Hyper Inflatables: Prefabricated Membranes And 3D

U.S. Department of the InteriorU.S. Geological SurveyScientific Investigations Map 3316Prepared for theMission OutlineSheet 1 of 2National Aeronautics and Space Administration180 55 MAP DESCRIPTION150 ErkhofEmde nfAv o ga droSo mme rfe ldACKNOWLEDGMENTS70 KarpinskiySe a re sS c h w ar z s c h i l dCo mpto nP o c z o b u t tRozhdestvenskiyCre mo na270 EBria ncho nCeatnaSyelvstNa nse nHe rmiteerBe l'ko v ich90 EPearyHa ynPa scalBa illaudMe tonIGO500 E60Siko rskyS chVal lisPe tzv a l–80 rö d ing erS c h r ö d i n g e rZe e manLippma nnSmith, D.E., Zuber, M.T., Neumann, G.A., Mazarico, E., Head, J.W., III, Torrence, M.H., and theLOLA Science Team, 2011, Results from the Lunar Orbiter Laser Altimeter (LOLA)—global,high-resolution topographic mapping of the Moon [abs.]: Lunar Planetary Science ConferenceXLII, Woodlands, Tex., Abstract 2350.VaSpeyerer, E.J., Robinson, M.S., Denevi, B.W., and the LROC Science Team, 2011, Lunar Reconnaissance Orbiter Camera global morphological map of the Moon [abs.]: Lunar PlanetaryScience Conference XLII, Woodlands, Tex., Abstract 2387.llisPlNumerovanckCro mme lin–70 Anto nia diFizea uPMinnae rtTooley, C.R., Houghton, M.B., Saylor, R.S., Peddie, C., Everett, D.F., Baker, C.L., and Safdie,K.N., 2010, Lunar Reconnaissance Orbiter mission and spacecraft design: Space ScienceReviews, v. 150, no. 1, p. 23–62, doi:10.1007/s11214-009-9624-4.lanckPra ndtlLe ma îtreBe rlageWagner, R.V., Speyerer, E.J., Robinson, M.S., and the LROC Science Team, 2015, New mosaickeddata products from the LROC Team [abs.]: Lunar Planetary Science Conference XLVI,Woodlands, Tex., Abstract 1473.Minko wskiWilliams, J.G., Boggs, D.H., and Folkner, W.M., 2008, DE421 Lunar orbit, physical librations, andsurface coordinates: Jet Propulsion Laboratory Interoffice Memorandum IOM335-JW,DB,WF-20080314-001, 1 moon coord iom.pdf.–60 21P0 Eoincar0 Eé15–55 180 55 SCALE 1:6 078 683 (1 mm 6.078683 km) AT 90 LATITUDEPOLAR STEREOGRAPHIC PROJECTION100090 EArchitectural Program20 separate crew quarters, galley, science stations, exercise facility, medical facilities, 6bathrooms, hygiene stations, manufacturing shop, greenhouse, laundry, at least 2 airlocks,operations control room, recreation facility. E300 Amundse nAshbroo kScholten, F., Oberst, J., Matz, K.-D., Roatsch, T., Wählisch, M., Speyerer, E.J., and Robinson,M.S., 2012, GLD100 - The near-global lunar 100 m raster DTM from LROC WAC stereoimage data: Journal of Geophysical Research, v. 117, no. E12, doi:10.1029/2011JE003926.Feature names on this sheet are approved by the IAU. All features greater than 85 km indiameter or length were included unless they were not visible on the map due to the small scale60 RISShoemakerShackletonSato, H., Robinson, M.S., Hapke, B., Denevi, B.W., and Boyd, A.K., 2014, Resolved Hapkeparameter maps of the Moon: Journal of Geophysical Research, Planets, v. 119, p. 17751805, doi: 10.1002/2013JE004580.NOMENCLATUREFRDe mona xSco ttCa be usDry ga lskiRobinson, M.S., Speyerer, E.J., Boyd, A., Waller, D., Wagner, R., and Burns, K., 2012, Exploringthe