Fragmentation and space radioprotection
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1 Fragmentation and space radioprotection C. La Tessa 1,2, E. Tracino 3, C. Schuy 2, M. Rovituso 2, C. Lobascio 3, A. Menicucci 4, E. Daly 4, M. Sivertz 1, A. Rusek 1, M. Durante 2 1 BNL (USA) 2 GSI (Germany) 3 Thales Alenia Space (Italy) 4 ESA (Netherlands)
2 Galactic Cosmic Rays (GCRs): the background radiation in space Equivalent dose contributions for the GCR 2% electrons and positrons 98% nuclei - 87% protons - 12% helium - 1% of heavier ions
3 Effects of nuclear fragmentation in space radioprotection The spacecraft is a complex system composed by: Internal out-fit Secondary Structure Primary Structure Thermal protection Micro-Meteoroids and Orbital Debris (MMOD) protection system Fragmentation of GCR can occur in: spacecraft structure shielding materials astronaut s body changing the composition of the radiation field and thus the dose SHELL
4 Space dosimetry: : some numbers Equivalent dose for the shortest round trip to Mars [Zeitlin et al, Science 31 (2013)] 0.66 ± 0.12 Sv One of the main limitation to space exploration is the health risk Average equivalent dose for a 6 month mission on the ISS [Cucinotta et al, Radiat. Res. 170 (2008)] 0.07 Sv (1 Sv for the whole career) Annual equivalent dose for radiation workers on Earth 0.02 Sv
5 Risk assessment and countermeasures Ground and space based experiments to assess: Radiation environment Effect of shielding materials on the incoming particles Dosimetry Biological effects but this approach alone is too time and money consuming Monte Carlo simulations
6 The experiments Characterization of heavy ions fragmentation in space relevant materials (Al, PE, moon and mars regolith ) Total charge-changing cross section in water ( 4 He 190 MeV/u, 7 Li 300 MeV/u and 16 O 360 MeV/u) [GSI and BNL] Optimization of shielding materials for space travels and permanent habitats Effectiveness of various shielding materials (1 GeV/u 56 Fe) [BNL] Yield and kinetic energy spectrum of secondary protons/neutrons (1 GeV/u 58 Ni) [GSI]
7 Total charge-changing changing cross section
8 Total charge-changing changing cross section Survival fraction of primary ions in a target N/N 0 = exp [- cc d N A /A T ] cc assumed energy independent above ~100 MeV/u Comparison with models Deterministic: Bradt-Peters formula [Bradt et al., Phys. Rev. 77 (1950)] r = r 0 (A P 1/3 + A T 1/3 b) 2 Monte Carlo: PHITS [Sato et al., J. Nucl. Sci. Technol 50 (2013)]
9 Experimental setup BEAM x BEAM MONITOR WATER TARGET D2 BEAM MONITOR and D2 are plastic scintillators The distance x is as small as possible (acceptance angle ~ 900 msr or 60 degrees)
10 190 MeV/u 4 He in H 2 O cc = 286 ± 14 mb (Data) cc = 435 mb (PHITS) cc = 653 mb (Bradt-Peters) N/N 0 = exp [- cc d N A /A T ]
11 Courtesy of G. Martino 300 MeV/u 7 Li in H 2 O cc = 966 ± 8 mb (Data) cc = 1437 mb (PHITS) cc = 727 mb (Bradt-Peters) N/N 0 = exp [- cc d N A /A T ]
12 cc = 1429 ± 46 mb (Data) cc = 1394 mb (PHITS) cc = 1063 mb (Bradt-Peters) 360 MeV/u 16 O in H 2 O N/N 0 = exp [- cc d N A /A T ]
13 Total charge-changing changing cross section: energy dependence *Courtesy of D. Schardt *
14 Shielding materials effectiveness
15 ROSSINI RadiatiOn Shielding by ISRU and/or INnovative MaterIals for EVA, Vehicle and Habitat A 2yearproject funded by ESA and lead by Thales Alenia Space started in January 2012 Main Objectives: Select innovative shielding materials Test under iron ion beam at 1 GeV/u (or equivalent) Give recommendation and guidelines for the design and use of surface and transfer habitat implementing the ALARA principle
16 Single materials -Polyethylene -Aluminum -Moon and Mars regolith -Moon concrete -Cella energy materials A and B Multilayers Columbus (ISS like shell) Shielding materials Light multilayer (C primary + soft MDPS) Hybrid multilayer A (Al primary + soft MDPS) Hybrid multilayer B (C primary + ISS MDPS) [Boron fiber added for neutron absorption]
17 Material test: shielding effectiveness Percent Dose Reduction per Unit Areal Density for Single Materials Fe MeV/n - NSRL/BNL Brookhaven 23/06/ % Dose reduction cm^2 g^ Cella Energy B Cella Energy A Polyethylene HDPE Kevlar Moon Regolith Aluminum Mars Regolith Moon Concrete Nextel
18 Experimental setup Beam monitor: 2 mm plastic scintillator (START) Particle identification: E E telescope E: 9 mm plastic scintillator E: 14 cm BaF 2 crystal, ~20% neutron efficiency Telescope placed at ~25 degrees Acceptance angle ~1 msr (<2 deg) TOF: START - BaF 2 START ϑ TOF VETO BaF 2 TARGET Yield of protons and neutrons (build-up curves) Kinetic energy spectra of protons and neutrons
19 E versus TOF (all particles) VETO ADC [ch] Hydrogen Neutrons + photons TDC [ch]
20 E versus TOF (Neutral particles) Time resolution of ~0.5 ns BaF ADC [ch] Prompt Photons Neutrons TDC [ch]
21 E versus TOF (Hydrogen particles) BaF ADC [ch] Protons TDC [ch]
22 Proton build-up up at 25 deg (primary beam 1 GeV/u 58 Ni)
23 Proton kinetic energy spectra: polyethylene target
24 Comparison with PHITS Proton yield (msr -1 source -1 *10-4 )
25 Conclusions I: total charge-changing changing cross section No models seem to reproduce well light ions (He and Li) - Extend the comparison to other codes (FLUKA, Geant4, ) Cross section dependence on energy - Additional experiments for different systems
26 Conclusions II: shielding effectiveness Promising materials (Cella energy B) better than PE: % 5 dose reduction per g cm -2 The proton build-up is pretty much equivalent for all materials - Additional experiments with Cella energy B - Complete the analysis for the neutrons - Compare kinetic energy spectra with Monte Carlo Disagreement between Monte Carlo and experimental data for build-up - Additional experiments and model benchmark
27 Acknowledgements ESA for funding the project NASA, BNL and GSI for hosting the experiments
28 2 Copyright NASA Thank you Copyright NASA
29 Neutron efficiency of the BaF 2 detector ~ 20 % efficiency above 100 MeV Gunterz Marx et al., NIMA 536 (2004) Wagner et al., NIMA 394 (1997)
30 VETO BaF 2 telescope START detector
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