An alternative simulation approach for the ONERA aerodynamic model and its application in the nonlinear aeroelastic analysis of slender wings with pylon-store system

Xu, Yuqian; Cao, Dengqing; Lin, Huagang; Shao, Chonghui

doi:10.1016/j.ijnonlinmec.2018.07.003

Cited by 7 publications

(2 citation statements)

References 23 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…(50) and (51), into the governing equations of motion, Eqs. (42){ (44). and following the Galerkin procedure, one can obtain a set of ordinary di erential equations describing the in-plane bending, out-of-plane bending, and torsional motions.…”

Section: Discretizing the Equations Of Motionmentioning

confidence: 99%

“…The structure was modeled as thin walled beams and the approximation of the Wagner's function in time domain was used to describe unsteady aerodynamic loads in the incompressible ow regime. Proposing an alternative simulation approach to the nonlinear ONERA aerodynamic model, leading to a reduction in the computational cost, Xu et al [44] studied the nonlinear aeroelastic behaviors of a slender wing without store and the wing-pylon-store system. Nejati et al [25] developed a nonlinear aeroelastic model to investigate nonlinear aeroelastic behavior of HAR wings.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

A Modified Indicial Functions Approximation for Nonlinear Aeroelastic Analysis

et al. 2019

View full text Add to dashboard Cite

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.

show abstract

Section: Discretizing the Equations Of Motionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%