Hyper Inflatables

Home , Arnold (crater), Babbage (crater), Baillaud (crater), Barrow (crater), Birmingham (crater), Brianchon (crater)

Hyper Inflatables: Prefabricated Membranes and 3D Printed Exoskeletons in Space Sasakawa International Center for Space Architecture Zachary Taylor credit: NASA credit: SpaceX

credit: Foster & Partners / ESA credit: NASA Columbus Destiny Harmony Kibo

MLM MRM1 MRM2 MPLM

PMM Tranquility Unity Zarya Proposed Apollo-Era Station Toroid inflatable station concept The Echo 1a credit: NASA credit: NASA credit: NASA SLS Block II Fairing BFR Cargo Fairing Volume: 80,563 m3 Volume: 1,166 m3 Volume: 780 m3 Ø: 53 m Weight: 100,000 kg Weight: 70,000 kg B330 B2100 No Exoskeleton Exoskeleton Manipulated Volume 330 m3 2100 m3 1500 m3 25000 m3 20000 m3 Grasshopper Simulation

Reinforced Unenforced 5 m

Membrane Composition Polytetrafluoroethylene (PTFE) Coating Purpose: UV stabilizer Density: 2.19 kg/m3 Thickness: 0.04 cm

Demron Fabric Purpose: high energy gamma radiation, micrometeroid protection Density: 3.14 kg/m3 Thickness: 5.04 cm Hydrogenated Boron Nitride Nanotube (BNNT) Purpose: neutron radiation protection Density: 2.10 kg/m3 Thickness: 4.12 cm Précontraint 402 N Membrane Purpose: water and air seal Density: 1.00 kg/m3 Thickness: 0.04 cm U.S. Department of the Interior Prepared for the Scientific Investigations Map 3316 U.S. Geological Survey National Aeronautics and Space Administration Sheet 1 of 2

