Impact damage imaging in a curved composite panel with wavenumber index via Riesz transform

2018 ◽  
Author(s):  
Huan-Yu Chang ◽  
Fuh-Gwo Yuan
Keyword(s):  
Impact Damage ◽  
Riesz Transform ◽  
Composite Panel ◽  
Damage Imaging

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.

scholarly journals Determination of strength criteria on conditions of visual testability of impact damage in composite aircraft constructions

2019 ◽  
Vol 22 (6) ◽  
pp. 86-99
Author(s):  
S. V. Dubinskiy ◽  
Yu. M. Feygenbaum ◽  
V. Ya. Senik
Keyword(s):  
Composite Materials ◽  
Polymer Composite ◽  
Impact Damage ◽  
Bootstrap Method ◽  
Defect Size ◽  
Polymer Composite Materials ◽  
Composite Panel ◽  
Weibull Function ◽  
Operational Factors

One of the principal criteria of aircraft composite design strength on the conditions of damage tolerance is the minimum defect size of accidental impact damage that is sure to be located during regular maintenance checks. Construction strength with similar (BVID – Barely Visible Impact Damage) and smaller damages must be ensured under design load. The analysis of operational factors affecting the criterion value is conducted in the paper. The effects of personnel qualification, surface color, level of contamination, distance to the object as well as defect size variations during the time due to relaxation of inner strains in the damaged construction were studied.Research was carried out using 90 carbon fiber three stinger panels of different color and contamination levels which were subject to impact damages by a 25 mm spherical striker. Totally 80 blows were struck when applying energy within the range of 3–107 J. In the visual damage detectability test under different conditions 42 experts were participated including 25 airlines inspectors. For the statistical analysis of empirical data and determination of dependence for the damage detection probability on its size, the Weibull function was utilized. Determination of BVID size using "90/95" criterion was performed by means of the bootstrap method (95% of inspectors must detect not less than 90% of defects with the size not smaller than BVID). The results obtained in this study enabled to access the degree of various operational factors impact on reliability of damage detectability during the visual inspection and determine BVID values depending on the combination of the given factors. In particular, it was demonstrated that from all the viewing distances the defects in polymer composite materials are more detectable on the blue surface than on the gray and red ones. Conducted research demonstrated a significant effect of relaxation (the reduction effect of the surface defect sizes in the composite panel affected by different factors during time span) on the probability of defect detectability during operation. Also water saturation of the construction under excessive temperatures has the critical compared with other factors impact on relaxation of damages in polymer composite materials. The obtained results accord with the data in foreign publications making them more supplement and specific. On the basis of conducted research the entire range of recommendations for aircraft designers and operators utilizing composite constructions is formulated. 

Numerical and experimental investigations of compressed stiffened composite panel with local impact damage

2018 ◽  
Vol 1 (2) ◽  
pp. 99-107
Author(s):  
A. A. Ryabov ◽  
O. V. Voronkov ◽  
S. V. Suhov ◽  
D. Y. Strelets ◽  
V. G. Slobodchikov
Keyword(s):  
Impact Damage ◽  
Composite Panel ◽  
Experimental Investigations ◽  
Local Impact

scholarly journals Novel Method for Strength Analysis of Damaged High-Loaded Composite Panel

2019 ◽  
Vol 304 ◽  
pp. 01019
Author(s):  
Mikhail Levchenkov ◽  
Alexander Shanygin ◽  
Ivan Mareskin
Keyword(s):  
Composite Structures ◽  
Finite Element Modelling ◽  
Impact Damage ◽  
Composite Panel ◽  
Strength Analysis ◽  
Automatic Mode ◽  
Reinforced Composite ◽  
Parametric Studies ◽  
Novel Method ◽  
Automated Methods

The paper is devoted to the creation of automated methods for calculating the strength of composite structures, taking into account the influence of impact damage and temperature effects in the range from -600 to +600. To solve this problem, a program for automated finite element modelling of a typical reinforced composite panel was created. Program allows to conduct parametric studies of strength and stability in an automatic mode, to model panel impact damage and to parameterize the temperature dependence of the strength of a composite. Using this method, results were obtained on the strength and stability of the panel in the temperature range and in various damage parameters.

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.

Effect of impact damage positions on the buckling and post-buckling behaviors of stiffened composite panel

2016 ◽  
Vol 155 ◽  
pp. 184-196 ◽  
Author(s):  
Yu Feng ◽  
Haoyu Zhang ◽  
Xiangfei Tan ◽  
Yuting He ◽  
Tao An ◽  
...  
Keyword(s):  
Impact Damage ◽  
Composite Panel ◽  
Post Buckling
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