Nonlinear Dynamic Buckling of FGM Shallow Conical Shells under Triangular Pulse Impact Loads

2012 ◽  
Vol 460 ◽  
pp. 119-126
Author(s):  
Jie Lin ◽  
Chao Deng ◽  
Jia Chu Xu
Keyword(s):  
Dynamic Response ◽  
Governing Equation ◽  
Nonlinear Dynamic ◽  
Dynamic Buckling ◽  
Impact Loads ◽  
Nonlinear Dynamic Response ◽  
Conical Shells ◽  
Triangular Pulse ◽  
Response Equation ◽  
The Impact

In this paper, nonlinear dynamic buckling of FGM shallow conical shells under the action of triangular pulse impact loads are investigated. The nonlinear dynamic governing equation of symmetrically FGM shallow conical shells is built. Using Galerkin method, the nonlinear dynamic governing equation is solved, and the nonlinear dynamic response equation of symmetrically FGM shallow conical shells is obtained. The Runge-Kutta method is introduced to numerically solve the nonlinear dynamic response equation and the impact response curve is achieved. Budiansky-Roth motion criterion expressed by the displacement of the peak of the shell is employed to determine the critical impact buckling load. The influences of geometric parameters and gradient constants on impact buckling are discussed as well.

scholarly journals A Multi-Scale Approach for Nonlinear Dynamic Response Predictions With Fretting Wear

2016 ◽  
Author(s):  
J. Armand ◽  
L. Pesaresi ◽  
L. Salles ◽  
C. W. Schwingshackl
Keyword(s):  
Dynamic Response ◽  
Nonlinear Dynamic ◽  
Accurate Prediction ◽  
Fretting Wear ◽  
Contact Interface ◽  
Contact Conditions ◽  
Nonlinear Dynamic Response ◽  
Multi Scale ◽  
Highly Nonlinear ◽  
The Impact

Accurate prediction of the vibration response of aircraft engine assemblies is of great importance when estimating both the performance and the lifetime of its individual components. In the case of underplatform dampers, for example, the motion at the frictional interfaces can lead to a highly nonlinear dynamic response and cause fretting wear at the contact. The latter will change the contact conditions of the interface and consequently impact the nonlinear dynamic response of the entire assembly. Accurate prediction of the nonlinear dynamic response over the lifetime of the assembly must include the impact of fretting wear. A multi-scale approach that incorporates wear into the nonlinear dynamic analysis is proposed, and its viability is demonstrated for an underplatform damper system. The nonlinear dynamic response is calculated with a multiharmonic balance approach, and a newly developed semi-analytical contact solver is used to obtain the contact conditions at the blade-damper interface with high accuracy and low computational cost. The calculated contact conditions are used in combination with the energy wear approach to compute the fretting wear at the contact interface. The nonlinear dynamic model of the blade-damper system is then updated with the worn profile and its dynamic response is recomputed. A significant impact of fretting wear on the nonlinear dynamic behaviour of the blade-damper system was observed, highlighting the sensitivity of the nonlinear dynamic response to changes at the contact interface. The computational speed and robustness of the adopted multi-scale approach are demonstrated.

scholarly journals A Multiscale Approach for Nonlinear Dynamic Response Predictions With Fretting Wear

2016 ◽  
Vol 139 (2) ◽  
Author(s):  
J. Armand ◽  
L. Pesaresi ◽  
L. Salles ◽  
C. W. Schwingshackl
Keyword(s):  
Dynamic Response ◽  
Nonlinear Dynamic ◽  
Accurate Prediction ◽  
Fretting Wear ◽  
Multiscale Approach ◽  
Contact Interface ◽  
Contact Conditions ◽  
Nonlinear Dynamic Response ◽  
Highly Nonlinear ◽  
The Impact

Accurate prediction of the vibration response of aircraft engine assemblies is of great importance when estimating both the performance and the lifetime of their individual components. In the case of underplatform dampers, for example, the motion at the frictional interfaces can lead to a highly nonlinear dynamic response and cause fretting wear at the contact. The latter will change the contact conditions of the interface and consequently impact the nonlinear dynamic response of the entire assembly. Accurate prediction of the nonlinear dynamic response over the lifetime of the assembly must include the impact of fretting wear. A multiscale approach that incorporates wear into the nonlinear dynamic analysis is proposed, and its viability is demonstrated for an underplatform damper system. The nonlinear dynamic response is calculated with a multiharmonic balance approach, and a newly developed semi-analytical contact solver is used to obtain the contact conditions at the blade–damper interface with high accuracy and low computational cost. The calculated contact conditions are used in combination with the energy wear approach to compute the fretting wear at the contact interface. The nonlinear dynamic model of the blade–damper system is then updated with the worn profile and its dynamic response is recomputed. A significant impact of fretting wear on the nonlinear dynamic behavior of the blade–damper system was observed, highlighting the sensitivity of the nonlinear dynamic response to changes at the contact interface. The computational speed and robustness of the adopted multiscale approach are demonstrated.

Nonlinear Dynamic Response of Elastically Supported Stiffened Plates with Initial Stresses and Geometric Imperfections Under Impact Loads

2020 ◽  
Vol 20 (04) ◽  
pp. 2050053
Author(s):  
Niu-Jing Ma ◽  
Li-Xiong Gu ◽  
Long Piao
Keyword(s):  
Dynamic Response ◽  
Nonlinear Dynamic ◽  
Dynamic Properties ◽  
Initial Stresses ◽  
Stiffened Plates ◽  
Impact Loads ◽  
Stiffened Plate ◽  
Geometric Imperfections ◽  
Nonlinear Dynamic Response ◽  
Elastically Supported

This paper deals with the nonlinear dynamic response of elastically supported stiffened plates with initial stresses under impact loads. A stiffened plate is assumed to be composed of a plate with some stiffeners, which are treated separately. The plate is modeled by the thin plate theory, whereas the stiffeners are considered as geometrically nonlinear Euler–Bernoulli beams. First, the equations of both the kinetic energies and strain energies of the plate and stiffeners are established. Then, the dynamic equilibrium equations for the stiffened plate are derived as the Lagrange’s equation of the functional. A parametric analysis is performed to evaluate how initial stresses, initial geometric imperfections, elastic supports, impact loads and configuration of stiffeners affect the time-history responses of the stiffened plates. Some useful nonlinear dynamic properties are obtained, which serve as references for engineering design and application.

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