Moon with the Lunar Reconnaissance Orbiter Camera: International Archives of thePhotogrammetry, Remote Sensing and Spatial Information Sciences, v. XXXIX-B4, XXIIInternational Society for Photogrammetry and Remote Sensing Congress, Melbourne,Australia.To create the final base image, the original WAC mosaic that was produced by the LunarReconnaissance Orbiter Camera team in a Simple Cylindrical projection with a resolution of100m/pixel was projected into the Mercator and Polar Stereographic pieces. The images werethen scaled to 1: 10,000,000 for the Mercator part and 1:6,078,683 for the two Polar Stereographic parts with a resolution of 300 pixels per inch. The two projections have a common scaleat 56 latitude.W. BondREEHe lmho ltzHa use n270 EPo nté coula ntBo gusla wskyyEMA0 lRobinson, M.S., Brylow, S.M., Tschimmel, M., Humm, D., Lawrence, S.J., Thomas, P.C., Denevi,B.W., Bowman-Cisneros, E., Zerr, J., Ravine, M.A., Caplinger, M.A., Ghaemi, F.T., Schaffner, J.A., Malin, M.C., Mahanti, P., Bartels, A., Anderson, J., Tran, T.N., Eliason, E.M.,McEwen, A.S., Turtle, E., Jolliff, B.L., and Hiesinger, H., 2010, Lunar ReconnaissanceOrbiter Camera (LROC) instrument overview: Space Science Reviews, v. 150, no. 1-4, p.81–124, doi:10.1007/s11214-010-9634-2.The equatorial WAC images were orthorectified onto the Global Lunar Digital TerrainMosaic (GLD100, WAC-derived 100 m/pixel digital elevation model; Scholten and others, 2012)while the polar images were orthorectified onto the lunar LOLA polar digital elevation models(Neumann and others, 2010).Gärtne r33l0 Birminghami240 E30De La Rue70 J. Hersche laMalapertCrewThe base can support a rotating crew of 20-30.GoldschmidtSo uthBLe GentilNeumann, G.A., 2011, Lunar Reconnaissance Orbiter Lunar Orbiter Laser Altimeter reduced datarecord and derived products software interface specification, version 2.42, LRO-L-LOLA-4GDR-V1.0, NASA Planetary Data System (PDS), athttp://imbrium.mit.edu/DOCUMENT/RDRSIS.PDFThe WAC global mosaic shown here is a monochrome product with a normalized reflectance at 643 nm wavelength, and consists of more than 15,000 images acquired between November 2009 and February 2011 (Sato and others, 2014) using revised camera pointing (Wagner andothers, 2015). The solar incidence angle at the Equator changes 28 from the beginning to theend of each month. To reduce these incidence angle variations, data for the equatorial mosaicwere collected over three periods (January 20, 2010 to January 28, 2010, May 30, 2010 to June 6,2010, and July 24, 2010 to July 31, 2010). The South Pole mosaic images were acquired fromAugust 10, 2010 to September 19, 2010, and the North Pole images were acquired from April 22,2010 to May 19, 2010. Remaining gaps were filled with images acquired at other times withsimilar lighting conditions (Robinson and others, 2012). There is a brightness difference wherethe polar mosaics meet the equatorial mosaics because the polar images were acquired in adifferent season than the equatorial images, and the lunar photometric function is not perfectlyknown (Sato and others, 2014).80 Py