Simulation for the Bird-Strike Damage of Drone Radome Composite Structure

2012 ◽  
Vol 151 ◽  
pp. 305-309 ◽  
Author(s):  
Yan Bin He ◽  
Xiao Hu Yao ◽  
Xuan Liu ◽  
Ling Feng He
Keyword(s):  
Composite Structure ◽  
Impact Damage ◽  
Dynamic Responses ◽  
Composite Panel ◽  
Sandwich Composite ◽  
Bird Strike ◽  
Damage State ◽  
Element Analysis ◽  
Medium Speed ◽  
Maximum Impact Force

The low and medium speed bird-strike impact damage of sandwich composite structure of drone radome during takeoff and landing is examined by numerical simulations, using nonlinear dynamic finite element analysis software LS-DYNA. For different impact velocities, the aircraft radome’s dynamic responses are obtained and the damage in composite panel is clearly demonstrated. The relations of impact energy, maximum impact force and the damage state are analyzed. The simulation results can provide some references for the aircraft radome design.

The Damage of Sandwich Composite Structure of Aircraft Radome under Debris-Strike

2011 ◽  
Vol 63-64 ◽  
pp. 515-518 ◽  
Author(s):  
Xiao Qing Zhang ◽  
Xuan Liu
Keyword(s):  
Composite Structure ◽  
Impact Damage ◽  
Dynamic Responses ◽  
Composite Panel ◽  
Sandwich Composite ◽  
Damage State ◽  
Element Analysis ◽  
Medium Speed ◽  
Maximum Impact Force ◽  
Sandwich Composite Structure

The low and medium speed impact damage of sandwich composite structure of aircraft radome shield under debris-strike during takeoff and landing along runway is examined by numerical simulations, using nonlinear dynamic finite element analysis software LS-DYNA. For different impact velocities, the dynamic responses of aircraft radome shield are obtained and the damage in composite panel is clearly demonstrated. The relations of impact energy, maximum impact force and the damage state are analyzed. The simulation results can provide some references for the design of aircraft radome.

The FEM Analysis on the Damage of Wing Leading Edge under Hail Impact

2012 ◽  
Vol 460 ◽  
pp. 330-333
Author(s):  
Xiao Qing Zhang ◽  
Xuan Liu ◽  
Xiao Hu Yao
Keyword(s):  
Impact Damage ◽  
Leading Edge ◽  
Fem Analysis ◽  
Dynamic Responses ◽  
Composite Panel ◽  
Damage State ◽  
Maximum Displacement ◽  
Element Analysis ◽  
Medium Speed ◽  
Hail Impact

The low and medium speed impact damage of composite structure of wing leading edge under hail impact is examined by numerical simulations, using nonlinear dynamic finite element analysis software LS-DYNA. For different impact velocities, the dynamic responses of wing leading edge are obtained and the damage in composite panel is clearly demonstrated. The relations of impact energy, maximum displacement and the damage state are analyzed. The simulation results can provide some references for the design of wing leading edge.

A Study on Impact Damage Analysis of Composite Propeller Blade of Turboprop Aircraft

2013 ◽  
Vol 577-578 ◽  
pp. 489-492
Author(s):  
Hyun Bum Park
Keyword(s):  
Structural Design ◽  
Impact Damage ◽  
Fuel Efficiency ◽  
Carbon Dioxide Emission ◽  
Design Procedure ◽  
Aerodynamic Load ◽  
Bird Strike ◽  
Propeller Blade ◽  
Element Analysis ◽  
Commercial Code

Recently, the development need of environmental and fuel efficient aircrafts has been emphasized as an eco-friendly requirement in response to high oil prices. Accordingly, it is necessary to develop the next-generation eco-friendly and high fuel efficiency engine technology to enhance the fuel efficiency and aerodynamic performance of aircrafts for the purpose of reducing carbon dioxide emission amount prior to collecting and dealing with air pollution substances being discharged. In this study, development of the turboprop propeller blade for turboprop engine including aerodynamic and structural design and analysis was performed. The proposed propeller will be used as a candidate propeller for a regional aircraft which has been developed in Korea. Because the propeller for the target aircraft must endure the high bending and twisting moment loads during the flight operation, the high stiffness and strength carbon/epoxy composite material is used as a major structure materials. As a design procedure for the present study, firstly the structural design load is estimated through the aerodynamic load case analysis, and then flanges of spars from major bending loads and the skin from shear loads are initially sized using both the netting rule and the rule of mixture. In order to investigate the structure safety and stability, the structure analysis is carried out by finite element analysis using commercial code, MSC. NASTRAN. In addition, because the propeller should be safe against the bird strike, the bird strike phenomenon is analyzed using a commercial code, ANSYS.

