Coefficient of Restitution for Low Velocity Transverse Impact of Thin Graphite-Epoxy Laminates

1984 ◽  
Vol 6 (3) ◽  
pp. 112 ◽  
Author(s):  
WW Feng ◽  
KL Reifsnider ◽  
GP Sendeckyj ◽  
TT Chiao ◽  
GL Rodericks ◽  
...  
Keyword(s):  
Coefficient Of Restitution ◽  
Transverse Impact ◽  
Low Velocity

Experimental study on axially preloaded circular steel tubes subjected to low-velocity transverse impact

2018 ◽  
Vol 130 ◽  
pp. 161-175 ◽  
Author(s):  
Xu-Dong Zhi ◽  
Rong Zhang ◽  
Feng Fan ◽  
Chao Huang
Keyword(s):  
Experimental Study ◽  
Transverse Impact ◽  
Low Velocity ◽  
Steel Tubes

scholarly journals Ultrasonic Analysis of Damage in CFRP Resulting from Static Indentation and Low Velocity Impact

1993 ◽  
Vol 2 (3) ◽  
pp. 096369359300200
Author(s):  
H. Kaczmarek
Keyword(s):  
Impact Testing ◽  
Low Velocity Impact ◽  
Ultrasonic Tomography ◽  
Transverse Impact ◽  
Low Velocity ◽  
Velocity Impact ◽  
Testing Procedures ◽  
Damage Initiation ◽  
Static Indentation ◽  
The Impact

In order to reduce hidden damage caused in CFRP by low velocity transverse impact, testing procedures must be established by understanding the impact phenomena and the roles of various parameters on damage initiation and growth. Hence, composite plates were stressed and an original method, “ultrasonic tomography,” was applied to detect delaminations on the interfaces. The results show the similarity of the damage growth resulting from static indentation and low velocity impact.

Dynamic Response and Damage Mechanism of Two-Core Composite Sandwich Panels under Low-Velocity Impact

2013 ◽  
Vol 405-408 ◽  
pp. 2810-2814
Author(s):  
Chang Liang Li ◽  
Da Zhi Jiang ◽  
Jing Cheng Zeng ◽  
Su Li Xing
Keyword(s):  
Dynamic Response ◽  
Contact Force ◽  
Impact Energy ◽  
Sandwich Structures ◽  
Sandwich Panels ◽  
Damage Mechanism ◽  
The Other ◽  
Foam Core ◽  
Transverse Impact ◽  
Low Velocity

Dynamic response and damage mechanism of two-core sandwich panels with foam and honeycomb cores and glass fiber/epoxy composite sheets under low-velocity transverse impact are investigated. The emphasis is focused on the contact force response and crash mechanism of the two-core sandwich panels. Effects of configurations, impact energy levels and types of the cores on the dynamic response are investigated. A modified drop-test experiment is carried out to obtain contact force history of the two-core sandwich structures under different impact energies. The experimental results show that the 10:10 configurations for both honeycomb and foam core sandwich structures under lower impact energy absorb more impact energy than the other two structures. However, under higher impact energy, the honeycomb core sandwich structures of 15:5 configuration absorbs a little more impact energy than the other two, while for the foam core sandwich structures the 5:15 configuration shows a little better impact resistance. Results also show that when impact energy is low foam core sandwich structures do better in absorbing impact energy than the honeycomb ones.

scholarly journals Analytical Solutions to Predict Impact Behaviour of Stringer Stiffened Composite Aircraft Panels

2021 ◽  
Author(s):  
A. Chao Correas ◽  
A. Casares Crespo ◽  
H. Ghasemnejad ◽  
G. Roshan
Keyword(s):  
Impact Loading ◽  
Variable Stiffness ◽  
Impact Response ◽  
Low Velocity Impact ◽  
Analytical Models ◽  
Transverse Impact ◽  
Low Velocity ◽  
Mass System ◽  
Stiffened Panels ◽  
Velocity Impact

AbstractThis paper aims to develop an analytical method to predict the low-velocity impact response of simply supported stringer stiffened panels. Since the combination of stringer and panel provides aircraft structure with variable thicknesses, significant mathematical modelling is required to predict the transverse impact response of this type of designs. Within this analysis, the effect of variable stiffness distribution due to the stringer presence has been included. The performance of various layups is investigated to find the most suitable combination for panel-stringer laminate under impact loading. Analytical models were developed based on a spring-mass system to predict the dynamic behaviour of the striker-plate domain and, finally, determine the contact force history, which shows the main novelty of this research. Compared with Finite Element results, the model developed proved to successfully predict stringer stiffened composite panels' response with a range of layups and geometry designs under low-velocity impact loading conditions. The analytical results agree with the available data in the literature, and the error is less than 5%.

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