tha gora sArno ldPingréMazarico, E., Rowlands, D.D., Neumann, G.A., Smith, D.E., Torrence, M.H., Lemoine, F.G., andZuber, M.T., 2012, Orbit determination of the Lunar Reconnaissance Orbiter: Journal ofGeodesy, v. 86, no. 3, p. 193–207.MAPPING TECHNIQUESBa rro wBo ussinga ultSchombe rge r–80 Lunar Reconnaissance Orbiter Project Lunar Geodesy and Cartography Working Group, 2008, Astandardized lunar coordinate system for the Lunar Reconnaissance Orbiter and lunar datasets: Lunar Reconnaissance Orbiter Project and Lunar Reconnaissance Orbiter Project LunarGeodesy and Cartography Working Group White Paper, v. 5, Paper-10-08.pdf.SitePermanent base at the Peary Crater in the Lunar North Pole.MAREHUMBOLDTIANUMBa bba geCa sa tusFolkner, W.M., Williams, J.G., and Boggs, D.H., 2009, The planetary and lunar ephemeris DE 421:Interplanetary Network Progress Report 42-178, 34 p., athttp://ipnpr.jpl.nasa.gov/progress report/42-178/178C.pdf.Longitude increases to the east and latitude is planetocentric, as allowed in accordance withcurrent NASA and U.S. Geological Survey standards (Archinal and others, 2011). The intersection of the lunar equator and prime meridian occurs at what can be called the Moon’s “meansub-Earth point.” The concept of a lunar “sub-Earth point” derives from the fact that the Moon’srotation is tidally locked to the Earth. The actual sub-Earth point on the Moon varies slightly dueto orbital eccentricity, inclination, and other factors. So a “mean sub-Earth point” is used todefine the point on the lunar surface where longitude equals 0 . This point does not coincide withany prominent crater or other lunar surface feature (Lunar Reconnaissance Orbiter Project LunarGeodesy and Cartography Working Group, 2008; Archinal and others, 2011).By rdXenophane sManzinus–70 MoretusKlapro thFolkner, W.M., Williams, J.G., and Boggs, D.H., 2008, The planetary and lunar ephemeris DE 421:Jet Propulsion Laboratory Memorandum IOM 343R-08-003, 31 p., 1.iom.v1.pdf.The Wide Angle Camera images were referenced to an internally consistent inertial coordinate system, derived from tracking of the LRO spacecraft and crossover-adjusted Lunar OrbiterLaser Altimeter (LOLA) data that were used together to determine the orbit of LRO in inertialspace (Smith and others, 2011). By adopting appropriate values for the orientation of the Moon,as defined by the International Astronomical Union (IAU; Archinal and others, 2011), the imageswere orthorectified into the planet-fixed coordinates (longitude and latitude) used on this map.The coordinate system defined for this product is the mean Earth/polar axis (ME) system,sometimes called the mean Earth/rotation axis system. The ME system is the method most oftenused for cartographic products of the past (Davies and Colvin, 2000). Values for the orientationof the Moon were derived from the Jet Propulsion Laboratory Developmental Ephemeris (DE)421 planetary ephemeris (Williams and others, 2008; Folkner and others, 2008; 2009) and rotatedinto the ME system. The LOLA-derived crossover-corrected ephemeris (Mazarico and others,2012) and an updated