Sensitivity Analysis of the Non-Linear Liouville Equation

2005 ◽  
pp. 601-606 ◽  
Author(s):  
Florian Seitz ◽  
Hansjörg Kutterer
Keyword(s):  
Sensitivity Analysis ◽  
Liouville Equation ◽  
Non Linear

scholarly journals Predictive modelling to support sensitivity analysis for robust design in aerospace engineering

2020 ◽  
Vol 61 (5) ◽  
pp. 2177-2192 ◽  
Author(s):  
Siva Krishna Dasari ◽  
Abbas Cheddad ◽  
Petter Andersson
Keyword(s):  
Sensitivity Analysis ◽  
Response Surface ◽  
Robust Design ◽  
Aerospace Engineering ◽  
Multivariate Adaptive Regression Splines ◽  
Linear Functions ◽  
Computational Time ◽  
Surface Modelling ◽  
Non Linear ◽  
Response Surface Modelling

AbstractThe design of aircraft engines involves computationally expensive engineering simulations. One way to solve this problem is the use of response surface models to approximate the high-fidelity time-consuming simulations while reducing computational time. For a robust design, sensitivity analysis based on these models allows for the efficient study of uncertain variables’ effect on system performance. The aim of this study is to support sensitivity analysis for a robust design in aerospace engineering. For this, an approach is presented in which random forests (RF) and multivariate adaptive regression splines (MARS) are explored to handle linear and non-linear response types for response surface modelling. Quantitative experiments are conducted to evaluate the predictive performance of these methods with Turbine Rear Structure (a component of aircraft) case study datasets for response surface modelling. Furthermore, to test these models’ applicability to perform sensitivity analysis, experiments are conducted using mathematical test problems (linear and non-linear functions) and their results are presented. From the experimental investigations, it appears that RF fits better on non-linear functions compared with MARS, whereas MARS fits well on linear functions.

scholarly journals Structural design sensitivity analysis in context of non-linear buckling

PAMM ◽  
2016 ◽  
Vol 16 (1) ◽  
pp. 711-712
Author(s):  
Lukas Radau ◽  
Nikolai Gerzen ◽  
Franz-Joseph Barthold
Keyword(s):  
Sensitivity Analysis ◽  
Structural Design ◽  
Design Sensitivity ◽  
Design Sensitivity Analysis ◽  
Linear Buckling ◽  
Non Linear

scholarly journals A Note on the Liouville Equation

1981 ◽  
Vol 36 (4) ◽  
pp. 417-418
Author(s):  
A. Grauel
Keyword(s):  
Lie Algebra ◽  
Liouville Equation ◽  
Curvature Form ◽  
Geometrical Features ◽  
Non Linear

We study some geometrical features of the non-linear scattering equations [1]. From this we deduce the Liouville equation. For that we interpret the SL(2, ℝ)-valued elements of the matrices in the scattering equations as matrix-valued forms and calculate the curvature 2-form with respect to a basis of the Lie algebra. We obtain the Liouville equation if the curvature form is equal to zero

Sensitivity Analysis to Flutter for Front Stages Compressor Blades

2015 ◽  
Author(s):  
Marcello Benvenuto ◽  
Andrea Silingardi ◽  
Pio Astrua ◽  
Stefano Cecchi
Keyword(s):  
Sensitivity Analysis ◽  
Travelling Wave ◽  
Operating Conditions ◽  
Mode Shapes ◽  
Elastic Behavior ◽  
Modal Shape ◽  
Compressor Blades ◽  
Flexural Mode ◽  
Non Linear ◽  
Heavy Duty Gas Turbine

Heavy duty gas turbine front stages compressor blades aero-elastic behavior is deeply analyzed and investigated by means of an uncoupled, non-linear and time-accurate CFD URANS solver. The travelling-wave approach and the energy method have been applied in order to assess the aerodynamic damping (in terms of logarithmic decrement) for each inter blade phase angle (IBPA) and thus to localize the flutter stability region. The work is mainly focused on a sensitivity analysis with respect to blade operating conditions, eigen-mode shapes and frequency in order to improve the understanding of flutter mechanism and to identify the key parameters. Transonic, supercritical and subsonic blades are investigated at different operating conditions with their corresponding eigenmode and eigen-frequency (first and second flexural mode and first torsional). The results show that non-linear effects can be neglected for subsonic blades. Besides, the modal-shape and the shock structure, if any, are identified to play a key role for flutter stability.

Incremental finite element sensitivity analysis for non-linear mechanics applications

1994 ◽  
Vol 37 (19) ◽  
pp. 3291-3308 ◽  
Author(s):  
Michal Kleiber ◽  
Tran Duong Hien ◽  
Eligiusz Postek
Keyword(s):  
Sensitivity Analysis ◽  
Finite Element ◽  
Non Linear ◽  
Non Linear Mechanics
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