1. THALES ALENIA SPACE ITALIA: EXPERIENCES ON SPACE RADIATION SHIELDING
SR2S pre kick-off meeting CERN, 5 December 2012
THALES ALENIA SPACE ITALIA: EXPERIENCES ON SPACE RADIATION SHIELDING
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2. Presentation summary Projects overview Main Collaborations
Past radiation shielding projects
Actual radiation shielding projects
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3. Radiation shielding projects summary
REMSIM
MOMA-COUNT
STEPS / PEPS
ROSSINI
IBER-10 / SPARTACUS
PERSEO
PAST
Current
Proposal
Studies on radiation shielding for interplanetary human missions
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4. Continuous involvement in radiation shielding R&D projects
Radiation shielding projects summary
REMSIM [2003 – 2004]
MOMA-COUNT [2005 – 2007]
STEPS / PEPS [2007 – 2011]
ROSSINI [2012 – 2013]
IBER-10 / SPARTACUS [2013 – 2016] ?
PERSEO (proposal) [2013 – 2016] ?
Continuous involvement in radiation shielding R&D projects
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5. Radiation shielding: main collaborations
GSI Helmholtzzentrum für Schwerionenforschung
Accelerator test and MC simulation with PHITS
Istituto Nazionale di fisica nucleare (TO, GE, FI, NA)
Flight test and MC simulations with FLUKA and G4
Università di Pavia
Personal shielding system
Università di Roma Tor Vergata
Material test on ISS using ALTEA and ALTEINO
SpaceIT
MC simulation with Geant4 and Fluka and code development
05/05/2018
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6. Radiation Exposure and Mission Strategies for Interplanetary Manned Mission - REMSIM
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7. REMSIM Study Team Alenia Spazio (Prime Contractor) RxTec INFN Genova
INFN Firenze
EADS-Astrium France
EADS-Astrium UK
BIRA
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8. Study purpose DURATION: 1 year
FOCUS: RADIASHION SHIELING IN INTERPLANETARY MISSIONS (Moon, Mars)
Radiation environment and its variability (Alenia)
Radiation effects on the crew (RxTec)
Transfer trajectories and associated fluences (EADS Astrium)
Concepts of transfer vehicles and surface habitats (Alenia + EADS Astrium)
Active shielding concept (INFN Firenze)
Geant4 simulations (INFN Genova)
Space weather forecasting and warning system (BIRA + REM Oxford)
05/05/2018
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9. REMSIM - Study logic Task 1 Task 2 Task 3 Task 4 Task 5 05/05/2018
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10. REMSIM - Environment SPE
Use JPL model for energies < 5 MeV, and King model for higher energies to calculate mission integrated fluences
Use confidence levels as suggested in ECSS-E-10-04A
95% confidence for King
Envelope (including ions) of CRÈME 96 worst week Oct 89’; and Aug 72’ events for mid range (10-70 MeV), if solar max mission
Ordinary event from King model if solar min mission
1/r3 scaling if < 1AU, no scaling if > 1AU
GCR
Envelope of the integral fluences, using both the 1970 fluxes from CRÈME96 and the 1980 fluxes from CREME86, if solar max mission
Envelope of the integral fluences, using both the 1977 fluxes from CRÈME96 and the 1975 fluxes from CREME86, if solar min mission
‘Surkov’ scaling if > 1AU, no scaling if < 1AU
15% uncertainty to account for uncertainty in the GCR background
Account for protons and electrons in Earth’s radiation belts
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11. REMSIM – Mission Scenario
This study identified 4 mission scenarios, and investigated every scenario for:
solar minimum
solar maximum.
These scenarios are:
Mars conjunction transfer, long stay mission
fast transfer mission to & from Mars
Venus Gravity Assist on Mars return mission,
lunar mission,
A daily heliocentric distance profile was produced for each mission scenario
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12. REMSIM – Mars mission limits (RxTec)
Proposed equivalent dose limits to the BFO
for a 1000 days human mission to Mars
1 minute hour month year mission
Warning Sv mSv Sv Sv Sv
Alarm 3 warnings mSv Sv Sv Sv
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13. REMSIM - Typical transfer vehicles
NASA Approach: Earth-to-Mars transfer vehicle
ISTC Approach: Interplanetary Orbital Vehicle
Crew of 6
2 Habitat sections
70 t
Aeroshell (13,4t)
TMI
Transit Habitat (28,5t)
Descent & landing module (16,3t)
3 individual cabins with radiation protection made of water tanks
Crew of 6
Aurora Approach: Habitation Transfer Module
Example of inflatable module
Transfer and in Mars orbit: about 750 days
Crew 6
2/3 Habitation, 1/3 storage
6 m diameter
Hard central core (3.3 m)and inflatable exterior shell (8.3m)
water jacket surrounding crew quarters in level 2
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14. Set-up of the simplified habitat for simulations
Multilayer  fixed component, corresponding to the basic vehicle structure
Shielding  optional components – e.g.: REMSIM modeled example cases included shielding consisting of water and polyethylene, with 5 and 10 cm thickness
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15. Equivalent dose results
Total equivalent dose in the phantom (mSv/day) with respect to shielding thickness
e.m. physics
e.m. + hadronic physics – bertini c.
e.m. + hadronic physics – binary c.
SIH + no shielding
2.15 cm Al
4. cm Al
SIH cm water
SIH + 5. cm water cm
mSv/day
WARNING
The simplified simulation model is
not adequate
for absolute dose calculations
Relative dose calculations are OK
A thicker shielding layer limits the astronaut’s exposure to the GCR
Water and polyethylene have equivalent shielding behaviour
The hadronic contribution to the dose should be taken into account
( ~ 20% )