camera pointing provide an average accuracy of 1 km in the horizontalposition (Scholten and others, 2012).MilankovičPlaske ttGrue mbe rge rDavies, M.E., and Colvin, T.R., 2000, Lunar coordinates in the regions of the Apollo landers:Journal of Geophysical Research, v. 105, no. E8, p. 20,277–20,280.COORDINATE SYSTEM80 Ro se nbe rgerCurtiusArchinal, B.A. (Chair), A’Hearn, M.F., Bowell, E., Conrad, A., Consolmagno, G.J., Courtin, R.,Fukushim, T., Hestroffer, D., Hilton, J.L., Krasinsky, G.A., Neumann, G.A., Oberst, J.,Seidelmann, P.K., Stooke, P., Tholen, D.J., Thomas, P.C., and Williams, I.P., 2011, Report ofthe IAU Working Group on cartographic coordinates and rotational elements—2009: CelestialMechanics and Dynamical Astronomy, v. 109, no. 2, p. 101–135, doi:10.1007/s10569-0109320-4. E60E0 YablochkovBlanca nusObjectivesStudy the long-term effects of 1/6th gravity on humans, astronomical study during darkphases, act as a construction material hub for projects in and around cis-lunar space,serve as a fuel depot, EVA capabilities for exploration, and a testbed for permanent spaceagriculture.12240 EGamo wRo be rtsScheine rREFERENCESThe Mercator projection is used between latitudes 57 , with a central meridian at 0 longitude and latitude equal to the nominal scale at 0 . The Polar Stereographic projection is usedfor the regions north of the 55 parallel and south of the –55 parallel, with a central meridianset for both at 0 and a latitude of true scale at 90 and -90 , respectively. The adopted sphericalradius used to define the maps scale is 1737.4 km (Lunar Reconnaissance Orbiter Project LunarGeodesy and Cartography Working Group, 2008; Archinal and others, 2011). In projection, thepixels are 100 meters at the equator.Ste bbins E–60 –60 C l a v i u sThis map was made possible with thanks to NASA, the LRO mission, and the Lunar Reconnaissance Orbiter Camera team. The map was funded by NASA's Planetary Geology and Geophysics Cartography Program.PROJECTIONva n'tHo ff30E0 330 Ei–55 12Bused for printing. However, some selected well-known features less that 85 km in diameter orlength were included. For a complete list of the IAU-approved nomenclature for the Moon, see theGazetteer of Planetary Nomenclature at http://planetarynames.wr.usgs.gov. For lunar missionnames, only successful landers are shown, not impactors or expended orbiters.This image mosaic is based on data from the Lunar Reconnaissance Orbiter Wide AngleCamera (WAC; Robinson and others, 2010), an instrument on the National Aeronautics andSpace Administration (NASA) Lunar Reconnaissance Orbiter (LRO) spacecraft (Tooley andothers, 2010). The WAC is a seven band (321 nanometers [nm], 360 nm, 415 nm, 566 nm, 604nm, 643 nm, and 689 nm) push frame imager with a 90 field of view in monochrome mode, and60 field of view in color mode. From the nominal 50-kilometer (km) polar orbit, the WACacquires images with a 57-km swath-width and a typical length of 105 km. At nadir, the pixelscale for the visible filters (415–689 nm) is 75 meters (Speyerer and others, 2011). Each month,the WAC provided almost complete