180° 0° 5555°° –55°

Rowland 150°E MAP DESCRIPTION used for printing. However, some selected well-known features less that 85 km in diameter or 30°E 210°E length were included. For a complete list of the IAU-approved nomenclature for the Moon, see the This image mosaic is based on data from the Lunar Reconnaissance Orbiter Wide Angle 330°E 6060°° Gazetteer of Planetary Nomenclature at http://planetarynames.wr.usgs.gov. For lunar mission Clavius –60°–60˚ Camera (WAC; Robinson and others,Mission 2010), an instrument on the National Aeronautics and Outline names, only successful landers are shown, not impactors or expended orbiters. Space Administration (NASA) Lunar Reconnaissance Orbiter (LRO) spacecraft (Tooley and others, 2010). The WAC is a seven band (321 nanometers [nm], 360 nm, 415 nm, 566 nm, 604 nm, 643 nm, and 689 nm) push frame imager with a 90° field of view in monochrome mode, and ACKNOWLEDGMENTS Birkhoff Emden 60° field of view in color mode. From the nominal 50-kilometer (km) polar orbit, the WAC This map was made possible with thanks to NASA, the LRO mission, and the Lunar Recon- Scheiner Avogadro acquires images with a 57-km swath-width and a typical length of 105 km. At nadir, the pixel naissance Orbiter Camera team. The map was funded by NASA's Planetary Geology and Geophys- scale for the visible filters (415–689 nm) is 75 meters (Speyerer and others, 2011). Each month, ics Cartography Program. Blancanus Sommerfeld the WAC provided almost complete coverage of the Moon. Rosenberger REFERENCES Curtius PROJECTION Archinal, B.A. (Chair), A’Hearn, M.F., Bowell, E., Conrad, A., Consolmagno, G.J., Courtin, R., Stebbins The Mercator projection is used between latitudes ±57°, with a central meridian at 0° Fukushim, T., Hestroffer, D., Hilton, J.L., Krasinsky, G.A., Neumann, G.A., Oberst, J., Gruemberger 7070°° longitude and latitude equal to the nominal scale at 0°. The Polar Stereographic projection is used Seidelmann, P.K., Stooke, P., Tholen, D.J., Thomas, P.C., and Williams, I.P., 2011, Report of –70° Manzinus Gamow for the regions north of the +55° parallel and south of the –55° parallel, with a central meridian van't Roberts the IAU Working Group on cartographic coordinates and rotational elements—2009: Celestial Hoff 120°E set for both at 0° and a latitude of true scale at +90° and -90°, respectively. The adopted spherical Mechanics and Dynamical Astronomy, v. 109, no. 2, p. 101–135, doi:10.1007/s10569-010- Moretus 60°E Klaproth 240°E Yablochkov radius used to define the maps scale is 1737.4 km (Lunar Reconnaissance Orbiter Project Lunar 9320-4. 300°E Karpinskiy Geodesy and Cartography Working Group, 2008; Archinal and others, 2011). In projection, the Davies, M.E., and Colvin, T.R., 2000, Lunar coordinates in the regions of the Apollo landers: pixels are 100 meters at the equator.Objectives Journal of Geophysical Research, v. 105, no. E8, p. 20,277–20,280. Casatus COORDINATE SYSTEM Folkner, W.M., Williams, J.G., and Boggs, D.H., 2008, The planetary and lunar ephemeris DE 421: Seares Jet Propulsion Laboratory Memorandum IOM 343R-08-003, 31 p., at Milankovič The Wide Angle Camera images were referenced to an internally consistent inertial coordi- ftp://ssd.jpl.nasa.gov/pub/eph/planets/ioms/de421.iom.v1.pdf. th nate system, derived from tracking of the LRO spacecraft and crossover-adjusted Lunar Orbiter Folkner, W.M., Williams, J.G., and Boggs, D.H., 2009, The planetary and lunar ephemeris DE 421: Boussingault Laser Altimeter (LOLA) data thatStudy were used together to determine the the orbit of LRO inlong-term inertial effects of 1/6 gravity on humans, astronomical study during dark Interplanetary Network Progress Report 42-178, 34 p., at Pontécoulant space (Smith and others, 2011). By adopting appropriate values for the orientation of the Moon, Boguslawsky http://ipnpr.jpl.nasa.gov/progress_report/42-178/178C.pdf. Schomberger 8080°° Schwarzschild as defined by the International Astronomical Union (IAU; Archinal and others, 2011), the images –80° were orthorectified into the planet-fixed coordinates (longitude and latitude) used on this map. Lunar Reconnaissance Orbiter Project Lunar Geodesy and Cartography Working Group, 2008, A Helmholtz Pingré Bailly The coordinate system defined for this product is the mean Earth/polar axis (ME) system, standardized lunar coordinate system for the Lunar Reconnaissance Orbiter and lunar datas- Plaskett Compton phases, act as a construction material hub for projects in and around cis-lunar space, sometimes called the mean Earth/rotation axis system. The ME system is the method most often ets: Lunar Reconnaissance Orbiter Project and Lunar Reconnaissance Orbiter Project Lunar used for cartographic products of the past (Davies and Colvin, 2000). Values for the orientation Geodesy and Cartography Working Group White Paper, v. 5, at Poczobutt of the Moon were derived from the Jet Propulsion Laboratory Developmental Ephemeris (DE) http://lunar.gsfc.nasa.gov/library/LunCoordWhitePaper-10-08.pdf. Demonax Scott 421 planetary ephemeris (Williams and others, 2008; Folkner and others, 2008; 2009) and rotated Malapert Rozhdestvenskiy Mazarico, E., Rowlands, D.D., Neumann, G.A., Smith, D.E., Torrence, M.H., Lemoine, F.G., and into the ME system. The LOLA-derivedserve crossover-corrected asephemeris (Mazarico a andfuel others, depot,Zuber, M.T., 2012, Orbit determination EVA of the Lunar capabilitiesReconnaissance Orbiter: Journal of for exploration, and a testbed for permanent space Le Gentil 2012) and an updated camera pointing provide an average accuracy of ~1 km in the horizontal Geodesy, v. 86, no. 3, p. 193–207. Cabeus position (Scholten and others, 2012). Neumann, G.A., 2011, Lunar Reconnaissance Orbiter Lunar Orbiter Laser Altimeter reduced data Shoemaker Longitude increases to the east and latitude is planetocentric, as allowed in accordance with Drygalski Nansen record and derived products software interface specification, version 2.42, LRO-L-LOLA-4- Cremona Hermite Bel'kovich current NASA and U.S. Geological Survey standards (Archinal and others, 2011). The intersec- Hausen Amundsen 270°E 90°E agriculture. GDR-V1.0, NASA Planetary