16. Radiation Shielding for Space Exploration: the MoMa – COUNT Programme

17. ASI - MoMa-COUNT MoMa: from Molecules to Man
Studying the early aging effect in the space environment
MoMa: from Molecules to Man
Space Research Applied to the Improvement of the Life Quality of the Ageing Population
COUNT: Countermeasures
Contributing to the development of Biotechnological applications
Mandatory for the Human exploration and colonisation of the Solar System
Pursuing significant Earth spin-offs to develop countermeasures against aging, enhancing our life quality
05/05/2018
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18. MoMa-COUNT WBS
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19. MoMa-COUNT TAS-I Activities
Activity : development of methods and materials (flexible, rigid) to be used as radiation shielding
Goal: designing passive radiation shielding means to be used as effective physical countermeasures against radiations for
Interplanetary vehicles
Surface habitat design concepts
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20. MoMa-COUNT TAS-I Activities
Concepts validation by means of
on ground tests (accelerator)
on flight tests
MC simulations
Direct correlation between ground tests and flight tests is difficult
Simulations are the missing link, utilisation of advanced Montecarlo toolkits, such as GEANT4
Gain the know how to perform effective and reliable predictions on the behaviour of materials on real situation
05/05/2018
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21. MoMa-COUNT - Ground Tests
Test Campaign: summer 2007
Results 1 GeV/nucleon 56Fe beam tests
Adding mass after the external shield brings to a remarkable reduction of the delivered dose
Equipment and structures inside the module actually contribute to mitigate the radiation effects on astronauts
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22. MoMa-COUNT Conclusions
Goals reached within the MoMa-Count programme:
Assessment of absolute and relative radiation shielding effectiveness of pure and composite, multi-layered materials
Kevlar, chiefly used for MMOD shielding, was determined to be an effective radiation shielding material
Extension of knowledge and understanding of the radiation environment inside a spacecraft in LEO, gained with PARIDE experiment in FOTON (i.e. first estimation of neutron flux dose vs total ionising dose)
Acquisition of know-how in correlating experimental and simulation results
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23. TSA-I R&D ACTIVITIES STEPS / PEPS
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24. PESP/STEPS Purpose of the work
Previous work:
Spacecraft shielding materials have been irradiated at BNL with 1 GeV/n 56Fe ions measuring:
Dose Reduction
Bragg peak position
Purpose of this work:
Geant4 Radiation Analysis for Space (GRAS) Monte Carlo characterization of two actual space structures:
1 GeV 56Fe Ion fragmentation
1 GeV 56Fe dose reduction
1 GeV 56Fe secondary LET spectrum
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25. PEPS/STEPS Materials simulations
Simulated materials:
Aluminum alloy
Kevlar®
Nextel®
Multilayered structures
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26. G4 Hadronic cascade models1 Fe
GRAS G4Abrasion Model
Exp. Zeitlin et al., Rad. Meas., 2008
GRAS G4BinaryIonCascade model
10-1
Fragmentation [/source] C Ca
10-2 Si Be
7 g/cm2 Aluminum
10-3 5 10 15 20 25 30
Atomic number [Z]
Good agreement between experimental data (from literature) and the G4BinaryIonCascade hadronic model used in our simulations
05/05/2018
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27. Columbus-induced fragmentation
Aluminum 3.5 g/cm2 1
Columbus 3.5 g/cm2
Aluminum 15 g/cm2
Columbus+Outfitting 15 g/cm2
10-1
Fragmentation [/source]
10-2
10-3 5 10 15 20 25 30
Atomic number [Z]
Columbus enhances high-Z fragments as compared to Al eq.
leading to similar Al. 15 g/cm2 high-Z spectrum!
05/05/2018
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28. With internal outfit Only external shell
Columbus vs. Remsim fragmentation 1
With internal outfit
10-1
Fragmentation [/source]
10-2
Only external shell
10-3
REMSIM 1g/cm2
Columbus 3.5 g/cm2
REMSIM + Outfit 8.6 g/cm2
Columbus + Outfit 15 g/cm2
10-4 5 10 15 20 25 30
Atomic number [Z]
Columbus displays more secondaries (heavier structure)
