Space station MMOD shielding

Christiansen, Eric L.; Nagy, Kornel; Lear, Dana M.; Prior, Thomas G.

doi:10.1016/j.actaastro.2008.01.046

Cited by 54 publications

(25 citation statements)

References 6 publications

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“…We assume that the detector module includes 20mm thick spherical aluminum shielding. Storing it in a random place inside the ISS typically adds 10mm further shielding by the pressure vessel and micro-meteoroid orbital debris impact shield of the ISS [52,53]. We thus simulate for a total of 30mm spherical aluminum shielding.…”

Section: Appendix Feasibility Of Using Si Apds As Single-photon Detementioning

confidence: 99%

Space QUEST mission proposal: experimentally testing decoherence due to gravity

Joshi¹,

Pienaar²,

Ralph³

et al. 2018

New J. Phys.

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Models of quantum systems on curved space-times lack sufficient experimental verification. Some speculative theories suggest that quantum correlations, such as entanglement, may exhibit different behavior to purely classical correlations in curved space. By measuring this effect or lack thereof, we can test the hypotheses behind several such models. For instance, as predicted by Ralph et al [5] and Ralph and Pienaar [1], a bipartite entangled system could decohere if each particle traversed through a different gravitational field gradient. We propose to study this effect in a ground to space uplink scenario. We extend the above theoretical predictions of Ralph and coworkers and discuss the scientific consequences of detecting/failing to detect the predicted gravitational decoherence. We present a detailed mission design of the European Space Agency's Space QUEST (Space-Quantum Entanglement Space Test) mission, and study the feasibility of the mission scheme.

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Section: Appendix Feasibility Of Using Si Apds As Single-photon Detementioning

confidence: 99%

Space QUEST mission proposal: experimentally testing decoherence due to gravity

Joshi¹,

Pienaar²,

Ralph³

et al. 2018

New J. Phys.

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“…This outfitting was parametrically sized using tools and assumptions consistent with the conceptual design of the Deep Space Habitat (DSH) for NASA's Human Spaceflight Architecture Team (HAT) 3 . The structure, subsystems, and logistics were then assigned densities based upon the parametric sizing and previous studies [4][5][6][7] .…”

Section: Radwork Spe Shelter Design Effortmentioning

confidence: 99%

Habitat Design Considerations for Implementing Solar Particle Event Radiation Protection

Simon

Clowdsley

Walker

2013

43rd International Conference on Environmental Systems

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Radiation protection is an important habitat design consideration for human exploration missions beyond Low Earth Orbit. Fortunately, radiation shelter concepts can effectively reduce astronaut exposure for the relatively low proton energies of solar particle events, enabling moderate duration missions of several months before astronaut exposure (galactic cosmic ray and solar particle event) approaches radiation exposure limits. In order to minimize habitat mass for increasingly challenging missions, design of radiation shelters must minimize dedicated, single-purpose shielding mass by leveraging the design and placement of habitat subsystems, accommodations, and consumables. NASA's Advanced Exploration Systems RadWorks Storm Shelter Team has recently designed and performed radiation analysis on several low dedicated mass shelter concepts for a year-long mission. This paper describes habitat design considerations identified during the radiation analysis phase of the study. These considerations include placement of the shelter within a habitat for improved protection, integration of human factors guidance for sizing shelters, identification of potential opportunities for habitat subsystems to compromise on individual subsystem performances for overall vehicle mass reductions, and pre-configuration of shelter components for reduced deployment times. Nomenclature AcronymsAES = Advanced Exploration Systems BEO = Beyond Earth Orbit BNNT = Boron Nitride Nanotubes CAD = Computer-Aided Design CTB = Cargo Transfer Bag DSH = Deep Space Habitat GCR = Galactic Cosmic Rays HAT = Human Spaceflight Architecture Team HDU = Habitat Demonstration Unit HMC = Heat Melt Compactor HZETRN = High charge (Z) and Energy TRaNsport code ISS = International Space Station LEO = Low Earth Orbit OLTARIS = On-Line Tool for the Assessment of Radiation in Space SPE = Solar Particle Event

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“…Low‐Earth orbiting spacecraft and satellites are in constant threat of collision from an ever‐increasing flux of hypervelocity particles . Impacts of this nature were recognized early on in the space program and much effort has been devoted to developing shielding materials and geometries that can best mitigate these threats while maintaining the low‐areal density required for space applications.…”

Section: Introductionmentioning

confidence: 99%

Hypervelocity Impact Testing of a Metallic Glass‐Stuffed Whipple Shield

et al. 2015

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In this work, hypervelocity impact tests up to 7 km Á s À1 are used to compare the performance of Whipple shields integrated with layers of metallic glasses with a baseline target analogue of one of the shields similar to what is used on the International Space Station. The baseline target failed under the impact while the target utilizing metallic glass as a replacement for the fabric layers in the baseline passed the test. The paper postulates on the prospects of future implementation of metallic glasses as spacecraft debris shields.

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Space station MMOD shielding

Cited by 54 publications

References 6 publications

Space QUEST mission proposal: experimentally testing decoherence due to gravity

Space QUEST mission proposal: experimentally testing decoherence due to gravity

Habitat Design Considerations for Implementing Solar Particle Event Radiation Protection

Hypervelocity Impact Testing of a Metallic Glass‐Stuffed Whipple Shield

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