Studies of hypervelocity impact phenomena as applied to the protection of spacecraft operating in the MMOD environment

Schonberg, William P.

doi:10.1016/j.proeng.2017.09.723

Cited by 27 publications

(5 citation statements)

References 53 publications

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“…Impacts at these velocities are often catastrophic due to the impactor’s overwhelming kinetic energy. Satellites orbiting Earth are at risk of HVI through micro meteor orbital debris (MMOD). − Yet on Earth, shaped charges are capable of launching jets of material at hypervelocity. − Therefore, to protect human life and critical infrastructure from these hypervelocity impacts, a fundamental understanding regarding the responses of various materials at such high velocities is paramount. The HVI response of materials, particularly that of metals and ceramics because of their importance in space applications, has been investigated widely using a two-stage light gas gun (2SLGG). ,− The HVI impact of MMOD can lead to an ultrahigh strain rate, ≥10 6 s –1, and in 2SLGGs, an estimated strain rate over the range 10 5 –10 6 s –1 can be achieved …”

Section: Introductionmentioning

confidence: 99%

High Strain Rate Failure Behavior of Polycarbonate Plates due to Hypervelocity Impact

2022

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Developing a fundamental understanding of how polymers respond during hypervelocity impact (HVI), a high strain rate process, is crucial for the potential use of polymers in HVI protection systems. Here, we present the high-strain-rate impact behavior of commercially available polycarbonates with two different molecular weights, 42 and 21 kg/mol. A powder gun and a two-stage light-gas gun were used to achieve the velocities (v0) of a 4 mm projectile impacting the polycarbonate targets over the range of 400–6,500 m/s. The deformation behavior of the polymer during the impact event was captured using high-speed cameras. The impact caused a variety of responses, ranging from deflection of the projectile to complete perforation for higher v0, leading to major debris cloud formation. These debris clouds consist of both fluid- and dust-like ejecta. The fluid-like debris cloud indicates the melting of polymer caused by the conversion of kinetic energy to thermal energy and subsequent adiabatic heating. The dust-like response can likely be attributed to the brittle failure behavior of polymers, as the polymer became brittle at a high strain rate. Dynamic mechanical analysis (DMA) and dielectric thermal analysis (DETA) on the polycarbonate samples used here indicate an approximately 40 °C increase of T g with increasing frequency from 1 Hz to 106 Hz, and such an increase has likely led to brittle behavior. While the leading-edge velocity of the debris clouds and perforation diameters scale linearly with v0, we found negligible differences in the HVI response for the two molecular weights of polycarbonate tested here. This study displays the importance of v0 and thickness contributing to responses of polycarbonates undergoing HVI.

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Section: Introductionmentioning

confidence: 99%

High Strain Rate Failure Behavior of Polycarbonate Plates due to Hypervelocity Impact

2022

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“…The space environment during the spacecraft travelling time and mission continues to be a major cause of anomalies in many space missions. The most common factors of such anomalies are surface charging and discharging, solar radiation heating loads, and the existence of orbital debris in space as indicated by several published studies [1][2][3][4][5][6][7][8][9][10][11][12]. In addition, the solar load, shielding material, onboard equipment location, thermal control and air conditioning systems must be considered during the design stage of spacecraft/satellites [13][14][15][16][17][18][19].…”

Section: Introductionmentioning

confidence: 99%

Modeling and Thermal Analysis of a Moving Spacecraft Subject to Solar Radiation Effect

et al. 2019

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The impact of solar radiation on spacecraft can increase the cooling load, degrade the material properties of the structure and possibly lead to catastrophic failure of their missions. In this paper, we develop a computational model to investigate the effect of the exposure to solar radiation on the thermal distribution of a spacecraft with a cylindrical shape which is traveling in low earth orbit environment. This is obtained by the energy conservation between the heat conduction among the spacecraft, the heating from the solar radiation, and the radiative heat dissipation into the surroundings while accounting for the dynamics of the space vehicle (rotational motion). The model is solved numerically using the meshless collocation point method to evaluate the temperature variations under different operating conditions. The meshless method is based on approximating the unknown field function and their space derivatives, by using a set of nodes, sprinkled over the spatial domain of the spacecraft wall and functions with compact support. Meshless schemes bypass the use of conventional mesh configurations and require only clouds of points, without any prior knowledge on their connectivity. This would relieve the computational burden associated with mesh generation. The simulation results are found in good agreement with those reported in previously-published research works. The numerical results show that spinning the spacecraft at appropriate rates ensures low and uniform temperature distribution on the spacecraft, treated as thick-walled object of different geometries. Therefore, this would extend its lifetime and protect all on-board electronic equipment needed to accomplish its mission.

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“…In the aviation sector, the components such as empennage leading edges, windshields, and the intake of engines Nacelles are subjected to highspeed impact loadings; also it was considered that almost 77% of the accidents are caused due to the impact in windshields [2,3]. In the space sector, the average velocity of debris is 7.5 km/s, and it varies from 0.5 to 16 km/s, which the satellites are supposed to withstand its impact [4,5]. Te military vehicles use organic composites such as kevlar and spectra which absorb energy by deformation of the fber itself, the same technology is used in formula (1) cars [6].…”

Section: Introductionmentioning

confidence: 99%

Estimation of Impact Strength of Kevlar/Basalt and Kevlar/Glass Interwoven Composite Laminate after High-Velocity Bullet Impact

Jensin Joshua,

Singh,

Murali Krishna

et al. 2023

Advances in Materials Science and Engineering

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The application of composite materials has increased so drastically in the aerospace industry. The Impact strength signifies the importance of composite materials when exposed to suddenly applied loads. This paper is focused on describing the behavior of interwoven kevlar/glass-epoxy and kevlar/basalt-epoxy composite laminate under high-velocity bullet impact. The composite lamina of kevlar/glass and that of kevlar/basalt are prepared using three different weaving techniques. The composite laminates are prepared using the compression moulding technique. The laminates have been subjected to high-velocity bullet impact. The velocity range is from 220 m/s to 260 m/s. The impact damage area in the laminate has been assessed through ultrasonic pulse echo submerged nondestructive technique. The impact strength has been calculated using the damaged area derived using the impact energy absorbed by the laminate. The results have shown that the maximum impact which found out to be kevlar/basalt (KB 1 × 1) is 28.24 J/cm2.

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Studies of hypervelocity impact phenomena as applied to the protection of spacecraft operating in the MMOD environment

Cited by 27 publications

References 53 publications

High Strain Rate Failure Behavior of Polycarbonate Plates due to Hypervelocity Impact

High Strain Rate Failure Behavior of Polycarbonate Plates due to Hypervelocity Impact

Modeling and Thermal Analysis of a Moving Spacecraft Subject to Solar Radiation Effect

Estimation of Impact Strength of Kevlar/Basalt and Kevlar/Glass Interwoven Composite Laminate after High-Velocity Bullet Impact

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