The outfits lead to similar fragmentation spectra
05/05/2018
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29. Columbus dose-reduction5 10 15 20 25 30 35 40 Al
3.5 g/cm2
Columbus
Aluminum
15 g/cm2
Columbus+Outfitting
Experimental data
GRAS Simulation
% Dose reduction
Columbus structure is more effective than aluminum for a given areal density due to the presence of low-Z materials!
05/05/2018
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30. Remsim dose-reduction30 25 20
% Dose reduction 15
Experimental data
GRAS simulation 10 5
REMSIM 1 g/cm2
REMSIM + Water 8.6 g/cm2
The presence of water leads to a dose reduction similar to the Columbus structure with the outfitting
05/05/2018
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31. Primary Iron ions ~ 1.4 MeV cm2 mg-1 LET spectra
Columbus 3.5 g/cm2
Primary Iron ions
~ 1.4 MeV cm2 mg-1
[/source]
REMSIM 1 g/cm2
Linear Energy Transfer [MeV/cm]
The two structures induce similar LET spectra
Columbus displays more secondaries (heavier structure)
05/05/2018
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32. SpaceIT
63rd International Astronautical Congress
1 - 5 October Napoli, Italy
The ROSSINI Project: Radiation Shielding by ISRU and Innovative Materials for EVA, Vehicles and Habitats
Emanuele Tracino, Chiara La Tessa, Alessandra Menicucci Laurent Desorgher, Cesare Lobascio, and Marco Durante
05/05/2018
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33. ROSSINI RadiatiOn Shielding by ISRU and/or INnovative MaterIals for EVA, Vehicle and Habitat
A 2 year project funded by ESA started in January 2012
Prime contractor: Thales Alenia Space Italia
Subcon.: GSI (Test and data analysis), SpaceIT (MC Simulations)
Main Objectives:
Select innovative shielding materials and passive systems
Test under iron ion beam at 1 GeV/n (or equivalent)
Give recommendation and guidelines for the design and use of surface and transfer habitat implementing the ALARA principle
05/05/2018
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34. ROSSINI Test Campaign – single materials
Iron 1 NSRL/BNL
Bragg peak
Aluminum
Polyethylene
Moon & Mars Regolith
Dose Reduction
Moon Concrete
Cella Energy Material A & B
Microdosimetry
Moon concrete
Protons 2.5 NSRL/BNL
Dose reduction
Aluminum
Polyethylene
Moon and Mars Regolith
Cella Energy Material A & B
Titanium 1 GSI
Neutron & Proton Yield
Polyethylene
Moon Regolith
Mars Regolith
Moon Concrete
05/05/2018
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35. ROSSINI 1st Test Campaign @ NSRL June 2012 EGG counter set-up
05/05/2018
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36. ROSSINI 1st Test Campaign @ NSRL June 2012 Fe-56 962
ROSSINI 1st Test NSRL June 2012 Fe MeV/n Irradiation Results
05/05/2018
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37. ROSSINI Test Campaign @ NSRL June 2012 Fe-56 962
ROSSINI Test NSRL June 2012 Fe MeV/n Irradiation Results
05/05/2018
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38. ROSSINI Test Campaign @ NSRL June 2012 Fe-56 962
ROSSINI Test NSRL June 2012 Fe MeV/n Irradiation Results
05/05/2018
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39. Interplanetary Habitat Shielding hydrogen-rich and light materials
The light multilayer perform better than the others for dose reduction per g/cm2
The use of a Carbon Composite primary shell with the Columbus MDPS increases the total dose reduction decreasing the weight of the structure
Innovative materials “Cella Energy Material B” performs 18% better than HDPE and could be employed as a dedicated radiation protection layer
Light MDPS is derived by the ESA funded study “HVI Expand” and have the comparable ballistic performance as the Columbus MDPS with 1/3 of the mass. It is advantageous in terms of mass and dose reduction per unit of areal density
05/05/2018
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40. Future Outlook what we plan to do in the near future
Comparison of the test results with Geant4 and FLUKA simulations
Selection of new materials and configurations
New materials tests
Study Milestones:
November 2012  Study Review
1st quarter 2013  Test Readiness Review
End of 2013  Final Review
05/05/2018
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41. Copyright © NASA
thanks!
05/05/2018
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Copyright © NASA

