Thermo-mechanical behavior and bulk texture studies on AA5052-H32 under dynamic compression

Pare, Vinod; Modi, Sahil; Jonnalagadda, Krishna

doi:10.1016/j.msea.2016.05.019

Cited by 20 publications

(3 citation statements)

References 74 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Also, Pare et al. [23] experiments on Al 5052-H32 alloy showed similar behavior in a wide range of strain rates according to Figure 3. They selected the strain rate of 2400 s −1 as reference strain rate by extracting the Johnson-Cook equation parameters.…”

Section: Modelingmentioning

confidence: 52%

“…[22] and Pare et al. [23], the reference strain rate was reported as 100 s−1 and 2400 s −1 , respectively. Therefore to apply the strain-rate effects on the behavior of Al 5052-H38 in this study, as the reported values are approximate according to Figure 3, the value of 1000 s-1 was chosen as the reference strain rate in the Johnson-Cook equation taking into account both reported values.…”

Section: Modelingmentioning

confidence: 99%

“…The C value is also set equal to 0.135, as reported by Pare et al. [23]. Using these parameters, the second term of Johnson-Cook equation is calculated in various strain rates and directly multiplied on the hardening curve of Figure 4 as the first coefficient of Johnson-Cook equation.…”

Section: Modelingmentioning

confidence: 99%

See 2 more Smart Citations

Numerical modeling of high velocity impact in sandwich panels with honeycomb core and composite skin including composite progressive damage model

Khodaei

Haghighi‐Yazdi

Safarabadi

2018

Jnl of Sandwich Structures & Materials

View full text Add to dashboard Cite

In this paper, a numerical model is developed to simulate the ballistic impact of a projectile on a sandwich panel with honeycomb core and composite skin. To this end, a suitable material model for the aluminum honeycomb core is used taking the strain-rate dependent properties into account. To validate the ballistic impact of the projectile on the honeycomb core, numerical results are compared with the experimental results available in literature and ballistic limit velocities are predicted with good accuracy. Moreover, to achieve composite skin material model, a VUMAT subroutine including damage initiation based on Hashin’s seven failure criteria and damage evolution based on MLT approach modulus degradation is used. To validate the composite material model VUMAT subroutine, the ballistic limit velocities of the projectile impact on the composite laminates are predicted similar to the numerical results presented by other researchers. Next, the numerical model of the sandwich panel ballistic impact at different velocities is compared with the available experimental results in literature, and energy absorption capacity of the sandwich panel is predicted accurately. In addition, the numerical model simulated the sandwich panel damage mechanisms in different stages similar to empirical observations. Also, the composite skin damages are investigated based on different criteria damage contours.

show abstract

Section: Modelingmentioning

confidence: 52%