Application of the NASA/JSC Whipple shield ballistic limit equations to dual-wall targets under hypervelocity impact

Schonberg, William P.; Compton, L. E.

doi:10.1016/j.ijimpeng.2008.07.054

Cited by 12 publications

(4 citation statements)

References 4 publications

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“…The studies showed that the diameter of the spherical whipple shield had to be large compared to that of the flat plate whipple shileds by an aspect ratio of 2.2 for 7 km/s and 1.6 for 14.5 km/s for the same extent of damages. In 2008, Schonberg et al, [56] determined determined the critical diameter of projectile for hypervelocity impacts and incroporated it into the NASA-JSC ballistic limit equation which reduced the mass by almost 52 %. A flaw in the NASA-JSC Ballistic limit equation was identified for oblique impact angles beyond 60 • .…”

Section: Numerical Simulationmentioning

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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Section: Numerical Simulationmentioning

confidence: 99%

Advances in the Whipple Shield Design and Development:

Pai

Divakaran

Anand

et al. 2021

J. dynamic behavior mater.

View full text Add to dashboard Cite

show abstract

“…The decided lack of overlapping of the rupture/non-rupture test data is primarily due to the judicious selection of the values of the exponents Q,S, and T. However, this lack of overlap is admittedly rather unusual, especially in hypervelocity impact test programs (see, e.g. the overlap and scatter in such testing of metallic dual-wall systems [9]). It is indeed possible that additional testing of similar COPVs could yield test results that cannot be so cleanly separated.…”

Section: Comparison With Empirical Datamentioning

confidence: 99%

A rupture limit equation for COPVs following a perforating MMOD impact

Schonberg

2019

2019 15th Hypervelocity Impact Symposium

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Most spacecraft have at least one pressurized vessel on board. One of the primary design considerations for earth-orbiting spacecraft is the anticipation and mitigation of the possible damage that might occur in the event of a micrometeoroid or orbital debris (MMOD) particle impact. To prevent mission failure and possibly loss of life, protection against perforation by such high-speed impacts must be included. In addition to a hole, it is possible that, for certain pressure vessel designs, materials, impact parameters, and operating conditions, a pressure vessel may experience catastrophic failure (i.e. rupture) as a result of a hypervelocity impact. If such a tank rupture were to occur on-orbit following an MMOD impact, not only could it lead to loss of spacecraft, but quite possibly, for human missions, it could also result in loss of life. In this paper we present an update to a Rupture Limit Equation, or RLE, for composite overwrapped pressure vessels (COPVs) that was presented previously. The update consists of modified RLE parameters and coefficients that were obtained after the RLE was re-derived using new / additional data. The updated RLE functions in a manner similar to that of a ballistic limit equation, or BLE, that is, it differentiates between regions of operating and impact conditions that, given a tank wall perforation, would result in either tank rupture or only a relatively small hole or crack. This is an important consideration in the design of a COPV pressurized tank – if possible, design parameters and operating conditions should be chosen such that additional sizable debris (such as that which would be created in the event of tank rupture or catastrophic failure) is not created as a result of an on-orbit MMOD particle impact.

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“…Further, consideration of threats such as micrometeoroid impact has led to development of inherently ballistic-resistant composite-based architectures such as spaced shielding and honeycomb structures. 2 In such cases the outer layers typically act to disrupt incident projectiles, with backing layers catching the resultant debris (analogous to the ‘Whipple Bumper’, a spaced shielding solution designed to disrupt incident projectiles 10–12 ). For example, Ryan et al 7 suggest that composites comprising sandwiches of low density Al honeycomb structures faced with stiff CFRP panels are likely to play a substantial structural role in next-generation European spacecraft.…”

Section: Hypervelocity Impactsmentioning

confidence: 99%

“…Spacecraft operate in environments subject to both extremes of thermal and electro-magnetic radiation and also a random, but statistically significant, threat of collision with orbital debris. 2,12,15,16,18 This debris arises from several sources, including: natural detritus (e.g. interstellar media and commentary debris 19 ); accidental release (e.g.…”

Section: Hypervelocity Impactsmentioning

confidence: 99%

The impact of structural composite materials. Part 2: hypervelocity impact and shock

Appleby-Thomas

Hazell

2012

The Journal of Strain Analysis for Engineering Design

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The combination of high strength and low density has resulted in increasing use of composite materials in structures such as aerospace systems that may be subjected to high-velocity impact during their in-service lives. In this review we focus on recent work surrounding the response of composites, primarily carbon fibre reinforced plastic and glass fibre reinforced plastic-based laminates to very high (hyper)-velocity impacts. To this end, the review is divided into two halves. In the first, hypervelocity impacts (e.g. impacts with velocities greater than ca. 2 km/s) that are likely to be encountered by aerospace systems are considered; while in the second, resultant material behaviour – in the form of shock response – is discussed. This review is designed to (1) build on previous studies which have typically largely focused on high-velocity impacts from the perspective of spacecraft protection against on-orbit impact, and; (2) complement an earlier part which focused on the lower impact velocity regime associated with ballistic-loading (Part 1).

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Application of the NASA/JSC Whipple shield ballistic limit equations to dual-wall targets under hypervelocity impact

Cited by 12 publications

References 4 publications

Advances in the Whipple Shield Design and Development:

Advances in the Whipple Shield Design and Development:

A rupture limit equation for COPVs following a perforating MMOD impact

The impact of structural composite materials. Part 2: hypervelocity impact and shock

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