Dimensional Variation of Aluminum Honeycomb Panel on Circular Cutting with Abrasive Jet Machining Technology

2015 ◽  
Vol 760 ◽  
pp. 397-402 ◽  
Author(s):  
Horatiu Bulea ◽  
Rodica Paunescu ◽  
Alexandru Catalin Filip
Keyword(s):  
Abrasive Waterjet ◽  
Main Process ◽  
Proper Solution ◽  
Abrasive Jet Machining ◽  
Circular Holes ◽  
Aluminum Honeycomb ◽  
Dimensional Parameters ◽  
Dimensional Variation ◽  
Pump Pressure ◽  
Honeycomb Panel

The manufacturing of aluminum honeycomb panel are usually difficult. The abrasive waterjet method can offer a suitable solution. This paper presents the results of some experiments on waterjet cutting of circular holes into aluminum honeycomb panel, which can be further used for cutting holes in aluminum honeycomb panel . The main problem which occurs is the tapered shape of the hole, due to the mechanics of the process and the control of the kerf produced by the waterjet. The experiments considered several values of the main process parameters like the pump pressure and the feed rate which have a direct influence on the part machineability. After measuring the parts, there were analyzed the main dimensional parameters of precision to reveal the proper solution for obtaining the required quality of the process.

scholarly journals Influence of Traverse Velocity and Pump Pressure on the Efficiency of Abrasive Waterjet for Rock Cutting

2017 ◽  
Vol 40 (3) ◽  
pp. 255-262 ◽  
Author(s):  
Paola Bruno Arab ◽  
Tarcísio Barreto Celestino
Keyword(s):  
Rock Cutting ◽  
Abrasive Waterjet ◽  
Pump Pressure

Thermal damage of aluminum honeycomb panel irradiated by continuous laser

Optik ◽  
2019 ◽  
Vol 182 ◽  
pp. 131-138 ◽  
Author(s):  
Aixi Sun ◽  
Chun Cheng ◽  
Zhonghua Du
Keyword(s):  
Thermal Damage ◽  
Continuous Laser ◽  
Aluminum Honeycomb ◽  
Honeycomb Panel

scholarly journals Comparative Analysis of Al-Li Alloy and Aluminum Honeycomb Panel for Aerospace Application by Structural Optimization

2015 ◽  
Vol 2015 ◽  
pp. 1-12 ◽  
Author(s):  
Naihui Yu ◽  
Jianzhong Shang ◽  
Yujun Cao ◽  
Dongxi Ma ◽  
Qiming Liu
Keyword(s):  
Comparative Analysis ◽  
Structural Optimization ◽  
System Level ◽  
Size Optimization ◽  
Honeycomb Core ◽  
Load Path ◽  
Reconstruction Process ◽  
Alloy Plate ◽  
Aluminum Honeycomb ◽  
Honeycomb Panel

Al-Li alloy and aluminum honeycomb panel (AHP) are both excellent materials for aeronautical structures. In this paper, a plate-type aeronautical structure (PAS), which is a base mounting structure for 172 kg functional devices, is selected for comparative analysis with different materials. To compare system-level performance under multidisciplinary constraints, mathematical models for optimization are established and then structural optimization is carried out using Altair OptiStruct. For AHP, its honeycomb core is regarded as orthotropic material and its mechanical properties are calculated by Allen’s model in order to establish finite element model (FEM). The heights of facing sheet and honeycomb core are selected as design variables for size optimization. For Al-Li alloy plate, topology optimization is carried out to obtain its most efficient load path; and then a reconstruction process is executed for practical manufacturing consideration; to obtain its final configuration, accurate size optimization is also used for reconstructed model of Al-Li alloy plate. Finally, the optimized mass and performance of two PASs are compared. Results show that AHP is slightly superior to Al-Li alloy.

scholarly journals Nonlinear Modeling and Identification of an Aluminum Honeycomb Panel with Multiple Bolts

2016 ◽  
Vol 2016 ◽  
pp. 1-8
Author(s):  
Yongpeng Chu ◽  
Hao Wen ◽  
Ti Chen
Keyword(s):  
Thin Layer ◽  
Plastic Material ◽  
Experimental Tests ◽  
Bolted Joints ◽  
High Excitation ◽  
Material Parameters ◽  
Elastic Plastic ◽  
Aluminum Honeycomb ◽  
Elastic Plastic Material ◽  
Honeycomb Panel

This paper focuses on the nonlinear dynamics modeling and parameter identification of an Aluminum Honeycomb Panel (AHP) with multiple bolted joints. Finite element method using eight-node solid elements is exploited to model the panel and the bolted connection interface as a homogeneous, isotropic plate and as a thin layer of nonlinear elastic-plastic material, respectively. The material properties of a thin layer are defined by a bilinear elastic plastic model, which can describe the energy dissipation and softening phenomena in the bolted joints under nonlinear states. Experimental tests at low and high excitation levels are performed to reveal the dynamic characteristics of the bolted structure. In particular, the linear material parameters of the panel are identified via experimental tests at low excitation levels, whereas the nonlinear material parameters of the thin layer are updated by using the genetic algorithm to minimize the residual error between the measured and the simulation data at a high excitation level. It is demonstrated by comparing the frequency responses of the updated FEM and the experimental system that the thin layer of bilinear elastic-plastic material is very effective for modeling the nonlinear joint interface of the assembled structure with multiple bolts.

