Aeroelastic Analysis for Future Air Vehicle Concepts Using a Fully Nonlinear Methodology

Strganac, Thomas W.; Cizmas, Paul G. A.; Nichkawde, Chetan; Gargolo, Joaquin; Beran, Philip S.; Afb, Wright-Patterson

doi:10.2514/6.2005-2171

Cited by 14 publications

(12 citation statements)

References 23 publications

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“…Considering the fact that rotary inertia is of order of two and neglecting the mass imbalance e ects, the same equations as those derived by Crespo da Silva can be obtained [8]. Moreover, the same equations as developed by Strganac et al [4] and Abbas et al [45] can be derived by ignoring nonlinear mass imbalance terms and the in-plane motion, respectively.…”

Section: Structural Modelmentioning

confidence: 75%

“…The SR between the out-of-plane and in-plane bending motions, i.e. , plays an important role in the dynamics of a nonlinear system [4]. Figure 10 shows the SR e ect on the post-utter response of the GW model at the ight condition given in Table 3.…”

Section: Hpamentioning

confidence: 99%

“…In fact, the nonlinear strain-displacement relations (geometric nonlinearity) are responsible for the appearance of nonlinear coupling terms in the bendingbending-torsion equations [2]. As a result of increasing aspect ratio, the importance of in-plane motion in the dynamic responses due to nonlinear coupling should also be included [3,4]. According to the above discussion, although the stability characteristics of HAR wings, e.g., utter speed, may be determined by linear methods, nonlinear analysis is inevitable to investigate the nonlinear phenomena and study the dynamic responses.…”

Section: Introductionmentioning

confidence: 99%

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A Modified Indicial Functions Approximation for Nonlinear Aeroelastic Analysis

et al. 2019

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The nonlinear dynamic response, Limit Cycle Oscillations (LCOs), of High-Aspect-Ratio (HAR) wings using novel indicial aerodynamics in subsonic ow was investigated. Using the nonlinear beam theory, the structural model was derived with in-plane and out-of-plane bending and torsional motions, all nonlinearities up to cubic order arising from large deformation, mass distribution, and cross-sectional mass imbalance. Based on new approximations of the indicial functions, a comprehensive unsteady aerodynamic model was used. Coupling such indicial aerodynamics to nonlinear structural equations can result in a uni ed nonlinear aeroelastic formulation in both incompressible and subsonic compressible ows. The e ects of ight conditions, wing tip initial disturbances, Sti ness Ratio (SR) between bending modes, and nonlinearity due to inertia and cross-sectional mass imbalance on the characteristics of LCO are discussed. The results showed that compressibility could a ect the LCO boundary up to 12 percent, which implied that appropriate Mach-dependent aerodynamics was required to achieve a more reasonable and realistic description of dynamic behavior of the system. It was observed that the presence of LCO before the linear utter speed depended on the initial disturbances as well as wing characteristics.

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Section: Structural Modelmentioning

confidence: 75%

Section: Hpamentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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A Modified Indicial Functions Approximation for Nonlinear Aeroelastic Analysis

et al. 2019

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“…Studies of nonlinear fluid-structure interactions have been motivated by evidence that there are adverse aeroelastic responses attributed to system nonlinearities. For example, the flexibility of some new classes of air vehicles leads to large out-of-plane deformations as well as to remarkable in-plane responses (Strganac et al, 2005). In addition, limit-cycle oscillations (LCOs) occur in nonlinear aeroelastic systems and remain a persistent problem on fighter aircraft with store configurations.…”

Section: Introductionmentioning

confidence: 99%

A Novel Method for Prediction of Nonlinear Aeroelastic Responses

Cizmas¹,

Strganac²

2010

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“…To close the formulation, the geometrically-nonlinear structural model needs to be coupled with the appropriate aerodynamic solver, i.e., potential-flow theory at low flight speeds [13]- [14] or Euler/NavierStokes equations for compressible flow [15]- [16]. From this coupling, some physical phenomena can arise that do not occur under small structural displacements.…”

Section: Aeroelastic Stability Evaluationmentioning

confidence: 99%

Reexamined Structural Design Procedures for Very Flexible Aircraft

Cesnik

Palacios

Reichenbach

2014

Journal of Aircraft

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This paper reviews the applicability of some conventional structural design practices to the analysis and design of very flexible aircraft. The effect of large structural deformations and the coupling between aeroelasticity and flight dynamics is investigated in different aspects of the aircraft structural design process, including aeroelastic stability, loads, and flight dynamics and control. This is illustrated with a numerical example of the static and dynamic responses of a representative high-altitude long-endurance vehicle. Suggestions are presented for the development of appropriate frameworks to design and analyze very flexible aircraft.

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Aeroelastic Analysis for Future Air Vehicle Concepts Using a Fully Nonlinear Methodology

Cited by 14 publications

References 23 publications

A Modified Indicial Functions Approximation for Nonlinear Aeroelastic Analysis

A Modified Indicial Functions Approximation for Nonlinear Aeroelastic Analysis

A Novel Method for Prediction of Nonlinear Aeroelastic Responses

Reexamined Structural Design Procedures for Very Flexible Aircraft

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