Stress Recovery in Composite Laminates Including Geometrically Nonlinear and Dynamic Effects

Hartman, Timothy B.; Hyer, M. W.; Case, Scott W.

doi:10.2514/1.j054700

Cited by 7 publications

(3 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…They first approximate a transverse stress field, whose error is reduced via minimisation of a least square functional at the element level. Later, Hartman et al [39] proposed an iterative stress recovery technique with application to laminated plates, which is then extended to include inertial effects in a later publication [42]. These works demonstrated considerable savings in the computational time for accurate interlaminar stresses.…”

Section: D Cauchy Stress Tracking In a Thick Laminated Roofmentioning

confidence: 99%

“…Firstly, the 3D stress accuracy of the VKCS model is validated with a simple benchmark from Hartman et al [39], as shown in Figure 7. It shall be noted that the benchmarks for nonlinear Cauchy stresses are scarce in the literature, and mostly focus on laminated flat plates [39][40][41][42] that are 2D in nature (plane stress/strain).…”

Section: D Cauchy Stress Tracking In a Thick Laminated Roofmentioning

confidence: 99%

See 1 more Smart Citation

A geometrically nonlinear variable-kinematics continuum shell element for the analyses of laminated composites

Hii

Minera

Groh

et al. 2022

Finite Elements in Analysis and Design

View full text Add to dashboard Cite

Section: D Cauchy Stress Tracking In a Thick Laminated Roofmentioning

confidence: 99%

Section: D Cauchy Stress Tracking In a Thick Laminated Roofmentioning

confidence: 99%

A geometrically nonlinear variable-kinematics continuum shell element for the analyses of laminated composites

Hii

Minera

Groh

et al. 2022

Finite Elements in Analysis and Design

View full text Add to dashboard Cite

“…Table 3 shows this comparison for mesh densities of 16 × 16 ×16 in the case of Abaqus 3-D models). In the 3-D models, it should be highlighted that the midplane outer edges were constrained in attempt to simulate the same restriction of the two-dimensional models [19].…”

Section: B Problemmentioning

confidence: 99%

New Generalized Unified Solution Method for Thin Laminated Plates

2016

View full text Add to dashboard Cite

Nomenclature C= related to the constitutive matrix in global coordinates and its components F N = functions of the Nth order used in the expansion along the thickness variable H i = two-dimensional Hermite interpolation functions K = related to the global stiffness matrix and its components M = related to the global mass matrix and its components N i = two-dimensional serendipity interpolation function N l = number of plies N τ = order of the complete polynomial chosen for the displacement fields P = vector of normal forces R = vector of moments and twist u = vector of displacement fields u, v = in-plane displacement fields w = transverse displacement field x, y = in-plane coordinate variables z = transverse coordinate variable Γ = plate's in-plane domain δ mn = Kronecker delta ρ = density Ω = plate's three-dimensional domain Subscripts i, j = recurrence indices for node numbering m, n = recurrence indices for Kronecker delta x = first derivative with respect to in-plane x position xy = crossed derivative in respect to in-plane position variables y = first derivative with respect to in-plane y position α = recurrence index related to any expansion term of the three displacement fields α u , α v = related to the order of the in-plane displacement fields polynomial expansion term α w = related to the order of the out-of-plane displacement field polynomial expansion term 1, 2, 3, 4, 5, 6 = local indices used to identify anisotropic material properties Superscripts e = related to the finite element i, j = recurrence indices for node numbering k = current ply r, s = recurrence indices indicating the terms in the displacement polynomial functions T = transpose

show abstract

Large displacement models for composites based on Murakami's Zig-Zag Function, Green-Lagrange Strain Tensor, and Generalized Unified Formulation

Santarpia

Demasi

2020

Thin-Walled Structures

View full text Add to dashboard Cite

Stress Recovery in Composite Laminates Including Geometrically Nonlinear and Dynamic Effects

Cited by 7 publications

References 16 publications

A geometrically nonlinear variable-kinematics continuum shell element for the analyses of laminated composites

A geometrically nonlinear variable-kinematics continuum shell element for the analyses of laminated composites

New Generalized Unified Solution Method for Thin Laminated Plates

Large displacement models for composites based on Murakami's Zig-Zag Function, Green-Lagrange Strain Tensor, and Generalized Unified Formulation

Contact Info

Product

Resources

About