Data System (PDS), at 270°E 90°E Shackleton Brianchon tion of the lunar equator and prime meridian occurs at what can be called the Moon’s “mean http://imbrium.mit.edu/DOCUMENT/RDRSIS.PDF sub-Earth point.” The concept of a lunar “sub-Earth point” derives from the fact that the Moon’s Peary Robinson, M.S., Brylow, S.M., Tschimmel, M., Humm, D., Lawrence, S.J., Thomas, P.C., Denevi, rotation is tidally locked to the Earth. The actual sub-Earth point on the Moon varies slightly due B.W., Bowman-Cisneros, E., Zerr, J., Ravine, M.A., Caplinger, M.A., Ghaemi, F.T., Schaff- Catena Sylvester Hayn to orbital eccentricity, inclination, and other factors. So a “mean sub-Earth point” is used to ner, J.A., Malin, M.C., Mahanti, P., Bartels, A., Anderson, J., Tran, T.N., Eliason, E.M., Ashbrook define the point on the lunar surface where longitude equals 0°. This point does not coincide with Byrd McEwen, A.S., Turtle, E., Jolliff, B.L., and Hiesinger, H., 2010, Lunar Reconnaissance Xenophanes any prominent crater or other lunar surface feature (Lunar Reconnaissance Orbiter Project Lunar Pascal MARE Orbiter Camera (LROC) instrument overview: Space Science Reviews, v. 150, no. 1-4, p. Sikorsky Geodesy and Cartography Working Group, 2008; Archinal and others, 2011). HUMBOLDTIANUM 81–124, doi:10.1007/s11214-010-9634-2. Schrödinger SiteMAPPING TECHNIQUES Robinson, M.S., Speyerer, E.J., Boyd, A., Waller, D., Wagner, R., and Burns, K., 2012, Exploring Vallis the Moon with the Lunar Reconnaissance Orbiter Camera: International Archives of the The WAC global mosaic shown here is a monochrome product with a normalized reflec- Photogrammetry, Remote Sensing and Spatial Information Sciences, v. XXXIX-B4, XXII Petzval tance at 643 nm wavelength, and consists of more than 15,000 images acquired between Novem- International Society for Photogrammetry and Remote Sensing Congress, Melbourne, 8080°° ber 2009 and February 2011 (Sato and others, 2014) using revised camera pointing (Wagner and –80° Schrödinger Australia. Zeeman Pythagoras others, 2015). The solar incidencePermanent angle at the Equator changes ~28° from the beginning base to the at the Peary Crater in the Lunar North Pole. Sato, H., Robinson, M.S., Hapke, B., Denevi, B.W., and Boyd, A.K., 2014, Resolved Hapke Baillaud end of each month. To reduce these incidence angle variations, data for the equatorial mosaic were collected over three periods (January 20, 2010 to January 28, 2010, May 30, 2010 to June 6, parameter maps of the Moon: Journal of Geophysical Research, Planets, v. 119, p. 1775- 2010, and July 24, 2010 to July 31, 2010). The South Pole mosaic images were acquired from 1805, doi: 10.1002/2013JE004580. Lippmann August 10, 2010 to September 19, 2010, and the North Pole images were acquired from April 22, Scholten, F., Oberst, J., Matz, K.-D., Roatsch, T., Wählisch, M., Speyerer, E.J., and Robinson, V a l is P la n c k Meton 2010 to May 19, 2010. Remaining gaps were filled with images acquired at other times with M.S., 2012, GLD100 - The near-global lunar 100 m raster DTM from LROC WAC stereo Babbage similar lighting conditions (Robinson and others, 2012). There is a brightness difference where image data: Journal of Geophysical Research, v. 117, no. E12, doi:10.1029/2011JE003926. Goldschmidt the polar mosaics meet the equatorial mosaics because the polar images were acquired in a 300°E Smith, D.E., Zuber, M.T., Neumann, G.A., Mazarico, E., Head, J.W., III, Torrence, M.H., and the 240°E different season than the equatorial images, and the lunar photometric function is not perfectly LOLA Science Team, 2011, Results from the Lunar Orbiter Laser Altimeter (LOLA)—global, Barrow 60°E Numerov known (Sato and others, 2014). 120°E Arnold Crew high-resolution topographic mapping of the Moon [abs.]: Lunar Planetary Science Conference De La Rue Crommelin 7070°° The equatorial WAC images were orthorectified onto the Global Lunar Digital Terrain XLII, Woodlands, Tex., Abstract 2350. –70° South J. Herschel Mosaic (GLD100, WAC-derived 100 m/pixel digital elevation model; Scholten and others, 2012) Speyerer, E.J., Robinson, M.S., Denevi, B.W., and the LROC Science Team, 2011, Lunar Recon- Antoniadi while the polar images were orthorectified onto the lunar LOLA polar digital elevation models naissance Orbiter Camera global morphological map of the Moon [abs.]: Lunar Planetary (Neumann and others, 2010). The base can supportScience Conference XLII, Woodlands,a rotatingTex., Abstract 2387. crew of 20-30. Fizeau Planck Minnaert To create the final base image, the original WAC mosaic that was produced by the Lunar Tooley, C.R., Houghton, M.B., Saylor, R.S., Peddie, C., Everett, D.F., Baker, C.L., and Safdie, Reconnaissance Orbiter Camera team in a Simple Cylindrical projection with a resolution of Prandtl Birmingham W. Bond K.N., 2010, Lunar Reconnaissance Orbiter mission and spacecraft design: Space Science 100m/pixel was projected into the Mercator and Polar Stereographic pieces. The images were Lemaître Gärtner Reviews, v. 150, no. 1, p. 23–62, doi:10.1007/s11214-009-9624-4. then scaled to 1: 10,000,000 for the Mercator part and 1:6,078,683 for the two Polar Stereo- Berlage graphic parts with a resolution of 300 pixels per inch. The two projections have a common scale Wagner, R.V., Speyerer, E.J., Robinson, M.S., and the LROC Science Team, 2015, New mosaicked at ±56° latitude. data products from the LROC Team [abs.]: Lunar Planetary Science Conference XLVI, Woodlands, Tex., Abstract 1473. Minkowski M A R E F R I G O R I S NOMENCLATURE Williams, J.G., Boggs, D.H., and Folkner, W.M., 2008, DE421 Lunar orbit, physical librations, and surface coordinates: Jet Propulsion Laboratory Interoffice Memorandum IOM 6060°° Feature names on this sheetArchitectural are approved by the IAU. All features greater than 85 km in Program –60° 330°E 335-JW,DB,WF-20080314-001, at 210°E diameter or length were included unless they were not visible on the map due to the small scale Poincaré 30°E 20 separate crewftp://ssd.jpl.nasa.gov/pub/eph/planets/ioms/de421_moon_coord_iom.pdf. quarters, galley, science stations, exercise facility, medical facilities,150°E 6 5555°° –55° 0° 180°

