Multi-layer insulation material models suitable for hypervelocity impact simulations

White, D.M.; Wicklein, M.; Clegg, R.A.; Nahme, H.

doi:10.1016/j.ijimpeng.2008.07.017

Cited by 13 publications

(7 citation statements)

References 5 publications

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“…An advanced material model defines the FRP composite material. 20,21 By separating the entire strain into deviatoric and volumetric strain components, the constitutive relation of composite has been modified to examine the nonlinear compressibility effect during a ballistic impact. The modified Hashin's criterion control the damage initiation criterion by incorporating out-of-plane shear stresses coupled with the in-plane stresses.…”

Section: Materials Modelsmentioning

confidence: 99%

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Effect of projectile’s nose shape on ballistic performance of ceramic/composite armour: A numerical study

Biswas

Datta

2023

Proceedings of the Institution of Mechanical Engineers, Part C:

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In the present study, finite element analysis were carried out to investigate the ballistic performance of Al2O3-Kevlar 29/epoxy armour system impacted by a 4340 steel projectile. The perforation capacity of a 10 mm thick target was studied against a blunt, ogive, and conical shaped projectile with a fixed diameter and mass of 7.56 mm and 10.7 gm, respectively. The simulations were carried out in Ansys/Autodyn by considering the projectile as a deformable body. The variation of the ballistic limit velocity (BLV) and energy, progressive damage of the target, and projectile deformation were studied comprehensively. It was found that the nose configuration of the projectile significantly influence the target’s ballistic performance. The perforation capacity of the blunt projectile was lower than the ogive and conical shape in all the velocity regimes. At higher impact velocity ( Vi >600 m/s), the target’s resistance was better against the ogive projectile than that of the sharp conical projectile. Interestingly, this phenomenon got reversed when the incident velocity nears the ballistic limit. Also, from the simulation results, it has been possible to obtain the optimum thicknesses of the components for a given total thickness of the armour.

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Section: Materials Modelsmentioning

confidence: 99%

“…In the present study, an advanced material model has been used, which was presented in Hayhurst et al 20 and Hiermaier et al, 21 to define composite laminate that couples constitutive relation with the non-linear equation of state (EOS). According to this model the anisotropic composite is considered to be an orthotropic material.…”

Section: Materials Modelsmentioning

confidence: 99%

Effect of projectile’s nose shape on ballistic performance of ceramic/composite armour: A numerical study

Biswas

Datta

2023

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…One widely known example of this effect is the Whipple shield where the spacecraft multilayer insulation is spaced off the underlying body panels. The benefits of this approach are discussed in the JSC MMOD Handbook [4] and a variety of other papers [17,18]. A similar effect happens in solid structures with layers.…”

Section: Spacecraft Protection Guidelinesmentioning

confidence: 99%

A review of the Solar Probe Plus dust protection approach

Mehoke

Brown

Swaminathan³

et al. 2012

2012 IEEE Aerospace Conference

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The Solar Probe Plus (SPP) spacecraft will go closer to the Sun than any manmade object has gone before, which has required the development of new thermal and micrometeoroid protection technologies. During the 24 solar orbits of the mission, the spacecraft will encounter a thermal environment that is 50 times more severe than any previous spacecraft. It will also travel through a dust environment previously unexplored, and be subject to particle hypervelocity impacts (HVI) at velocities much larger than anything previously encountered. New analytical methodologies and designs have been developed to meet this environment's extreme micrometeoroid protection challenge while also fulfilling the mission's low mass requirement. These new analytical capabilities and protection system concepts could produce similar benefits if applied to Earth orbiting and deep space missions.The SPP dust study was developed to overcome the velocity limitations in the existing micrometeoroid and orbital debris (MMOD) analysis capability. In this study, we developed the hydrocode modeling techniques needed to characterize the material behaviors for a high-shock particle impact event. An additional novel development was an algorithm to calculate the particle flux on specific spacecraft surfaces. Our approach predicts particle impacts for a given spacecraft geometry, including the aforementioned effects. In addition, our approach introduces a size-velocity particle correlation, which lowers the shielding needed for a given protection level. This paper covers the new analytical capabilities developed for the SPP dust environment and how they dramatically lower the mass of the protective systems. The paper also discusses the application of these new analytical capabilities to spacecraft protection in the LEO debris field.

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“…In many missions, CFRP-Al/HC is covered by MLI (multi layer insulation) to control the thermal environment of the spacecraft. The mechanical behaviour of MLI under HVI and its influence on the impact process was also investigated and is presented in a separate paper [4].…”

Section: Wicklein Et Al / International Journal Of Impact Engineeringmentioning

confidence: 99%

Hypervelocity impact on CFRP: Testing, material modelling, and numerical simulation

Wicklein

Ryan

White³

et al. 2008

International Journal of Impact Engineering

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This paper describes the derivation and validation of a numerical material model that predicts the highly dynamic behaviour of CFRP (carbon fibre reinforced plastic) under hypervelocity impact. CFRP is widely used in satellites as face sheet material in CFRP-Al/HC sandwich structures (HC = honeycomb), that can be exposed to space debris. A review of CFRP-Al/HC structures typically used in space was performed. Based on this review, a representative structure in terms of materials and geometry was selected for study in the work described here. An experimental procedure for the characterisation of composite materials is documented in [1]. The test results from the CFRP of the current study allow for the derivation of an experimentally based orthotropic continuum material model data set that is capable of predicting the mechanical behaviour of CFRP under hypervelocity impact. Such a data set was not previously available. In [2] an orthotropic material data set was used for modelling HVI on AFRP (aramid fibre reinforced plastic), which shows relatively high deformability before failure. The enhancements of the modelling approaches in [1] and [3] necessary to model brittle CFRP are specified. An experimental hypervelocity impact campaign was performed at two different two stage light gas guns which encompassed both normal and oblique impacts for a range of impact velocities and projectile diameters. Validation of the numerical model is provided through comparison with the experimental results. For that purpose measurements of the visible damage of the face sheets and of the HC core are conducted. In addition, the numerically predicted damage within the CFRP is compared to the delamination areas found in ultrasonic scans.

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Multi-layer insulation material models suitable for hypervelocity impact simulations

Cited by 13 publications

References 5 publications

Effect of projectile’s nose shape on ballistic performance of ceramic/composite armour: A numerical study

Effect of projectile’s nose shape on ballistic performance of ceramic/composite armour: A numerical study

A review of the Solar Probe Plus dust protection approach

Hypervelocity impact on CFRP: Testing, material modelling, and numerical simulation

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