High-order nonlinear contact effects in cyclic loading of delaminated sandwich panels

2007 ◽  
Vol 38 (1) ◽  
pp. 86-101 ◽  
Author(s):  
H. Schwarts-Givli ◽  
O. Rabinovitch ◽  
Y. Frostig
Keyword(s):  
Cyclic Loading ◽  
Sandwich Panels ◽  
High Order ◽  
Nonlinear Contact ◽  
Contact Effects

Modeling of tapered sandwich panels using a high-order sandwich theory formulation

AIAA Journal ◽  
2002 ◽  
Vol 40 ◽  
pp. 1867-1875
Author(s):  
J. R. Vinson ◽  
O. T. Thomsen
Keyword(s):  
Sandwich Panels ◽  
High Order ◽  
Theory Formulation

Comparative Study of Two Different Conceptual Design Principles for Non-Circular Pressurized Sandwich Fuselage Sections Using a High-Order Sandwich Theory Formulation

2000 ◽  
Author(s):  
Ole T. Thomsen ◽  
Jack R. Vinson
Keyword(s):  
Air Force ◽  
United States Air Force ◽  
Sandwich Panels ◽  
The United States ◽  
High Order ◽  
Elastic Response ◽  
Modeling And Analysis ◽  
Theory Formulation ◽  
Range Transport ◽  
Core Thickness

Abstract Results obtained as part of a design study regarding a non-circular pressurized sandwich fuselage section are presented. The originating problem is associated with preliminary studies for the “Global Range Transport” envisaged by the “New World Vistas” program of the United States Air Force. The modeling and analysis is conducted using a high-order sandwich theory formulation in which the elastic response of each face laminate is accounted for, including bending-stretching coupling and transverse shear deformations, and where the transverse flexibility of the core is included. The sandwich fuselage envisaged may contain flat, tapered and curved sandwich elements, and a high-order sandwich theory formulation is developed to analyze each of these configurations. The paper includes a brief presentation of the adopted high-order sandwich theory with special emphasis on the application for the analysis of sandwich panels with variable core thickness, and for the analysis of curved sandwich panels. Numerical results obtained for two different mid-plane asymmetric fuselage sections are presented and compared; one with constant core thickness, and one with varying core thickness.

Modeling of Tapered Sandwich Panels Using a High-Order Sandwich Theory Formulation

AIAA Journal ◽  
2002 ◽  
Vol 40 (9) ◽  
pp. 1867-1875 ◽  
Author(s):  
Ole Thybo Thomsen ◽  
Jack R. Vinson
Keyword(s):  
Sandwich Panels ◽  
High Order ◽  
Theory Formulation

scholarly journals Use of Blind Rivets in Sandwich Panels—Experimental Investigation of Static and Quasi-Cyclic Loading

Buildings ◽  
2020 ◽  
Vol 10 (9) ◽  
pp. 155
Author(s):  
Robert Studziński ◽  
Katarzyna Ciesielczyk
Keyword(s):  
Experimental Investigation ◽  
Cyclic Loading ◽  
Sandwich Panel ◽  
Tensile Force ◽  
Sandwich Panels ◽  
Core Layer ◽  
Mineral Wool ◽  
Expanded Polystyrene ◽  
Eccentric Load ◽  
Pull Out

In this paper, we present an original experimental investigation on a pull-out test of a blind rivet from the external facing of sandwich panels with various core layer materials (polyisocyanurate foam, mineral wool, and expanded polystyrene). The blind rivets were subjected to an axial and eccentric tensile force introduced as static and quasi-cyclic loading. The statistical sample size was 5. The laboratory results depicted that the core layer of a sandwich panel influenced the load-displacement path of the investigated blind rivet connections, regardless of the nature of the load (static, quasi-cyclic) and the point of the load application (axial, eccentric). It was observed that the blind connection with the polyisocyanurate foam core sandwich panel was characterized by a reduction of both the capacity and the secant stiffness when compared with the blind connection with the mineral wool or the expanded polystyrene core sandwich panels. Moreover, the tested connections demonstrated that the eccentric load gave a higher flexural stiffness than the axial load and that the quasi-cyclic load did not reduce their stiffness and capacity.

Sign in / Sign up

Export Citation Format

Share Document