Large deformation numerical analysis of plate anchor keying process

2015 ◽  
pp. 845-850
Author(s):  
Z Chen ◽  
K Tho ◽  
C Leung ◽  
Y Chow
Keyword(s):  
Numerical Analysis ◽  
Large Deformation ◽  
Plate Anchor

Numerical Analysis of Dynamic Compaction based on Large Deformation

2010 ◽  
Vol 168-170 ◽  
pp. 330-333
Author(s):  
Neng Gang Xie ◽  
Yun Chen ◽  
Ye Ye ◽  
Lu Wang
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Numerical Analysis ◽  
Large Deformation ◽  
Governing Equation ◽  
Dynamic Compaction ◽  
Iterative Calculation ◽  
Non Linear ◽  
The Relationship ◽  
Element Method

In the numerical analysis of foundation consolidation by using dynamic compaction, many kinds of non-linear conditions exist. This paper adopts large deformation on the relationship between strain and displacement. Non-linear governing equation of soil, based on finite element method, is established. Iterative calculation form is raised. Finally, non-linear numerical analysis is done to a calculation example.

scholarly journals Transonic Static Aeroelastic Numerical Analysis of Flexible Complex Configuration Wing

2021 ◽  
Vol 2021 ◽  
pp. 1-9
Author(s):  
Changrong Zhang ◽  
Hongtao Guo ◽  
Binbin Lv ◽  
Jun Zha ◽  
Li Yu
Keyword(s):  
Numerical Analysis ◽  
Large Deformation ◽  
Body Length ◽  
Small Diameter ◽  
Static Stability ◽  
Complex Configuration ◽  
Flight Performance ◽  
Design Point ◽  
Static Aeroelasticity ◽  
Lift Line

Diamond back wing is subjected to large deformation while gliding, which significantly changes characteristics of the lift as well as the static stability. For this reason, conventional rigid aircraft assumption cannot meet the requirements of the aerodynamic analysis of such aircrafts for accuracy. In this paper, based on CFD/CSD methods, the static aeroelasticity of a small diameter bomb with diamond back wing was studied. The results showed that static aeroelastic effects cause the slope of lift line to drop by 21% and the aerodynamic centre to move backwards by a 1.5% bomb body length, which will deviate the actual flight performance from the design point, thereby decreasing the cruise efficiency and the cruise range.

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