Quantitative analysis of debris clouds from SiC-fiber-reinforced silicon nitride bumpers

Tamura, Hideki; Mutou, Yasuo

doi:10.1016/j.ijimpeng.2004.07.004

Cited by 8 publications

(2 citation statements)

References 13 publications

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“…Porous fillers as part of all-aluminum multi-wall systems were also considered by Colombo et al (2003) and Li et al (2004). In nearly all of the studies, the results showed that the composite material bumpers faired at best only marginally better in terms of ballistic limit of the dual-wall systems than their equivalent monolith aluminum counterparts (see also Robinson and Nolen, 1995;Sil'vestrov et al, 1999a,b;Tamura and Mutou, 2005). However, there were some differences in bumper hole sizes, fragmentation of the impacting projectile, debris cloud composition and motion/spread between the dualwall systems with composite and with aluminum bumpers that gave rise to this slight improvement in protection when composite material bumpers were used.…”

Section: Composite Outer Bumpersmentioning

confidence: 99%

Protecting Earth-orbiting spacecraft against micro-meteoroid/orbital debris impact damage using composite structural systems and materials: An overview

Schonberg

2010

Advances in Space Research

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Section: Composite Outer Bumpersmentioning

confidence: 99%

Protecting Earth-orbiting spacecraft against micro-meteoroid/orbital debris impact damage using composite structural systems and materials: An overview

Schonberg

2010

Advances in Space Research

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“…The debris cloud is comprised of three parts: a frontal central portion, a peripheral portion, and an ejecta veil [8][9][10] . The frontal central portion of the debris cloud contains remnants from both the projectile and the perforated layer.…”

Section: Introductionmentioning

confidence: 99%

Novel Composite Space Shielding Concepts for Hypervelocity Orbital Debris Impact Mitigation

Offenberger

Warren

Lacy

et al. 2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Micro two-stage light gas gun experiments were carried out to assess the hypervelocity impact (HVI) response of two different composite laminates as well as identical laminates with a graphite nanoplatelet composite sheet adhered to the impact side. Two laminate types were made using epoxy-reinforced carbon fiber pre-impregnated unidirectional tape: a quasi 3D five-harness satin weave (Q3DO5) and a cross-ply laminate. 50 percent of the Q3DO5 and cross-ply specimens had a graphite sheet bonded to their impact side. The projectiles were 1 mm diameter aluminum spheres, and the impact velocities ranged from 2.9 km/s to 5.25 km/s. Visual observations were made of the debris cloud impacts were made on witness plates positioned behind the laminated specimens to assess the size, constituents, and energy of the debris cloud. The woven Q3DO5 composite without the graphite sheet was thicker than the cross-ply laminate without the graphite sheet. This additional thickness resulted in less debris cloud damage present on the Q3DO5 witness plates. There was less of a difference in thickness between the two types of specimens once the graphite sheets were bonded. However, the relative damage to the witness plate for the Q3DO5 and cross-ply specimens with the graphite sheet was much greater than that seen without the graphene sheets. This suggests that a relatively thin light weight graphite nanoplatelet composite sheet adhered to a laminate could potentially increase its resistance to HVI. Nomenclature 2D= Two Dimensional GP = Graphite Nanoparticle Composite Sheets Bonded in a Polyetherimide Thermoplastic Matrix GP/cross-ply = Nanographite/Polyetherimide Paper Sheet Bonded to a cross-ply Laminate GP/Q3D0 5 = Nanographite/Polyetherimide Paper Sheet Bonded to a Q3DO5 Laminate HVI = Quasi-Three-Dimensional MMOD = Micrometeorite and Orbital Debris PEI = Polyetherimide Q3D = Quasi-Three-Dimensional Q3dO5= 5 Harness Orthogonally Woven Quasi-Three-Dimensional

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Assessing the Resiliency of Composite Structural Systems and Materials Used in Earth-Orbiting Spacecraft to Hypervelocity Projectile Impact

Schonberg¹

2009

Predictive Modeling of Dynamic Processes

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Quantitative analysis of debris clouds from SiC-fiber-reinforced silicon nitride bumpers

Cited by 8 publications

References 13 publications

Protecting Earth-orbiting spacecraft against micro-meteoroid/orbital debris impact damage using composite structural systems and materials: An overview

Protecting Earth-orbiting spacecraft against micro-meteoroid/orbital debris impact damage using composite structural systems and materials: An overview

Novel Composite Space Shielding Concepts for Hypervelocity Orbital Debris Impact Mitigation

Assessing the Resiliency of Composite Structural Systems and Materials Used in Earth-Orbiting Spacecraft to Hypervelocity Projectile Impact

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