An engineering model to describe fragments clouds propagating inside spacecraft in consequence of space debris impact on sandwich panel structures

Francesconi, Alessandro; Giacomuzzo, Cinzia; Feltrin, Francesco; Antonello, Alessandro; Savioli, Livia

doi:10.1016/j.actaastro.2015.07.013

Cited by 26 publications

(4 citation statements)

References 23 publications

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“…In this context, on one hand, dedicated protections are designed to shield satellites from hypervelocity impacts; ground tests are usually employed to assess their capability to mitigate collisions [15,16] and to protect spacecraft components [17,18]. Furthermore, critical elements are usually subjected to similar tests to evaluate their survivability in the debris environment [19].…”

Section: Introductionmentioning

confidence: 99%

Research at the University of Padova in the Field of Space Debris Impacts against Satellites: An Overview of Activities in the Last 10 Years

et al. 2023

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Space debris represent a threat to satellites in orbit around Earth. In the case of impact, satellites can be subjected to damage spanning from localized craterization to subsystem failure, to complete loss of the vehicle; large collision events may lead to fragmentation of the spacecraft. Simulating and testing debris impacts may help in understanding the physics behind these events, modelling the effects, and developing dedicated protection systems and mitigation strategies. In this context, the Space Debris group at the University of Padova investigates in-space collisions with experimental campaigns performed in a dedicated Hypervelocity Impact Facility and with numerical simulations with commercial and custom software. In this paper, an overview is given of the last 10 years of research activities performed at the University of Padova. First, the hypervelocity impact testing facility is described and the main experimental campaigns performed in the last few years are summarized. The second part of this work describes impact modelling research advances, focusing on the simulation of complex collision scenarios.

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Section: Introductionmentioning

confidence: 99%

Research at the University of Padova in the Field of Space Debris Impacts against Satellites: An Overview of Activities in the Last 10 Years

et al. 2023

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“…1–4 When compared to monolithic structures of equivalent weight, combined solutions such as sandwich panels, typically made up of thin, rigid front and back face sheets, and soft low-density core materials, have demonstrated attractive qualities in high strength-to-weight ratio and exceptional energy absorption capability. 5,6 Being used in the protection and shielding systems, 7–10 such sandwich structures can also be investigated under perforation to assess their performance against bullets, 11 fragments, 12 micrometeoroids and orbital debris 13 and other flying debris, generated from an improvised explosive device (IED). 14 Depending on the threat's nature and origin, the projectile velocities vary between different levels, from low 15 or intermediate 16 values to several hundreds of meters per second.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation on the perforation behaviour of sandwich panels with hybrid composite face sheets and cellular aluminium core using quasi-static and instrumented inverse impact methods

Derbala

Tria

Gilson

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part L:

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With the rising demand for lightweight and high-performance shielding systems, sandwich panels made of thin rigid face sheets and cellular material cores have recently received much attention. The present study aims to investigate the perforation behaviour of lightweight sandwich panels made of fibre reinforced composite face sheets and aluminium foam core under quasi-static and dynamic testing conditions. A particular focus is made on the fibre hybridization effect on the overall panel behaviour. Impact perforation tests were conducted using an inverse perforation technique. Instead of conventional free-flying projectile impact tests, studied samples are fixed in a hollow projectile. Then, this assembly is accelerated toward an instrumented steel perforator replacing the incident bar of a split Hopkinson pressure bar. Consequently, this modified split Hopkinson pressure bar system can be used as both a perforator and a measuring device. Therefore, the piercing force-displacement curves, the energy absorption capability as well as the penetration and damage mechanisms of the tested panels was analysed and compared to quasi-static perforating tests. To better assess the testing results, quasi-static tensile and bending tests were carried out on the face sheets materials. Moreover, quasi-static and dynamic compression tests were performed on the aluminium foam core using conventional test methods and direct split Hopkinson pressure bar. Unlike the aluminium alloy face sheets, the experimental findings revealed that the sandwich panels with composite face sheets demonstrated higher rate sensitivity, better perforation resistance and specific energy absorption capability. Results have also shown that the hybridization of carbon and glass fabrics combined their best tension and bending properties as well as their higher dynamic strength, which has increased the sandwich panel's perforation resistance.

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“…Ding et al [9] calculated the cratering depth by taking the mass fraction of each fragment into consideration. Francesconi et al [10] stated that the large central fragment is also significant for impact on the sandwich plane. Furthermore, Ryan et al [6] evaluated shield performance in the shatter regime and concluded that an accurate reflection of the shield's performance could be provided by considering the large central fragment.…”

Section: Introductionmentioning

confidence: 99%

An Alternative Ballistic Limit Equation for the Whipple Shield in the Shatter Regime, Based on Characteristics of the Large Central Fragment

Wen

Chen

2021

Transactions on Aerospace Research

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In the shatter regime of a Whipple shield, a large central fragment makes a significant contribution to the damage-causing capacity of the debris cloud. Herein we present a feasible scheme for the identification and measurement of this large central fragment and propose an alternative approach to the ballistic limit equation (BLE) for the Whipple shield, deducing an alternative ballistic limit in the shatter regime based on the large central fragment’s characteristics. This alternative BLE is compared with the phenomenological Whipple BLE, the JSC Whipple BLE and the Ryan curve. Our alternative BLE, modified at the incipient fragmentation and completed fragmentation point, is shown to agree well with experimental results.

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An engineering model to describe fragments clouds propagating inside spacecraft in consequence of space debris impact on sandwich panel structures

Cited by 26 publications

References 23 publications

Research at the University of Padova in the Field of Space Debris Impacts against Satellites: An Overview of Activities in the Last 10 Years

Research at the University of Padova in the Field of Space Debris Impacts against Satellites: An Overview of Activities in the Last 10 Years

Experimental investigation on the perforation behaviour of sandwich panels with hybrid composite face sheets and cellular aluminium core using quasi-static and instrumented inverse impact methods

An Alternative Ballistic Limit Equation for the Whipple Shield in the Shatter Regime, Based on Characteristics of the Large Central Fragment

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