coverage of the Moon.60 300 ERo wland0 E210 0SCALE 1:6 078 683 (1 mm 6.078683 km) AT -90 LATITUDEPOLAR STEREOGRAPHIC PROJECTION5001000 KILOMETERS90 90 70 55 70 55 500100005001000 KILOMETERS–90 –90 –70 –55 –70 –55 NORTH POLAR REGIONSOUTH POLAR REGIONNorth240 E210 E270 E300 E30 E0 330 E60 E90 ERo wland120 E150 ECo mpto nHUMBOLDTIANUMCo ulo mbMAREFRIGORISAssumptions- The fully realized BFR rocket is relative in size and function to the version presented at IAC 2017 conference.- The remaining fuel of the BFR rocket on the moon’s surface is around 110 tons (half empty).- Advances in space-applicable robotics continue, particularly ones for construction which are an aspirational element of the project.- There is a growing commercial and industrial demand for space in the Cis-lunar region.- An inflatable membrane thickness of 8-12 cm utilizing advanced materials is sufficient to block out micro-meteorites and most radiation.- The inflatable will have two means of egress.Vo ltaCa rnotaUSCASESMOLACI T USATISOBmAMORI SDBa orsrlo awApo llo 17De c. 11, 1972)daeusr(GDSurv e y or 5(Sep. 11, 1967)TRANQUILLITATISApo llo 11ProclusPALUSSOMNIaima A riaMARED orsusaSINUSHONORISR imNrsteLiD orCaucSINUSCONCORDIAELo mo noso vMOMARECRISIUMGodda rdAnderso nGuyotSpe nce r Jo ne sOstwaldhyNe pe rSINUSSEFlemingMAREMARGINISLuna 24(Aug. 18, 1976)Luna 20(Fe b. 21, 1972)E NAR EM OVISCOVe rna dskiyISdelovLa rmo rUc k l anUSppatSha ynGBuSINUSJo lio tDHa orsarkers a SmirnovDorCle o me desKurchatovrcha ven noatC motaArTAURUSKuSe y fe rtMONTESLuna 21Jan. 15, 1973)RVallisBohrCatenerrsa vDo tyaeTeEMMAREVAPORUMSINUSmnSzila rdANNSHAINS UL A RUMaSuMax we llRa yle ighEOsumLACUSDOLORI SRH y im ag inuste nWie ne rRicha rdso nHa hnorTEESCo pe rnicusSurv e y or 6S E R E N I TAT ISDVe stineARSMSApo llo 15(July 30, 1971)UChandlerH. G.WellsCaH a r k h e b iMVaelneHe ve liusMARERie ma nnSOMNIORUMNTrkPA TUumD o rs raA zaZichHe dinMusheCARNPENNIUReinerGammaLeicRLuna 9Feb. 3, 1966)aMTE SNTSINUSAESTUUMLAennaMONMOELaR im u sanC a rdatMiche lso nteACCTsa nderMontesHarbingerPA LUSREDIN ISAristarchusOVascoda Ga maCaMontesArchimedesPUTCa mp be llISLACUSSPEIPo sido niusMAREmWey limEinsteinSINUSLUNICUS50 GausssuKekuléMcMa thFe rsma niPo y nti ngllichs S röPRMachaHerodotusLuna 13Eddingto n (Dec. 24, 1966)Mose leyolte rStruveBe llicsaor netrBuBe rknerRo be rtso nMitraDPa re nagogrorRusse llosAHeJo uleFitzge ra ldMentDumaLa ueIMBRIUMrsillDoScKo v ale v ska y ad'Ale mbe rtMillika nORMessa laLACUSMontesSpitzbergenmCo ckcroft30 MPAlex a nderMARErsuL o r e n t zLa rmo rRö ntgenTEFabryCAUMonsPitonLuna 17(Nov. 17, 1970)DoNe rnstSMORTISSCharlie rAtla sCURima G. BondMontesShRimaRimae GerardLASANUMonsRümkerAristo tele sPEL a n d a uA lpALPe rrinell isesLACUSMonsPicoS I NUSVaESFo wle rMontesRectiI RI DUMOCEGera rdNTSte fanWegenerMontesTeneriffeJuraar pMOSchle singe rvo nBé késyS I NUS RO RI SDe by ePa ra skev o po ulo sEndymio naeR imP la toPlatoRe pso ld50 180 57 MAREB i r k h o f fMAREUNDARUMBa nachiew iczLo ba che v skiyBa bco ckIbn Firna sVe tchinkinCM e a te nande leev180 57 Me ndele e vPa pale ksiMandel'shtamSchuste r30

