“…In open literature several works report the appearance of three distinct velocity regimes that occur during the impact of metal specimens [32,33,48,49]. The first is typical of small impact velocities, with the perforation being dominated by the petalling of the target.…”
This work presents an investigation on the damage and high-speed impact deformation mechanisms at elevated temperatures in honeycomb sandwich panels made from PM1000 and PM2000 alloys. The impact temperatures ranged from 22°C to 866°C. The investigation was performed experimentally using a custom-made gas gun rig, and by using Finite Element and developing a phenomenological analytical model to predict the residual velocity and ballistic limit equations for the case in which the diameter of the projectile is close or smaller to the honeycomb cell length. The sizes of the holes have been also evaluated by carrying out numerical thermal loading simulations on honeycomb sandwich specimen models impacted at high speed. The predictions provided by the Finite Elements and the analytical model give a good agreement with the results from the experimental tests. The hole diameters for the two idealized normal impact cases, in which the projectile hits the cell core and at the triple-wall intersection of the core, were also presented as a function of the projectile diameter and velocity in this paper.
“…In open literature several works report the appearance of three distinct velocity regimes that occur during the impact of metal specimens [32,33,48,49]. The first is typical of small impact velocities, with the perforation being dominated by the petalling of the target.…”
This work presents an investigation on the damage and high-speed impact deformation mechanisms at elevated temperatures in honeycomb sandwich panels made from PM1000 and PM2000 alloys. The impact temperatures ranged from 22°C to 866°C. The investigation was performed experimentally using a custom-made gas gun rig, and by using Finite Element and developing a phenomenological analytical model to predict the residual velocity and ballistic limit equations for the case in which the diameter of the projectile is close or smaller to the honeycomb cell length. The sizes of the holes have been also evaluated by carrying out numerical thermal loading simulations on honeycomb sandwich specimen models impacted at high speed. The predictions provided by the Finite Elements and the analytical model give a good agreement with the results from the experimental tests. The hole diameters for the two idealized normal impact cases, in which the projectile hits the cell core and at the triple-wall intersection of the core, were also presented as a function of the projectile diameter and velocity in this paper.
“…Several versions of the ballistic limit equation have been developed for Whipple structures, of which we select the modified Cour-Plais/Christiansen damage equations by Reimerdes et al. [16] for comparison. This is a modification of Cour-Plais/Christiansen ballistic limit equation and the modifications allow to consider the bumper shield thickness also for higher velocities.…”
Section: Simulation Modelingmentioning
confidence: 99%
“…ballistic regime, shatter regime and melt/vaporize regime. Important structure physical and material properties are included in the ballistic limit equations and the equations go as follows Figure 4.Comparison of modified Cour-Plais/Christiansen ballistic limit curve [16] (above the curve: theoretical penetration; below the curve: theoretical no penetration; on the curve: theoretical critical penetration) with numerical simulation results for Whipple structure of 0.2 cm Al bumper followed at 10 cm by 0.3 cm Al rear wall.…”
The stuffed corrugated sandwich structure was proposed for the application in the protection of the spacecraft against orbital debris. In order to investigate the protection properties of the stuffed corrugated sandwich structure under hypervelocity impact, numerical simulations were carried out to analyze the impact characteristics. The hypervelocity impact process was presented and the properties such as shock waves propagation, energy absorption, and expansion of the debris cloud were discussed; corresponding properties of mass equal Whipple structure under impact were analyzed for comparison. The results illustrate the protection mechanism of the stuffed corrugated sandwich subject to hypervelocity impact and show that it has superior protection performance to monolithic plate, which prove that the stuffed corrugated sandwich structure has potentially broad application prospect in the field of spacecraft protection against the orbital debris. The research can provide reference for the design of protection shield of the spacecraft.
“…With the modification by Reimerdes made in an ESA/ESTEC technology study and additional work [Wohlers, 2003], [Reimerdes, 2006] modified Cour-Palais/Christiansen equations are given for double wall structures allowing optimization.…”
Section: Ballistic Limit Equations For Optimizationmentioning
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