SCALE 1:6 078 683 (1 mm = 6.078683 km) AT 90° LATITUDE bathrooms, hygiene stations, manufacturing shop, greenhouse,SCALE 1:6laundry, 078 683 (1 mm = 6.078683 km) AT -90at° LATITUDE least 2 airlocks, POLAR STEREOGRAPHIC PROJECTION POLAR STEREOGRAPHIC PROJECTION 1000 500 0 500 1000 KILOMETERS 1000 500 0 500 1000 KILOMETERS 90° 90° –90° –90° 70° 70° operations control room, recreation facility. –70° –70° 55° 55° –55° –55° NORTH POLAR REGION SOUTH POLAR REGION North 180° 210°E 240°E 270°E 300°E 330°E 0° 30°E 60°E 90°E 120°E 150°E 180° 57° 57° Rowland MARE Birkhoff HUMBOLDTIANUM Compton Coulomb MARE FRIGORIS Volta Endymion Rimae Carnot Plato von d'Alembert Plato Assumptions Repsold Békésy SINUS RORIS

50° MONTES ALPES 50° Debye Montes Jura Teneriffe Aristoteles arp Paraskevopoulos h LACUS TEMPORIS d Vallis Alpes r S Montes a r s Schlesinger e Recti e t - The fully realized BFR rocket is relative in size and functiona to the version presented at IAC 2017 conference.Atlas Millikan Stefan G n

m Mons LACUS

e i Campbell

R Pico M

SINUS m

Wegener

Ri Gerard O IRIDUM MORTIS LACUS C SPEI Fowler Chandler - The remaining fuel of the BFR rocket on the moon’sE surface is around 110 tons (half empty). Perrine Landau Fabry H. G. A Mons Mons Wiener Rümker Piton Wells N Luna 17 CAUCASUS Alexander Catena Sumner U (Nov. 17, 1970) Messala Riemann MARE Harkhebi Ca S LACUS SOMNIORUM ten Kurchatov a Ku - Advances in space-applicable robotics continue, particularly ones for construction which are an aspirational element of the project. r c Dorsum Scilla h a Charlier Gauss to Nernst v Montes d Spitzbergen n o

