Topic
Sandwich panel
About: Sandwich panel is a research topic. Over the lifetime, 4665 publications have been published within this topic receiving 49812 citations.
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22 Apr 2002
TL;DR: In this article, a composite, grid stiffened, cylindrical panel loaded in axial compression was used for the Minotaur OSP space launch vehicle to carry operational loads past the initial postbuckling.
Abstract: Due to weight and cost goals, a grid-stiffened panel concept is being used for redesign of a structural component on the Minotaur OSP space launch vehicle. By designing the structural panels to carry operational loads past the point of initial buckling (local postbuckling), the resulting grid stiffened panel concept is lighter and 30% less costly to manufacture than other design candidates such as the existing honeycomb sandwich panel concept flown today. During June 2001 in Seattle, Boeing performed a structural certification experiment of a composite, grid stiffened, cylindrical panel loaded in axial compression. Pretest predictions were made for linear elastic (bifurcation) buckling, and non-linear post buckling. The tools used for pretest analysis were HyperSizer, and the FEM based tools MSC/NASTRAN and STAGS. Local buckling of the facesheet triangular shaped skin pocket occurred at a load of around 230 (lb/in). The test panel was able to sustain considerable additional loading, with post buckling failure occurring at 1320 (lb/in). The HyperSizer post buckling pretest prediction was 1300 (lb/in), the STAGS pretest prediction was 1250 (lb/in), and the MSC/NASTRAN pretest prediction ranged from 1425 to 2000 (lb/in). HyperSizer’s implementation of local post buckling based on an effective width approach is presented.
33 citations
TL;DR: In this paper, a comparative study on impact damage detection in light composite sandwich panels is presented, where three different non-destructive testing methods are used to characterize damage in a test specimen that resulted from a controlled low velocity impact event.
33 citations
25 May 2011-Materials Science and Engineering A-structural Materials Properties Microstructure and Processing
TL;DR: In this paper, the authors used the Finite Element Method (FEM) to study the brazing residual stresses in a stainless steel X-type lattice truss sandwich structure, and the nanoindentation experiment was used to verify the validity of FEM.
Abstract: The lattice truss sandwich structures are considered as the most promising advanced lightweight materials used in modern industries and aircrafts. Most sandwich panel structures are fractured at brazed joints named node failure during static and dynamic testing, which is mainly influenced by brazing residual stresses. Finite element method (FEM) was used to study the brazing residual stresses in a stainless steel X-type lattice truss sandwich structure. And the nanoindentation experiment is used to verify the validity of FEM. The effects of braze processing parameters including applied load, face sheet thickness, truss thickness and truss length on residual stresses have been investigated. It is shown than the residual stresses are concentrated on the brazed joint, which has a significant effect on node failure. As the applied load increases, the residual stresses decrease first and then remain unchanged, and the optimal applied load is around 1 MPa. As the face sheet thickness increasing, the residual stresses are increased. Too thin face sheet can cause large residual stresses on the top surface of face sheet. With truss thickness and truss length increase, the residual stresses are decreased first and then increased. The optimized face sheet, truss thickness and truss length are found to be 2 mm, 1 mm and 26 mm.
33 citations
TL;DR: In this article, a finite element study is conducted to determine optimal geometric parameters of hollow tetrahedral truss cores given height and density constraints, and nodal height truncation is introduced as an additional parameter for this architecture, and demonstrate that nodal truncation can yield further improvements in the shear and compression strength.
33 citations