Influence of large-deflection effects on the impact response of flat and curved composite plates

Ambur, Damodar R.; Starnes, H James; Stoumbos, Tom; Kapania, Rakesh K.

doi:10.2514/6.1995-1205

Cited by 9 publications

(5 citation statements)

References 7 publications

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“…Swanson scaling investigation to the impact response of composite cylinders, and found that the cylinder radius is a geometric factor, and scales by λ [17]. Previous analytical and experimental studies [6][7][8][9][10][11] have shown that thin composite panels exhibit geometrically nonlinear response when impacted at very low impact energies. Thin flat panels exhibit a nonlinear stiffening response, and some thin curved panels exhibit an initial nonlinear softening response.…”

Section: Nonlinear Analysis and Scaling Rulesmentioning

confidence: 99%

“…The clamping screws that attach the fixture base-plate and face-plate penetrate the test specimen through holes drilled in the specimen. This fixture has been used in previous investigations [6][7][8][9], and was designed to minimize translations and rotations at the test section boundary. Satisfying these conditions is particularly important for studying the impact response of thin plates and curved panels in which geometrically nonlinear effects are significant.…”

Section: Test Apparatus and Testsmentioning

confidence: 99%

“…Therefore, scaling laws and analysis methods for these structures must include the effects of geometric nonlinearity. A geometrically nonlinear analysis method has been previously developed for predicting the elastic impact response of thin, curved, anisotropic panels [6][7][8][9]. The analysis method is based on the Lagrangian equations of motion, which are solved using the Rayleigh-Ritz method and assumed mode shapes.…”

Section: Nonlinear Analysis and Scaling Rulesmentioning

confidence: 99%

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Scaling the Non-linear Impact Response of Flat and Curved Composite Panels

Ambur

Chunchu

Rose

et al. 2005

46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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The application of scaling laws to thin flat and curved composite panels exhibiting nonlinear response when subjected to low-velocity transverse impact is investigated. Previous research has shown that the elastic impact response of structural configurations exhibiting geometrically linear response can be effectively scaled. In the present paper, a preliminary experimental study is presented to assess the applicability of the scaling laws to structural configurations exhibiting geometrically nonlinear deformations. The effect of damage on the scalability of the structural response characteristics, and the effect of scale on damage development are also investigated. Damage is evaluated using conventional methods including C-scan, specimen de-plying and visual inspection of the impacted panels. Coefficient of restitution and normalized contact duration are also used to assess the extent of damage. The results confirm the validity of the scaling parameters for elastic impacts. However, for the panels considered in the study, the extent and manifestation of damage do not scale according to the scaling laws. Furthermore, the results indicate that even though the damage does not scale, the overall panel response characteristics, as indicated by contact force profiles, do scale for some levels of damage.

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Section: Nonlinear Analysis and Scaling Rulesmentioning

confidence: 99%

Section: Test Apparatus and Testsmentioning

confidence: 99%

Section: Nonlinear Analysis and Scaling Rulesmentioning

confidence: 99%

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Scaling the Non-linear Impact Response of Flat and Curved Composite Panels

Ambur

Chunchu

Rose

et al. 2005

46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

Self Cite

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“…There is very limited information in the literature that addresses the low-speed impact response of curved sandwich composite with thin facesheet that is typical of fuselage skins. It has been shown that composite plates with curvature and certain combinations of plate dimensions exhibit a nonlinear ''softening" response when impacted with dropped-weight impactors [15,16].…”

Section: Introductionmentioning

confidence: 99%

Impact behavior of composite antenna array that is conformed around cylindrical bodies

You¹,

Kim

Cho

et al. 2010

Composites Science and Technology

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“…The effect of impactor contact force on response was studied by Prasad et al (1994). The nonlinear impact response of thin laminates was studied analytically by Byun and Kapania (1992), and by Ambur et al (1995). Matsuhashi et al (1993) investigated the effect of inplane stiffening on linear and nonlinear response of composite panels.…”

Section: Introductionmentioning

confidence: 99%

Response of a thin cylindrical panel with constrained edges

El‐Raheb¹

2006

International Journal of Solids and Structures

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Static and transient responses of a thin cylindrical panel constrained from motion along its straight edges and simply supported along its curved edges are treated analytically. Independent of modulus, and for a range of geometric parameters, static deformation along the panel's circumference from a uniform radial pressure exhibits an indentation. This indentation does not appear in transient response of the panel from an impulse of short duration. Extensional boundary constraints strongly affect peak stress in static and transient response.Static response, buckling and frequency response of curved panels were treated extensively in the literature. Skvortsov et al. (1998) analyzed static response of a cylindrical panel adopting general shell, shallow shell and curved plate theories, as well as a nonlinear model with arbitrary generator shape. Skvortsov et al. (2000) treated static response and stability of an arbitrary singly curved sandwich panel with general boundary conditions based on the Reissner-Mindlin plate theory. Blevins (1981) adopted Sewall's approximate shallow shell formulation to consider a wide range of boundary conditions. Approximate solutions to free vibration, buckling and transient response of the panel were obtained by Sheinman and Reichman (1992) using the reduced bending stiffness method, and by Chun and Lam (1995) employing the Ritz method with the beam's eigenfunctions or simple admissible polynomials as trial functions. DeRosa and Franciosi (2000) adopted the differential quadrature method to determine the inextensional resonances of thin arcs. All analyses above are based on approximate solutions along the circumferential direction.Dynamic response of curved panels from a pulse of duration much longer than the panel's fundamental period has been the subject of recent investigations. Among these, Johnson et al. (1984) treated the response of an infinite panel or arc to an eccentric line load. Ramkumar and Thakar (1985) extended the analysis to laminated panels with finite length along the generator and neglected inplane and rotary inertias and shear deformation confining their analysis to quasi-static conditions. The effect of panel geometric imperfection on 0020-7683/$ -see front matter Ó

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Influence of large-deflection effects on the impact response of flat and curved composite plates

Cited by 9 publications

References 7 publications

Scaling the Non-linear Impact Response of Flat and Curved Composite Panels

Scaling the Non-linear Impact Response of Flat and Curved Composite Panels

Impact behavior of composite antenna array that is conformed around cylindrical bodies

Response of a thin cylindrical panel with constrained edges

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