Crater distribution on the rear wall of AL-Whipple shield by hypervelocity impacts of AL-spheres

Guan, Guixia; Pang, Baojun; Zhang, Wei; Yue, Honghao

doi:10.1016/j.ijimpeng.2008.07.028

Cited by 27 publications

(5 citation statements)

References 8 publications

(8 reference statements)

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“…The yield strength of this material provided by CAST is 47 ksi (≈ 324 MPa). Values in the literature vary between 110 MPa and 340 MPa [32][33][34][35][36]. The rear wall material used for the ISS Columbus shield is aluminum alloy 2219-T851 [6].…”

Section: Shield Componentsmentioning

confidence: 99%

A stuffed Whipple shield for the Chinese space station

Putzar

Zheng

et al. 2019

International Journal of Impact Engineering

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Section: Shield Componentsmentioning

confidence: 99%

A stuffed Whipple shield for the Chinese space station

Putzar

Zheng

et al. 2019

International Journal of Impact Engineering

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“…Low orbit flights are marred with the presence of space debris and meteoroids which physically impact the spacecraft at hypervelocities causing catastrophic failures. In 2008, Gongshun et al [85] made use of a two-stage light gas gun which launched aluminium alloy (with T4 temper) sphere projectiles at a hyper-velocity range of 0.69 km/s to 6.98 km/s on aluminium whipple shields. The crater distribution on the rear wall was studied.…”

Section: Experimental Analysis Of Whipple Shieldsmentioning

confidence: 99%

Advances in the Whipple Shield Design and Development:

Pai

Divakaran

Anand

et al. 2021

J. dynamic behavior mater.

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Safety of satellites as well as spacecrafts during space missions is a primary objective to preserve the physical and virtual assets onboard. Whipple shields belong to the class of protective equipment provided on the surface of the spacecrafts and satellites, to sustain impacts from the ultra-high speed debris, which can otherwise cause considerable damage to the corresponding structures. Recent works on whipple shields are focussed on determining the response of different geometrical arrangements and material properties under hyper-velocity impact at projectile speeds of 3-18 km/s. Advances in the whipple shield design include integrated and mechanised models employing high performance materials like fiber-metal laminates ensuring better operational capability. The forward bumper of the whipple shield is the first line of defence as it regulates the state of projectile after the primary impact. Use of aluminium alloys for front bumpers is popular, owing to their lightweight and strength characteristics. The advances for the front bumper have seen usage of ceramic, metallic foams, and super composite mixtures, which resulted in enhanced performance, durability and safety of the whipple shields. This work is a comprehensive coverage of the latest materials used for whipple shields, their performance characterization—both experimental and theoretical, and applications.

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“…In this work, the HVI experiments of the Basalt fabric, UHMWPE fabric, and 5A06 aluminum alloy (Al) plate, were carried out by using a two-stage light gas gun. Specially, the 5A06 Al plate is selected for comparison of shielding performance, for this material is commonly used to manufacture spacecraft bulkheads [ 22 ]. The projectile is a 2017-T4 Al sphere with a diameter of 3.97 mm toward replacing irregular space debris, and the impact velocity range is 4.1~4.3 km/s.…”

Section: Introductionmentioning

confidence: 99%

The Hypervelocity Impact Behavior and Energy Absorption Evaluation of Fabric

Cui

et al. 2023

Polymers

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In this work, the mechanical behavior and energy absorption characteristics of flexible fabric under hypervelocity impact (HVI) were investigated. Basalt fabric, ultra-high molecular weight polyethylene (UHMWPE) fabric, and aluminum alloy (Al) plate were chosen to be the sample materials for their excellent mechanical properties and applicative prospect in spacecraft shielding. HVI experiments had been conducted with the help of a two-stage light-gas gun facility, wherein Al projectile with 3.97 mm diameter was launched at velocities in the range 4.1~4.3 km/s. Impact conditions and areal density were kept constant for all targets. The microstructural damage morphology of fiber post-impact was characterized using a scanning electron microscope (SEM). Analysis results show that a brittle fracture occurred for Basalt fiber during HVI. On the contrary, the ductile fractures with large-scale plastic deformation and apparent thermal softening/melting of the material had happened on the UHMWPE fiber when subjected to a projectile impact. According to the HVI shielding performance and microstructural damage analysis results, it can be inferred that ductile fractures and thermal softening/melting of the material were the prevailing energy absorption behaviors of UHMWPE fabric, which leads to absorbing more impact energy than Basalt fabric and eventually, contributes the superior shielding performance.

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Crater distribution on the rear wall of AL-Whipple shield by hypervelocity impacts of AL-spheres

Cited by 27 publications

References 8 publications

A stuffed Whipple shield for the Chinese space station

A stuffed Whipple shield for the Chinese space station

Advances in the Whipple Shield Design and Development:

The Hypervelocity Impact Behavior and Energy Absorption Evaluation of Fabric

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