shown
accelerometers active controls active strips actuated aerodynamic damping aerodynamic energy aerodynamic forces aerodynamic stiffness terms Aeroelasticity airplane Amin and Amax amplitude gain APPENDIX considered control deflection control parameters determine diagonal matrix dissipative eigenvectors energy approach error function Figure 12 flight conditions flutter equations flutter speed flutter suppression fluttering system frequency modes give rise Gust Alleviation Hence Hermitian matrix L.E.-T.E. control system Langley Research Center Mach number main surface matrix modal mode shapes mode stabilization NACA negative obtained optimized control law Optimum Power optimum values oscillation oscillatory phase lags phugoid positive Power for T. E. power requirement quadratic form range of reduced rigid-body modes rotational sensor shown in sketch shows simplified flutter model spanwise structural mode suppression of flutter T.E. control surface T.E. control system T.E. system two-dimensional V-g plot value of Amin Variation of Amin vector whereas wing strip Xmin yields