scholarly journals Effect of Elastic Modulus on Maximum Displacement Response of Truss Structure

2019 ◽  
Author(s):  
Xin-yang CHEN ◽  
Zu-ping MENG
Keyword(s):  
Elastic Modulus ◽  
Truss Structure ◽  
Maximum Displacement ◽  
Displacement Response

Simulation of sub-micron indentation tests with spherical and Berkovich indenters

2001 ◽  
Vol 16 (7) ◽  
pp. 2149-2157 ◽  
Author(s):  
A. C. Fischer-Cripps
Keyword(s):  
Experimental Data ◽  
Elastic Modulus ◽  
Material Properties ◽  
Indentation Testing ◽  
Depth Sensing ◽  
Displacement Response ◽  
Analysis Methods ◽  
Detailed Treatment ◽  
Indentation Tests ◽  
Load Displacement

The present work is concerned with the methods of simulation of data obtained from depth-sensing submicron indentation testing. Details of analysis methods for both spherical and Berkovich indenters using multiple or single unload points are presented followed by a detailed treatment of a method for simulating an experimental load–displacement response where the material properties such as elastic modulus and hardness are given as inputs. A comparison between simulated and experimental data is given.

Dynamic Response Analysis for the Solar-Powered Aircraft Composite Wing Panel with Viscoelastic Damping Layer

2011 ◽  
Vol 105-107 ◽  
pp. 491-494
Author(s):  
Tie Jun Liu ◽  
Yong Zhang ◽  
Gang Li ◽  
Feng Hui Wang
Keyword(s):  
Dynamic Response ◽  
Vibration Isolation ◽  
Viscoelastic Damping ◽  
Response Analysis ◽  
Aircraft Wing ◽  
Maximum Displacement ◽  
Displacement Response ◽  
Stiffened Structures ◽  
Solar Powered ◽  
Wing Panel

In design of solar powered aircraft wing panel, vibration properties of wing panel should be considered, especially for the peak value of dynamic response. In this research, a viscoelastic damping layer is built for vibration isolation, wing panel finite element models of stiffened and no-stiffened structures base on fiber-reinforced laminates with damping layer in the middle are built. Natural frequency and displacement response are analyzed with different thickness of damping layer and structures. Result shows natural frequencies decrease as thickness increased, and that of laminates are lower than stiffened structure. The maximum displacement response value decreased when thickness increased and that of laminates is higher than structured with stiffer. The presented work is helpful for type selection and designing of solar powered aircraft wing panel.

The Effect of Cable Material Characteristics on Suspendome

2010 ◽  
Vol 156-157 ◽  
pp. 1251-1255 ◽  
Author(s):  
Zhi Hua Chen ◽  
Guo Jun Sun ◽  
Zhan Sheng Liu
Keyword(s):  
Elastic Modulus ◽  
High Temperature ◽  
Low Temperature ◽  
Expansion Coefficient ◽  
Linear Expansion ◽  
Steel Structure ◽  
Linear Expansion Coefficient ◽  
Maximum Displacement ◽  
Material Characteristics ◽  
Prestressed Steel Structure

Cable is the key component in the prestressed steel structure. In order to study the effect of cable elastic modulus and expansion coefficient on the prestressed steel structure, Suspendome of Tianbao Center was taken as the research object and APDL language is applied to write a corresponding program, thereby carrying out analysis to the model; The results indicate that the change of cable expansion coefficient and cable elastic modulus have a different effect on the performance of the suspendome: at high temperature, the effect of the expansion coefficient of hoop cable and radial cable is larger on the maximum displacement; at low temperature, the effect of the elastic modulus of hoop cable is larger on the support constrained force. Therefore, it is necessary to give precise linear expansion coefficient and elastic modulus for different cables.

Use of combined elastic modulus in depth-sensing indentation with a conical indenter

2003 ◽  
Vol 18 (5) ◽  
pp. 1043-1045 ◽  
Author(s):  
A. C. Fischer-Cripps
Keyword(s):  
Elastic Modulus ◽  
Test Data ◽  
Data Use ◽  
Indentation Test ◽  
Indentation Testing ◽  
Depth Sensing ◽  
Conical Indenter ◽  
Displacement Response ◽  
Conventional Methods ◽  
Elastic Unloading

Conventional methods of analysis for depth-sensing indentation test data use the slope of the elastic unloading portion of the load–displacement response in conjunction with the elastic equations of contact for a rigid cone. It is common practice to incorporate the combined modulus of the indenter and specimen in these equations although the validity of this practice never appears to have been verified. This work demonstrates the validity of using the combined elastic modulus in depth-sensing indentation testing in conjunction with the elastic equations of contact for a conical indenter.

Air Compressor Plate Drum’s Reliability Analysis

2011 ◽  
Vol 217-218 ◽  
pp. 1483-1487
Author(s):  
Xiao Ying Li ◽  
Yan Bin Han
Keyword(s):  
Finite Element ◽  
Elastic Modulus ◽  
Angular Velocity ◽  
Normal Distribution ◽  
Random Input ◽  
Output Variable ◽  
Maximum Displacement ◽  
Air Compressor ◽  
Input Variables ◽  
Element Theory

Based on the finite element theory, air compressor plate drum is analyzed in the rotating and loading circumstances. The maximum displacement sum was regarded as a random output variable, when plate angular velocity the elastic modulus, Poisson’s ratio density and equivalent centrifugal force were randomized, and were considered as a random input variable. Supposed all input variables are normal distribution. After Monto Carlo sampling is implemented one thousand times, the reliability and sensitivity of air compressor plate drum can be obtained.

The Optimization of Damping of Four Configurations of a Vibrating Uniform Beam

1963 ◽  
Vol 85 (3) ◽  
pp. 259-264 ◽  
Author(s):  
Alex Henney ◽  
J. P. Raney
Keyword(s):  
Digital Computer ◽  
Empirical Formula ◽  
Response Curves ◽  
Maximum Displacement ◽  
Single Degree Of Freedom ◽  
Displacement Response ◽  
Single Degree ◽  
Uniform Beam ◽  
Computer Response ◽  
Analytical Expressions

Approximate analytical expressions for optimum damping for four configurations of forcing and damping a uniform beam were evaluated and the displacement responses for optimum damping values obtained from these expressions were calculated by a digital computer. It was found that the responses were accurately optimized. The sensitivity of maximum displacement response to deviation from optimum damping was investigated, but no analytical expressions relating change to deviation were obtained. An empirical formula, based upon consideration of the response of the beam as a single-degree-of-freedom system, was shown to be a good approximation of results obtained from the computer response curves. The four configurations investigated were relatively insensitive to changes in damping from optimum.

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