High-Frequency Vibration Response of Metal Honeycomb Sandwich Structure

2009 ◽  
Vol 79-82 ◽  
pp. 1727-1730 ◽  
Author(s):  
Xiao Dong He ◽  
Xiang Hao Kong ◽  
Li Ping Shi ◽  
Ming Wei Li
Keyword(s):  
High Frequency ◽  
Sandwich Structure ◽  
Dynamic Pressure ◽  
Vibration Response ◽  
Element Analysis ◽  
High Frequency Vibration ◽  
Honeycomb Sandwich ◽  
Vibration Experiment ◽  
Aerial Vehicle ◽  
Honeycomb Sandwich Structure

ARMOR TPS panel is above the whole ARMOR TPS, and the metal honeycomb sandwich structure is the surface of the ARMOR TPS panel. So the metal honeycomb sandwich structure plays an important role in the ARMOR TPS, while it bears the flight dynamic pressure and stands against the flight dynamic calefaction. So the active environment of metal honeycomb sandwich structure is very formidable. We have to discuss any extreme situation, for reason of making sure aerial vehicle is safe. And high-frequency vibration is one of active environment. In this paper we have analyzed high-frequency vibration response of metal honeycomb sandwich structure. We processed high-frequency vibration experiment by simulating true aerial environment. Sequentially we operated high-frequency vibration experiment of metal honeycomb sandwich structure with cracks, notches and holes. Then finite-element analysis was performed by way of validating the experiment results. Haynes214 is a good high temperature alloy material of both face sheet and core at present, so we choose it in this paper.

Experiment and Simulation on Natural Frequency of Fiber-Paper Honeycomb Sandwich Structure Composites

2011 ◽  
Vol 101-102 ◽  
pp. 360-364 ◽  
Author(s):  
Xiao Jun Yang ◽  
Qing Shan Lan ◽  
Yu Ning Zhong
Keyword(s):  
Sandwich Structure ◽  
Optimization Design ◽  
First Order ◽  
Finite Element Software ◽  
Honeycomb Sandwich ◽  
Vibration Experiment ◽  
Paper Honeycomb ◽  
Result Analysis ◽  
Equivalent Method ◽  
Honeycomb Sandwich Structure

The theory of natural frequencies were acquired from vibration experiment, meanwhile, the first order frequencies of honeycomb sandwich structure composites were obtained by using the sandwich laminboard theory and equivalent panel theory via the finite element software ANSYS. The simulation results were compared to the experiment results to get the error of calculation of the two different equivalent methods, thereby we can select more appropriate equivalent method to ensure the veracity of the result analysis and provide a reference for the optimization design of the fiber-paper honeycomb sandwich structure composites.

Study on Automobile Body Performance of Honeycomb Sandwich Composite Material

2012 ◽  
Vol 567 ◽  
pp. 146-149 ◽  
Author(s):  
Xue Mei Fan ◽  
Jian Feng Wang ◽  
Cheng Jin Duan ◽  
Xiang Xin Xia ◽  
Zhao Hui Wang
Keyword(s):  
Mechanical Properties ◽  
Sandwich Structure ◽  
Testing Machine ◽  
Sandwich Composite ◽  
Element Analysis ◽  
Bending Tests ◽  
Three Point Bending ◽  
Honeycomb Sandwich ◽  
Core Thickness ◽  
Honeycomb Sandwich Structure

In order to analyze the mechanical properties of Carbon/epoxy facings-Aluminum honeycomb sandwich structure, we simulated panels of different layers and core thickness using ABAQUS finite element analysis program. And three-point bending tests and shear tests were made on the same panels using electronic universal testing machine. In addition, we also made the same three-point bending tests on steel tubes to get a comparison with honeycomb sandwich panels. It could be seen that, the simulated results were basically identified with experimental results. The results indicated that core thickness played an important role in the panels’ bulking modulus, and number of carbon fiber layers decided the shear strength. As a whole, honeycomb sandwich structure was suitable for use in the car body with good mechanical properties under premise of lighter.

Thermally induced microcracks and mechanical property of composite honeycomb sandwich structure: Experiment and finite element analysis

2018 ◽  
Vol 22 (8) ◽  
pp. 2544-2566 ◽  
Author(s):  
Sandesh Rathnavarma Hegde ◽  
Mehdi Hojjati
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Mechanical Strength ◽  
Sandwich Structure ◽  
Crack Density ◽  
Thermal Cycles ◽  
Element Analysis ◽  
Honeycomb Sandwich ◽  
Number Of Cycles ◽  
Honeycomb Sandwich Structure

Microcracking in composite honeycomb sandwich structure and its effect on mechanical properties are studied in this paper. A methodology is presented to study the extent of mechanical strength degradation of composite sandwich structure, subjected to thermal fatigue. The material under study is used for spacecraft structural applications. The test coupons were exposed to thermal cycling at elevated temperature as high as +150°C inside the oven and cryogenic temperature of −190°C by dipping in liquid nitrogen, which is comparable to the thermal environment experienced by spacecraft structures. After each thermal cycle, coupons were inspected for microcracks under an optical microscope at the cross section. The microcracks were then quantified using parameters like crack length and crack density with increase in the number of cycles. Flatwise tensile test was conducted on the coupons after every 10 thermal cycles, up to 60 cycles, to make a correlation between crack density and mechanical strength. It was observed that by increasing the number of thermal cycles, the crack density increases and the flatwise tensile strength decreases up to a specific number of cycles. Finite element analysis was performed to predict the possible location of microcracks formation and compared with experimental observation. Good correlation was observed.

Analysis and Research of Honeycomb Sandwich Structure for MicroSatellite Based on Equivalent Theory

2010 ◽  
Vol 426-427 ◽  
pp. 472-476 ◽  
Author(s):  
Kan Zheng ◽  
W.H. Liao ◽  
Y.T. Qin
Keyword(s):  
Mechanical Properties ◽  
Finite Element ◽  
Sandwich Structure ◽  
Plate Theory ◽  
Mechanical Test ◽  
Element Analysis ◽  
Cell Library ◽  
Finite Element Software ◽  
Honeycomb Sandwich ◽  
Honeycomb Sandwich Structure

With the honeycomb sandwich structure widely used in aerospace, the research of its mechanical properties becomes especially important. All of the finite element analysis software have no corresponding cell library, so before the analysis, the honeycomb sandwich panels should be equivalent processed. The paper by taking the floor of a microsatellite as the research object, used the equivalent plate theory and sandwich plate theory for equivalent processing, then adopted the finite element software to analyze the mechanical properties of the floor under two alternative condition. By compared with analytical solution, the equivalent results were reasonable, and the two methods were basically identical. Meanwhile, the equivalent results provided the reliable basis for the satellite structure optimum design and mechanical test.

Honeycomb-Cored Sandwich Structure Composites

2010 ◽  
pp. 223-235
Keyword(s):  
Composite Materials ◽  
Sandwich Structure ◽  
Complex Structure ◽  
Failure Mechanisms ◽  
Resin System ◽  
Lower Weight ◽  
Film Adhesive ◽  
Adhesive Prepreg ◽  
Honeycomb Sandwich ◽  
Honeycomb Sandwich Structure

Abstract The honeycomb sandwich structure composite is a very efficient and complex structure widely used in the aircraft industry. Honeycomb-cored sandwich panels increase part stiffness at a lower weight than monolithic composite materials. This chapter describes the analysis of the intermingling of the film adhesive/prepreg resin system. It discusses the causes and effects of honeycomb core movement, which results in core crush. The chapter also explains the formation of a void in honeycomb composites and the failure mechanisms in honeycomb sandwich structure composites.

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