Crew ConfigurationCargo ConfigurationCargo Crew Configuration

Rigid CarbonFiber FrameFoldable CarbonFiber Structure1500 mm3215 mmTruss DesignWidest Point: 1600 mmTallest Point: 1500 mmFolded Length: 90 mmDeployed Length: 3215 mm1600 mm90 mm

Fuel TankHolds 240 tons of CH4Common DomeSeparates CH4 and 02Header TankHolds landing propellant during transitCargo BayPressurized to unpressurized volumeOxygen TankHolds 860 tons of liquid 02Crew CabinPressurized volume

3D Printing Material (AlSiC)ISRU Collector & ProcessorNASA Chariot ChassisFeeder Hatch for 3DPrinterGraphite ProcessorHatchSiliconeCollectorDozer BladeCameraGraphiteCollectorSiliconeProcessor HatchCameraContentAluminumSilicon Carbide(AMC640XA)40% Silicon Carbide,60% AluminumTensileStrength570 MPaDensityMeltingPointYoung’sModulus2.90 g/cm³400 C40 GPaKey AdvantagesWear resistance, Low coefficient of thermalexpansion, crack-resistance, class 1 gradematerial by ESA testing, very high chemicaland corrosion resistance, no porosity.

3D Printer RoverPacked TrussMaterial Transfer ArmISRU to 3D Printer TransferMounting plate forhorizontal truss3D Printer HeadCamera

Heat Panels3D Printer TrussFoldable CarbonFiber Structure1562 mm3215 mm1804 mmHeat PanelsMade of Minco Polyimide Thermofoil, which work in (-200) C to200 C temperature ranges and are NASA approved. The panelsrequire 17.49 watts per 1 unit (as drawn) to heat to 130 C, thenecessary temp to cause the carbon fiber to revert to its originalposition. It takes 15 minutes for each section to be deployed.90 mmTruss Design1 unit (as drawn to the right)Volume: 8,714.78 cm3Total Weight: 15.60 kg22 meter length (20 meter structure): 0.630 meters folded (7 Units)Total Weight: 109.20 kg

Heat Panels3D Printer TrussFoldable CarbonFiber Structure1562 mm3215 mm1804 mmHeat PanelsMade of Minco Polyimide Thermofoil, which work in (-200) C to200 C temperature ranges and are NASA approved. The panelsrequire 17.49 watts per 1 unit (as drawn) to heat to 130 C, thenecessary temp to cause the carbon fiber to revert to its originalposition. It takes 15 minutes for each section to be deployed.90 mmTruss Design1 unit (as drawn to the right)Volume: 8,714.78 cm3Total Weight: 15.60 kg22 meter length (20 meter structure): 0.630 meters folded (7 Units)Total Weight: 109.20 kg

Heat Panels3D Printer TrussFoldable CarbonFiber Structure1562 mm3215 mm1804 mmHeat PanelsMade of Minco Polyimide Thermofoil, which work in (-200) C to200 C temperature ranges and are NASA approved. The panelsrequire 17.49 watts per 1 unit (as drawn) to heat to 130 C, thenecessary temp to cause the carbon fiber to revert to its originalposition. It takes 15 minutes for each section to be deployed.90 mmTruss Design1 unit (as drawn to the right)Volume: 8,714.78 cm3Total Weight: 15.60 kg22 meter length (20 meter structure): 0.630 meters folded (7 Units)Total Weight: 109.20 kg

Heat Panels3D Printer Truss41 mFoldable CarbonFiber Structure70 1562 mm30 m3215 mm1804 mmHeat PanelsMade of Minco Polyimide Thermofoil, which work in (-200) C to200 C temperature ranges and are NASA approved. The panelsrequire 17.49 watts per 1 unit (as drawn) to heat to 130 C, thenecessary temp to cause the carbon fiber to revert to its originalposition. It takes 15 minutes for each section to be deployed.90 mmTruss Design1 unit (as drawn to the right)Volume: 8,714.78 cm3Total Weight: 15.60 kg30 meter length (20 meter structure): 0.630 meters folded (7 Units)Total Weight: 109.20 kg

ScienceHygieneMaintenance & EVALife SupportPower SupplyPublic & Private AreasAir & Water ContaminantDetectors5 square metersLaundry5 square metersMedical Facility35 square metersExercise Chamber50 square metersFood Production200 square metersWorkshop50 square metersEVA Vehicles100 square metersWaste Recovery andTreatment10 square meters3 Toilets15 square metersRecreation30 square metersGalley Dining120 square metersGeneral Laboratory50 square metersEquipment Storage20 square metersAirlock Nodes10 square metersThermal Control andWaste Heat Rejection15 square metersHumidity Control5 square meters2 Hand WashingStations 4 Shower40 square metersBase Operations ControlRoom60 square meters2 Shower 2 HandWashing Stations20 square metersISRU Collection (Water)10 square metersCrew Quarters100 square metersAstronomicalObservatory20 square metersFood Storage40 square metersPortable Water Supply40 square metersFuel Depot100 square metersSolar Array Field550 square meters