42. HUMEX Study Recommendations
Achievements
HUMEX Study Recommendations
REMSIM output
Improve & advance risk assessment
develop risk criteria appropriate for exploratory Long Term Missions
integrate risk assessment of radiation hazards in a risk analysis
reduce uncertainties for exposure estimates
reduce uncertainties for dose effect relations (late & early)
TN1
TN2
Code
05/05/2018
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43. HUMEX Study Recommendations
REMSIM - Achievements
HUMEX Study Recommendations
REMSIM output
Minimise Radiation Exposure
optimise shielding design (material & thickness)
optimise mission design
- duration
- timeline relative to solar activity cycle
- guaranteed shelter accessibility
advance forecasting capabilities for solar particle events
monitor and document
- exposure history
- health status
TN2,TN4,Code
TN3
TN3, TN5
TN2, TN5
TN5
TN1, TN5 -
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44. ESA concept (from HMM CDF)
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45. Interior Configuration Transfer Module
HMM CDF
Interior Configuration Transfer Module
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46. HMM CDF (cont’d)
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47. Multi layer configuration
Geometry sets
Layer configuration
Multi layer configuration
SIH (Simplified Inflatable Habitat) + shielding configuration
SPE shelter
SIH (Simplified Inflatable Habitat) + shielding + shelter + partitions configuration
Complete vehicle
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48. Materials Kevlar Polyethylene Aluminum 2219-T851 Water
Materials analyzed in such configurations include – in order of priority – the following:
Kevlar
Polyethylene
Aluminum 2219-T851
Water
Nextel 312 AF62
Combitherm
Betacloth
Mylar
Nomex
Target is a box or cylinder of water. Depth(s) for dose determination: first voxel, 10 mm, 50 mm
05/05/2018
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49. Equivalent dose calculation
Method
Energy deposit in the phantom
Dose per event : D
Dose per second: where is the fluence
The fluence is calculated from the flux given by CREME

50. Equivalent dose calculation
Method
The fluence is calculated from the flux given by CREME
Aincidence
Projection of energy deposit on a plane
perpendicular to the incident beam direction
Calculate the radius r whose circumference
contains the 90% of the energy deposit ( ~ 20. cm )
A = l2 where l = 2 x r y X
Radius

51. Equivalent dose calculation
GCR
GCR p
GCR alpha
GCR C-12
GCR Si-28
GCR Fe-52
Method
Dose per second x Quality Factor = Equivalent Dose/s (quality factor from PDG)
Calculation of equivalent dose per day for each kind of GCR ion with respect to the depth in the phantom
Calculation of equivalent dose per day with respect to the depth in the phantom
Calculation of total equivalent dose per day,
based on the simulated ions
Q = 5 for protons
Q = 20 for ions

52. SPE shelter model Geant4 model Shelter air vacuum Phantom Geant4 model
SIH
SIH/shielding + additional 10. cm water shielding
Both GCR and SPE dosimetric effects have been studied
Dosimetric effect of e.m. physics, hadronic processes added on top
Shelter
vacuum
air
Multilayer (28 layers)
Phantom
Shelter
SIH + 10 cm water
GCR and SPE
particles
Geant4 model
Geant4 model
May
Bertini only
New:
Study of the dosimetric effect of different hadronic models
Calculation of equivalent dose of GCR in the phantom

53. Energy deposit – e.m. + hadronic physics
e.m. physics
e.m. + bertini approach
e.m. + binary approach
GCR p

54. Results – GCR, SIH + shielding + shelter
Total equivalent dose per day in the phantom, GCR:
34.86 mSv/day – e.m. physics
51.66 mSv/day – e.m. + hadronic physics – bertini c.
51.9 mSv/day – e.m. + hadronic physics – binary c.
Hadronic contribution
to the energy deposit ~ 48%
WARNING
The simplified simulation model is
not adequate
for absolute dose calculations
Relative dose calculations are OK

