Application of two synthesis methods for active flutter suppression on an aeroelastic wind tunnel model

Abel, I.; Newsom, J. R.; Dunn, H. J.

doi:10.2514/6.1979-1633

Cited by 8 publications

(4 citation statements)

References 2 publications

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“…(5) and (6) amount to (7) Notice here that the D C P is related to the mode shape h rather than the downwash w in a formal AIC formulation. The modalbased matrix [A m ] contains intrinsically all of the necessary aerodynamic information as provided by the baseline pressure-mode relation Eq.…”

Section: Modal-based Aicmentioning

confidence: 99%

Transonic-Aerodynamic-Influence-Coefficient Approach for Aeroelastic and MDO Applications

Chen

Sarhaddi

Liu

2000

Journal of Aircraft

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A developed transonic-aerodynamic-in uence-coef cient (TAIC) method is proposed as an ef cient tool for applications to utter, aeroservoelasticity, and multidisciplinary design/analysis optimization. Several plausible procedures for AIC generation are described. The modal-based AIC procedure is formally established as a general AIC scheme applicable to all classes of computational uid dynamics (CFD) methods. The present TAIC method integrates the previous transonic equivalent strip (TES) method with the modal AIC approach; its computer code ZTAIC has a similar input format to that of doublet lattice method (DLM) except with the additional steady pressure input. The versatility of ZTAIC is shown by two sets of cases studied: those cases with pressure input from measured data and those from CFD computation. Computed results of unsteady pressures and utter points are presented for six wing planforms. In contrast to the usual CFD practice, the effective use of the modal AIC in ZTAIC is clearly demonstrated by the utter calculations of the weakened and solid 445.6 wings, where the CPU time of a transonic utter point using warm-started AIC is less than 1 min on a SUN SPARC20 workstation. Moreover, the AIC capability allows ZTAIC to be readily integrated with structural nite element method (FEM). Hence, it is most suitable to be adopted in a multidisciplinary design (MDO) environment such as ASTROS.

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Section: Modal-based Aicmentioning

confidence: 99%

Transonic-Aerodynamic-Influence-Coefficient Approach for Aeroelastic and MDO Applications

Chen

Sarhaddi

Liu

2000

Journal of Aircraft

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“…Other works utilizing classical SISO control methods were implemented such as that by Abel et al [94]. Around the same time, controllers utilizing modern control theory were being developed [95].…”

Section: Siso Flutter Suppressionmentioning

confidence: 99%

Robust Modal Filtering for Control of Flexible Aircraft

Suh

2013

AIAA Atmospheric Flight Mechanics (AFM) Conference

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me invaluable advice and contributed to my work. My foremost and sincere appreciation goes to Dr. Dimitri Mavris, my thesis advisor for his course corrections and thoughtful input which shaped my dissertation. Special thanks to Mr. Steve Jacobson, Branch Chief of NASA's Dryden Flight Research Center (DFRC), who inspired the thesis concept. Gratitude is owed to Mr. Martin Brenner for confirming that the modal filtering approach was mathematically sound from the beginning. I would like to acknowledge thesis committee members Dr.

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“…State-spaceASE models have been used in variousapplicationsof optimal (full-state feedback) and reduced-order control techniques such as those of Abel et al 16 and Mukhopadhyay et al 17 Clearly, recasting the equations of motion of the ASE system into the rstorder, state-space form will allow the user of an MDO system such as ASTROS to apply various modern control techniques for control law design.…”

Section: Aeroservoelastics In State-space Formmentioning

confidence: 99%

Unified Aerodynamic-Influence-Coefficient Approach for Aeroservoelastic and Multidisciplinary Optimization Applications

Chen

Sarhaddi

Liu

et al. 2000

Journal of Aircraft

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A uni ed aerodynamic in uence coef cient (UAIC) method has been developed for aeroservoelastic (ASE) analysis as well as multidisciplinary optimization (MDO) applications. The UAIC method is applicable to all Mach numbers from subsonic, to transonic, to supersonic, to hypersonic ight regimes. It is fully compatible with the structural nite element method and, hence, with an MDO system such as ASTROS. Based on this UAIC approach, a uni ed aerodynamic module ZAERO and an ASE module can be developed; the former performs in the k domain and the latter in the s domain. A minimum-state technique is found most effective in converting the k-domain solution to the s domain for all Mach numbers. Flutter results computed by the root-locus method are found to agree well with those of the V -g method and measured data.

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Application of two synthesis methods for active flutter suppression on an aeroelastic wind tunnel model

Cited by 8 publications

References 2 publications

Transonic-Aerodynamic-Influence-Coefficient Approach for Aeroelastic and MDO Applications

Transonic-Aerodynamic-Influence-Coefficient Approach for Aeroelastic and MDO Applications

Robust Modal Filtering for Control of Flexible Aircraft

Unified Aerodynamic-Influence-Coefficient Approach for Aeroservoelastic and Multidisciplinary Optimization Applications

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