Effect of Top Piston Ring Wear on Its Sealing and Scraping Performance

2005 ◽  
Author(s):  
Andre Ferrarese ◽  
Amilton Sinatora ◽  
Fabio Luz Almeida
Keyword(s):  
Gas Flow ◽  
Piston Ring ◽  
Superior Performance ◽  
Test Results ◽  
Oil Consumption ◽  
Dimensional Parameter ◽  
Dimensional Parameters ◽  
Dimensional Variation ◽  
The Individual ◽  
Engine Components

New engines are presenting a constant increase of mechanical and thermal loads. The engine components should guarantee similar, or superior, performance than the baseline components in spite of the unfavorable wear conditions. For piston rings, the performance is given by the ring capacity of sealing and scraping. This performance can be measured in an engine by the lube oil consumption (LOC) and the gas flow to the crankcase (Blow-by) results. The purpose of this work is to evaluate the top piston ring wear influence on its sealing and scraping performance. Two engines were tested, one Otto and the other Diesel, in a dynamometer in order to quantify the top ring dimensional variation due to wear. Numerical simulations were performed in order to evaluate the individual influences of each dimensional parameter. The results of LOC and Blow-by were compared to literature data and engine test results of each engine. A proposal of combined effects among the dimensional parameters is presented.

Finite Element Simulation on Three-point Bending of Brazed Aluminum Honeycomb Panel

2010 ◽  
Vol 168-170 ◽  
pp. 1046-1050 ◽  
Author(s):  
Ming Jun Peng ◽  
Yong Sun ◽  
Ji Yao ◽  
Yong Hua Duan ◽  
Sai Bei Wang
Keyword(s):  
Failure Modes ◽  
Shear Failure ◽  
Failure Load ◽  
Honeycomb Core ◽  
Three Point Bending ◽  
Aluminum Honeycomb ◽  
Longitudinal Bending ◽  
Panel Thickness ◽  
Bending Failure ◽  
Honeycomb Panel

The mechanics behaviors on three-point bending of brazed aluminum honeycomb panel by FEM are investigated in this paper. The results show that honeycomb panel have three typical failure modes under bending load：failure of honeycomb core collapse, the whole panel bending failure and face sheet shear failure. Honeycomb lateral bending failure load is greater than the longitudinal bending failure load. When the ratio of honeycomb core thickness and panel thickness is between 10% to 15%, the strongest cellular panel bending occurs.

Temperature Effect on the Modal Frequencies of Aluminum Honeycomb Plate

2020 ◽  
Vol 1159 ◽  
pp. 27-41
Author(s):  
Redha Amri
Keyword(s):  
Natural Vibration ◽  
Natural Frequencies ◽  
Vibration Modes ◽  
Thickness Direction ◽  
The Core ◽  
Modes Of Vibration ◽  
Aluminum Honeycomb ◽  
Core Thickness ◽  
Very High ◽  
Honeycomb Panel

The aim of this paper is to perform a study on how the elevated temperature and gradient of temperature affect the natural frequencies of aluminum honeycomb plate. This study is carried out for temperature range between 200K and 800K, and gradient temperature (ΔT) across the thickness direction of the plate between [0-500K]. Different honeycomb plate geometries have been selected for the analysis, by changing the core thickness, skins thickness and cell size. The obtained results show that the effect of the temperature is noticeable. At temperature 800K, the natural frequencies decrease by 16.1% in comparison to their values at ambient temperature (300K). That means, high temperature makes the material suffers from weak rigidity, which furthermore contribute to high decrease of all the frequencies. In addition, investigations carried out in this work relate to the modal analysis of the honeycomb plate, under various gradients of temperature across the core of the plate. The obtained results show that the gradient of temperature has an effect on the modes of vibration of the honeycomb plate. This effect becomes significant when the gradient of temperature is very high. At ΔT equal 500K, the natural vibration modes decrease by 9.5% in comparison to the case where no gradient of temperature (ΔT = 0K) is applied between the two faces of the plate. Keywords: honeycomb panel; aluminum; natural frequency; finite element method; temperature.

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