A Computational Study on Residual Strength of Sandwich Composite Panel

2011 ◽  
Vol 393-395 ◽  
pp. 521-525 ◽  
Author(s):  
Sang Kyo Lee ◽  
Mohd. Zahid Ansari ◽  
Na Wang ◽  
Chong Du Cho
Keyword(s):  
Residual Strength ◽  
Computational Study ◽  
Static Condition ◽  
Composite Panel ◽  
Sandwich Composite ◽  
Element Analysis ◽  
Reinforced Plastic ◽  
Out Of Plane ◽  
Aluminum Honeycomb ◽  
Plane Direction

The present study investigates numerically the compressive residual strength of indented sandwich composite panel. The composite is made of carbon fiber reinforced plastic (CFRP) face sheets and aluminum honeycomb core. The sandwich is loaded under quasi-static condition and along out-of-plane direction. A commercial finite element analysis software ABAQUS is used. The results show that the indented composite retains significant amount of strength after indentation. And, the post-indentation strength of the composite is about 65% its pre-indentation strength under compression.

Study on Finite Element Model for Impact Damage of Composite Structure

2015 ◽  
Vol 752-753 ◽  
pp. 769-772
Author(s):  
Hyun Bum Park
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Composite Structure ◽  
Sandwich Structure ◽  
Impact Analysis ◽  
Impact Damage ◽  
Element Model ◽  
Sandwich Composite ◽  
The Impact ◽  
Element Method

In this work, study on impact damage FEM model of composite sandwich structure was performed. Sandwich structure configuration is made of carbon-epoxy face sheets and foam cores. From the finite element method analysis results of sandwich composite structure, it was confirmed that the results of analysis was reasonable. The velocity of impactor to initiate damage was estimated, and in order to investigate the damage at the predicted velocity, impact analysis using finite element method was performed. According to the impact analysis results of sandwich structure, it was confirmed that the damage was generated at the estimated impact velocity. Finally, the comparison of the numerical results with those measured by the experiment showed good agreement.

FEA of Dynamic Behavior of Top Hat Bonded Stiffened Composite Panel

2010 ◽  
Vol 446 ◽  
pp. 137-145 ◽  
Author(s):  
G. Mohamad ◽  
Mostapha Tarfaoui ◽  
Volker Bertram
Keyword(s):  
Dynamic Behavior ◽  
Dynamic Responses ◽  
Composite Panel ◽  
Stiffened Panel ◽  
Analysis Model ◽  
Cohesive Elements ◽  
Element Analysis ◽  
Finite Element Analysis Model ◽  
Impact Speed ◽  
2D Model

In this work the dynamic responses of bonded top hat stiffened panel have been studied by using finite element analysis model (Abaqus). A symmetrical 2D model was performed and used in the simulations. In the first part, dynamic behavior and impact speed effects at such composite structure have been studied. In the second part, other simulations were carried out by using cohesive elements proposed to predict the delamination might happen under such loading.

scholarly journals Online detection of barely visible low-speed impact damage in 3D-core sandwich composite structure

2018 ◽  
Vol 185 ◽  
pp. 646-655 ◽  
Author(s):  
Shirsendu Sikdar ◽  
Pawel Kudela ◽  
Maciej Radzieński ◽  
Abhishek Kundu ◽  
Wiesław Ostachowicz
Keyword(s):  
Composite Structure ◽  
Impact Damage ◽  
Sandwich Composite ◽  
Online Detection ◽  
Low Speed ◽  
Sandwich Composite Structure

A Study on the Bending Analysis of the Al Honeycomb Core Sandwich Composite Panel Bearing Large Bending Load

2013 ◽  
Vol 702 ◽  
pp. 245-252 ◽  
Author(s):  
Hong Gun Kim ◽  
Young Jun Kim ◽  
Hee Jae Shin ◽  
Sun Ho Ko ◽  
Hyun Woo Kim ◽  
...  
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Tensile Modulus ◽  
Composite Panel ◽  
Sandwich Composite ◽  
Test Results ◽  
Honeycomb Core ◽  
Element Analysis ◽  
Bending Load ◽  
The Finite Element Analysis

Al honeycomb core sandwich composite panels have different core and plate materials. The core is the Al honeycomb core, and the thin plate is GFRP sheets with fibers laminated in the 0°/90° symmetric structure. The Al honeycomb core sandwich composite panel is used for structures, which involve relatively high bending load. Before designing the structures, their stability is evaluated via the finite element analysis. In this study, an analysis method that is closest to the reality was proposed for designing the structures with Al honeycomb core sandwich composite panels. For that purpose, the modulus was reviewed. In the finite element analysis, the tensile modulus is generally used. In the results of this study, however, the tensile modulus led to significant deviations from the test results, whereas the bending modulus led to a closer value to the test results.

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