Total Volume23000 m336 m22 mCBMHatch 2Bay DoorCBMHatch 1Total Volume293 m3Power CommsFluid TransferPenetrationPenetrationUHT Transmitters& Satellite uplinks3.7 m Bay Door

ECLSS & SubsystemsCO2 ScrubberWater Filtration UnitWater TankPower and Databoxes

Floor Panels Levels8m4m4m4m4m3m2m2m2m1mConnection Method 1Connection Method 2

Columns Levels8m4m4m4m4m3m2m2m2m

Interior Perspectives

Thank You

Future and Current Rocket Arsenaldeliverable to LEO (kg)deliverable to Moon (kg)fairing size (m)Ariane 520,00010,0005.4 x 17Proton Briz-M22,2266,3204.35 x 9.75Falcon 922,8008,3005.2 x 13.1Delta IV Heavy28,79014,2205 x 19.1Falcon Heavy63,80026,7005.1 x 13.7SLS Block IB70,00035,0008.4 x 31Glenn 386,35038,6005.4 x tbdSLS Block II130,00065,00010 x 31BFR Cargo Variant500,000150,0009.6 x 17

Examined Materials ChartProposed advantagesProven for space applications, has been selectedas metal of choice of Orion capsules. Corrosiveresistant.Does not take blunt forces well.Medium weightLightest structural material. Used when highstrength is not necessary, but where a thick,light form is desired, or if higher stiffness isneeded.Temperatures as low as 200 F(93 C) produce considerablereduction in the yield strength.Aluminum(Weldalite 049-T8)97-98% Aluminum, 2-3%Lithium710 MPa2.66 g/cm³600-655 C69 GPaAluminumMagnesium SiliconAlloyAluminum, Magnesium,Silicon230 MPa1.80 g/cm³436 C48 GPa95% carbon, 5% resin3310 MPa1.79 g/cm³3652 CResin:260 C30 GPaDoes not fatigue, high stiffness, high tensilestrength, low weight, high chemical resistance,high temperature tolerance and low thermalexpansion, non poisonous, biologically Inert andis a shape-memory polymer, non-corrosive.At temperatures above 66 C,carbon fiber resin strength willbe reduced. Cannot easily handleIsotrophic force, strength focusedon direction of fiber.Aluminum 60611-4% Magnesium, 1% Silicon, 95-98%Aluminum290 MPa2.70 g/cm³585 C68.9 GPaGreat tension strength, very common aluminumproduct in aircraft structures. Corrosionresistant. Very wieldable. Verified as stable inultra-high vacuum chambers.Not very strong against bruntforces.Aluminum 70752-3% Magnesium, 1%Magnese, 98-97%Aluminum572 MPa2.81 g/cm³635 C72 GPaCorrosion resistance, no exhibit age hardening,nor does it need a precipitation heat treatmentto promote hardening. Weldability is good.Machinability is only fair to poor.40% Silicon Carbide,60% Aluminum570 MPa2.90 g/cm³400 C40 GPaWear resistance, Low coefficient of thermalexpansion, crack-resistance, class 1 gradematerial by ESA testing, very high chemical andcorrosion resistance, no porosity.Very new material that hasn’tbeen used in space structurallyyet.Silicon, Iron1,586 MPa6.70 g/cm³4892 C206 GPaLighter than aluminum based alloys,Very prone to get rusty, requiresresin to protect it. Not a strongtensile material, flamable, notbendable.Carbon Fiber(IM10)AluminumSilicon Carbide(AMC640XA)FerrosiliconUnit LegendMpa: MegapascalsGPa: Gigapascalsmm: Millimeterscm: Centimetersg: Grams C: Celsius

- An inflatable membrane thickness of 8-12 cm utilizing advanced materials is sufficient to block out micro-meteorites and most radiation. - The inflatable will have two means of egress. Any use of trade, product, or firm names in this publication is for descriptive purposes o