Vivek Mukhopadhyay

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Three control law design techniques for utter suppression are presented. Each technique uses multiple control surfaces and/or sensors. The rst method uses traditional tools (such as pole/zero loci and Nyquist diagrams) for producing a controller that has minimal complexity and which is su ciently robust to handle plant uncertainty. The second procedure uses(More)
iii CIP I am sincerely indebted to the dozens of current and retired employees of NASA who consented to be interviewed and submitted their personal experiences, recollections, and files from which this documentation of Langley contributions was drawn. The following active and retired Langley personnel contributed vital information to this effort: I would(More)
The benchmark active controls technology and wind tunnel test program at NASA Langley Research Center was started with the objective to investigate the nonlinear, unsteady aerodynamics and active flutter suppression of wings in transonic flow. The paper will present the flutter suppression control law design process, numerical nonlinear simulation and wind(More)
An interactive computer program was developed for wing flutter analysis in the conceptual design stage. The objective was to estimate the flutter instability boundary of a flexible cantilever wing, when well defined structural and aerodynamic data are not available, and then study the effect of change in Mach number, dynamic pressure, torsional frequency,(More)
Initial results of an investigation towards finding an efficient non-cylindrical fuselage configuration for a conceptual blended-wing-body flight vehicle were presented. A simplified 2-D beam column analysis and optimization was performed first. Then a set of detailed finite element models of deep sandwich panel and ribbed shell construction concepts were(More)
An interactive computer program was developed for wing flutter analysis in the conceptual design stage. The objective was to estimate flutter instability boundaries of a typical wing, when detailed structural and aerodynamic data are not available. Effects of change in key flutter parameters can also be estimated in order to guide the conceptual design.(More)
The benchmark active controls technology and wind tunnel test program at NASA Langley Research Center was started with the objective to investigate the nonlinear, unsteady aerodynamics and active flutter suppression of wings in transonic flow. The paper will present the flutter suppression control law design process, numerical nonlinear simulation and wind(More)