Extension of an Euler/Navier-Stokes aeroelastic analysis method for shell structures

1998 ◽  
Author(s):  
A. Lewis ◽  
M. Smith
Keyword(s):  
Shell Structures ◽  
Navier Stokes ◽  
Analysis Method ◽  
Aeroelastic Analysis

scholarly journals Static Aeroelastic Characteristics of Morphing Trailing-Edge Wing Using Geometrically Exact Vortex Lattice Method

2019 ◽  
Vol 2019 ◽  
pp. 1-15
Author(s):  
Sen Mao ◽  
Changchuan Xie ◽  
Lan Yang ◽  
Chao Yang
Keyword(s):  
Vortex Lattice ◽  
Deflection Angle ◽  
Aircraft Design ◽  
Analysis Method ◽  
Lattice Method ◽  
Trailing Edge ◽  
Vortex Lattice Method ◽  
Analysis And Design ◽  
Aeroelastic Analysis ◽  
Typical Model

A morphing trailing-edge (TE) wing is an important morphing mode in aircraft design. In order to explore the static aeroelastic characteristics of a morphing TE wing, an efficient and feasible method for static aeroelastic analysis has been developed in this paper. A geometrically exact vortex lattice method (VLM) is applied to calculate the aerodynamic forces. Firstly, a typical model of a morphing TE wing is chosen and built which has an active morphing trailing edge driven by a piezoelectric patch. Then, the paper carries out the static aeroelastic analysis of the morphing TE wing and corresponding simulations were carried out. Finally, the analysis results are compared with those of a traditional wing with a rigid trailing edge using the traditional linearized VLM. The results indicate that the geometrically exact VLM can better describe the aerodynamic nonlinearity of a morphing TE wing in consideration of geometrical deformation in aeroelastic analysis. Moreover, out of consideration of the angle of attack, the deflection angle of the trailing edge, among others, the wing system does not show divergence but bifurcation. Consequently, the aeroelastic analysis method proposed in this paper is more applicable to the analysis and design of a morphing TE wing.

Phase-Lagged Boundary Condition Methods for Aeroelastic Analysis of Turbomachines: A Comparative Study

1999 ◽  
Author(s):  
R. Srivastava ◽  
Milind A. Bakhle ◽  
Theo G. Keith ◽  
G. L. Stefko
Keyword(s):  
Boundary Condition ◽  
Comparative Study ◽  
Decomposition Method ◽  
Decomposition Methods ◽  
Navier Stokes ◽  
Fourier Decomposition ◽  
Computational Costs ◽  
Aeroelastic Analysis ◽  
Study Results ◽  
Time Marching

In the present work a comparative study of phase-lagged boundary condition methods is carried out. The relative merits and advantages of time-shifted and the Fourier decomposition methods are compared. Both methods are implemented in a time marching Euler/Navier-Stokes solver and are applied to a flat plate helical fan with harmonically oscillating blades to perform the study. Results were obtained for subsonic as well as supersonic inflows. Results for subsonic inflow showed good comparisons with published results and between the two methods along with comparable computational costs. For the supersonic inflow, despite the presence of shocks at the periodic boundary results from both the methods compared well, however, Fourier decomposition method was computationally more expensive. For linear flowfield Fourier decomposition method is best suited, especially for work-station environment. The time-shifted method is better suited for CRAY category of computers where fast input-output devices are available.

scholarly journals Transfer Path Analysis and Contribution Evaluation Using SVD- and PCA-Based Operational Transfer Path Analysis

2020 ◽  
Vol 2020 ◽  
pp. 1-23
Author(s):  
Wei Cheng ◽  
Diane Blamaud ◽  
Yapeng Chu ◽  
Lei Meng ◽  
Jingbai Lu ◽  
...  
Keyword(s):  
Path Analysis ◽  
Principal Component ◽  
Structure Design ◽  
Shell Structures ◽  
Analysis Method ◽  
Transfer Path ◽  
Frequency Components ◽  
Transfer Path Analysis ◽  
Value Decomposition ◽  
Traditional Counterpart