55. 3m
toroid
SHELTER
Toroidal shelter ( 2m, length 3m) integrated in the habitat scheme of the AURORA CDF concept. At the outer diameter the electric current can be supposed to be returned by a few conductors
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56. Active shields in Inflatable modules
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57. - the outer part of the system must be deployed or assembled in space.
electric current
B=0 inside
B 1/R
B=0 inside
B 1/R
return of the electric current
return of the electric current a)
-  the solenoidal configuration is not adequate and must be adopted a toroidal configuration where the field diminishes at the increasing of the radius;
-   the outer part of the system must be deployed or assembled in space. b)
05/05/2018
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58. REMSIM – Mars mission limits (RxTec)
The mission limits are based on stochastical effect considerations
(3% increase in death risk, as in less safe terrestrial occupations).
For shorter exposure to radiation, deterministic effects limits are more adequate for crew protection than stochastic effects limits.
The 1 year & 1 month limits are based on deterministic effect considerations; these limits shall be referred to BFO tissues.
The short time limits (1 hour & 1 minute) are intended as a SPE detection or co-detection for activating emergency procedures (assuming an average exposure to GCR of  0.5 Sv/h).
05/05/2018
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59. In Flight Tests(1/2) PARIDE : PARticle & Ion Dosimetry Experiment *
Main parameters
max altitude
304 km
min altitude
262 km
Orbit Inclination
63°
Mission Duration
12 days
On board the last Foton mission (Sep. 2007) to study the effectiveness of different radiation shelters
Detectors to evaluate the neutron component of the radiation field: Bubble Detectors Neutron Dosimeter (BDND)
Detectors to evaluate the ionizing component of the radiation field: Thermo-luminescence Detectors (TLD)
Aluminum and Kevlar shelters to assess their shielding capability
* Close cooperation with Marco Durante, Università Federico II, Napoli and Alba Zanini Università degli studi di Torino
05/05/2018
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60. On Flight Tests(2/2)
PARIDE : Results
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61. On Flight Tests Simulation
Neutron fluxes inside Foton M3 s/c obtained using GEANT4
The neutron dose per day calculated by simulations is about 6 µSv/d
the experimental data are about (65 ÷ 88) ± 20% µSv/d
Difference is due to the coarse approximations and simplifications made on materials and geometry
A = neutrons from GCR protons
B = neutrons from GCR alphas
C = neutrons from Van Allen trapped protons
05/05/2018
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62. Multilayered structures+
OUT IN
“Columbus” target aims to reproduce the shield of the ISS-Columbus module IN
OUT +
“Remsim” target aims to reproduce the shield of the next inflatable modules
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63. Shielding materials selection Target description
Innovative Materials
Cella Energy Material A
Cella Energy Material B
Cella Energy is an 'Advanced Materials and Technologies' sector company
safe, low-cost hydrogen storage proprietary technology
Visit:
05/05/2018
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64. Shielding materials selection Target description
In Situ Resource Utilization - ISRU Materials
Mars Regolith Simulant  Orbitec JSC Mars1A <1mm (0.93 g/cm3)
Moon Regolith Simulant  Orbitec JSC Lunar-1A <1mm (1.64 g/cm3)
Moon Concrete  Dinitech D-NA-1 (1.76 g/cm3)
05/05/2018
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65. Carbon Composite (Internal)
Shielding materials selection Target description
Multilayer – Tested with Iron 1 GeV/n for Dose Reduction and Microdosimetry
Columbus (ISS like shell) 3.8 g/cm2
Light Multilayer (C primary + soft MDPS) 1.4 g/cm2
Hybrid Multilayer A (Al primary + soft MDPS) 1.6 g/cm2
Hybrid Multilayer B (C primary + ISS MDPS) 3.6 g/cm2
Columbus
Aluminum (external)
Nextel Fabric
Kevlar/Epoxy Comp.
MLI
Aluminum (Internal)
Light Multilayer
Betacloth (external)
MLI
Nextel Fabric
Kevlar Fabric
Carbon Composite (Internal)
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66. ROSSINI 1st Test Campaign @ NSRL June 2012 Experimental set-up
Lunar Regolith
Lunar Concrete
Mars Regolith
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