To quantitatively identify the transfer paths and evaluate path contributions of shell structures, an singular value decomposition- (SVD-) and principal component analysis- (PCA-) based operational transfer path analysis method is constructed and studied in this paper. Firstly, SVD is used to determine the contribution of each path and reduce crosstalk. Secondly, PCA is applied to reduce the influence of unwanted frequency components and thus reduce noises. This allows the presented OTPA to be more accurate than its traditional counterpart. Once the transmissibility function is obtained, the response synthesis is determined, and the transfer path analysis and path contribution evaluation can be effectively carried out. Numerical and experimental case studies are carried out to validate and test the performance of the presented method. Furthermore, a comprehensive observing the influences of correlation between sources and distance of sources and receiver is also provided. Generally, this paper provides accurate transfer path analysis and path contributions for mechanical systems, which can benefit vibration and noise monitoring and reduction through vibration reduction structure design for new equipment or vibration damping on the major vibration transfer paths for current equipment.

Efficient Aeroelastic Analysis Method Including Inverse Design for Body Effects

2009 ◽  
Vol 46 (6) ◽  
pp. 2164-2169
Author(s):  
Seung-Jun Lee ◽  
Dong-Kyun Im ◽  
Myung-Koo Kang ◽  
In Lee ◽  
Jang-Hyuk Kwon
Keyword(s):  
Inverse Design ◽  
Analysis Method ◽  
Aeroelastic Analysis

Dynamic Instability of a Cylindrical Shell Structure Subjected to Horizontal and Vertical Excitations Simultaneously

2004 ◽  
Author(s):  
Katsuhisa Fujita ◽  
Taisuke Nosaka ◽  
Tomohiro Ito
Keyword(s):  
Cylindrical Shell ◽  
Dynamic Stability ◽  
Parametric Excitation ◽  
Dynamic Instability ◽  
Simulation Analysis ◽  
Seismic Analysis ◽  
Shell Structures ◽  
Analysis Method ◽  
Water Tanks ◽  
Vertical Excitations

Many structures such as support columns such as those for elevated expressways and towers tend to become larger and more flexible recently, thus the buckling or collapse of these structures is considered to easily occur than ever due to huge earthquakes. Actually, in the Hyogo-ken Nambu earthquake in Japan, buckling phenomena of tall support columns were observed every-where. Therefore, the evaluation technology on the dynamic stability is very important in order to ensure the seismic design reliability for these structures. The authors have ever studied the effects of the horizontal and vertical simultaneous excitations on the above-mentioned buckling phenomena of support columns experimentally. More-over, they also investigated the fundamental phenomena of the dynamic stability of the support columns subjected to the horizontal and vertical excitations simultaneously by numerical simulations using an analytical model where the support column is treated as a tall elastic cantilever beam. The purpose of this paper is on the dynamic instability, that is dynamic buckling, of a cylindrical shell structures such as those for elevated expressways, towers, containment vessels, LNG tanks and water tanks in various industrial plants so on subjected to horizontal and vertical excitations simultaneously. The coupled motion of equation with horizontal and vertical excitations simultaneously for these cylindrical shell structures is derived in this paper, and this modeling is shown to become a Mathieu type’s parametric excitation. The numerical simulation analysis is carried out for a cylindrical shell model with an attached mass on its tip. Comparing with the classical seismic analysis method, this proposed dynamic instability analysis method shows the larger deformation in horizontal direction due to the parametric excitation of the vertical seismic wave. As the results, the structures are apt to lose the structural stability more due to the coupling effects between the horizontal and vertical seismic simultaneous loadings.

scholarly journals Aeroelastic Analysis of a Typical Section using Euler and Navier-Stokes Mesh-less Method

2016 ◽  
Vol 23 (1) ◽  
pp. 194-205
Author(s):  
S. Sattarzadeh ◽  
A. Jahangirian ◽  
H. Shahverdi
Keyword(s):  
Navier Stokes ◽  
Aeroelastic Analysis ◽  
Mesh Less
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