Dorsum Heim B Vestine Szilard

Röntgen MONTES . Lorentz IMBRIUM SINUS G Shayn

Larmor Dorsum Zirkel Posidonius a Richardson - There is a growing commercial and industrial demand for space in the Cis-lunar region. im

LUNICUS R Hahn Cockcroft Kovalevskaya MARE Larmor 30° Maxwell 30° v Rayleigh Dorsum o Seyfert

Azara r

Laue PALUS i MONTES Luna 21 MARE ANGUIS ArtamonovCatena Montes Agricola PUTREDINIS m

Joule S Fitzgerald Russell Schr Montes Apollo 15 Jan. 15, 1973) TAURUS MARE ö a is t - An inflatable membrane thickness of 8-12 cm utilizing advancede materials is sufficient to blocks out micro-meteorites and most radiation. Dorsa ll Montes Archimedes (July 30, 1971) Joliot Lomonosov a r r Burnet i Cleomedes Berkner V o Harbinger MOSCOVIENSE Parenago SE RE NITATIS D

Struve S D Aristarchus U M o Vernadskiy N r LACUS I O s Dorsa Robertson Bell Herodotus N u r Tetyaev N N m e el Moseley Luna 13 T t SINUS p E B s BONITATIS p P E u i O - The inflatable will have two means of egress. (Dec. 24, 1966) A S c L k Eddington la m nd a rs Apollo 17 u S H D o s E A AMORIS r MARE Mach T E Dec. 11, 1972) o Mitra Fersman P N M Poynting O U D R M LACUS S Kekulé Wey l Einstein MONTES CARPATUS McMath O DOLORIS Goddard Proclus CRISIUM Fleming Dorsa Anderson Vasco C MARE PALUS Barlow Dorsa MARE da Gama SOMNI E SINUS VAPORUM Harker L SINUS R Luna 24 MARGINIS Rima AESTUUM im SINUS Guyot L MARE (Aug. 18, 1976) Spencer Jones HONORIS a CONCORDIAE Cardanus A C Ostwald Copernicus au

Vallis C Bohr Luna 9 c atena R MARE Rima hy Neper Papaleksi Feb. 3, 1966) Hyginus Rima Ariadaeus U Vetchinkin MARE Lobachevskiy Leuschner (GDL) M TRANQUILLITATIS Ibn Firnas Catena Reiner UNDARUM Luna 20 Catena Mandel'shtam Tsander Gamma Banachiewicz (Feb. 21, 1972) Michelson I N S U L A R U M Babcock Mendeleev Schuster Michelson (GIRD) Surveyor 5 Mendeleev Hedin Surveyor 6 (Sep. 11, 1967) Kibal'chich Hevelius SINUS Apollo 11 SINUS MARE Hertzsprung (Nov. 10, 1967) Catena MEDII Rimae Hypatia(July 20, 1969) SUCCESSUS SPUMANS MARE Gregory 0° 0° East

West Vening Meinesz Surveyor 1 Apollo 14 MARE Luna 16 Wy ld Saha (June 2, 1966) Apollo 12 SINUS e Lipskiy Vavilov i (Sep. 20, 1970) Catena Lucretius (RNII) (Feb. 5, 1971) k SMYTHII Riccioli (Nov. 19, 1969) i Gilbert e G Korolev S C O R Ventris E D a Icarus T I Grimaldi Surveyor 3 Hipparchus s L Schlüter Fra Mauro Vallis r Hirayama Daedalus N L Capella o Chaplygin E (April 20, 1967) Apollo 16 Kästner Love O R D Daedalus M A (April 21, 1972) ASPERITATIS Dorsa Dorsa Ewing E S R O MARE Mons Mawson Langrenus N T O Ptolemaeus Keeler O K Penck Langemak M AUTUMNILACUS Montes Riphaeus FECUNDITATIS Perepelkin Heaviside COGNITUM Albategnius Theophilus Pasteur Meitner Fridman Letronne LACUS VERIS Paschen Alphonsus Cyrillus Ansgarius Doppler Galois MARE Catena Kondratyuk Abulfeda NECTARIS Montes Vendelinus Zwicky Aitken Gassendi Pyrenaeus Isaev Arzachel Catharina Hilbert Rimae Sirsalis Sklodowska MARE Rupes Recta Vertregt Sternfeld Darwin MARE Fermi Gagarin Balmer Tsiolkovskiy ORIENTALE R u Fracastorius Hecataeus p V MARE s e Catena Paracelsus a Lamarck u s Curie

Gerasimovich l l Humboldt l Alden

a NUBIUM i s Levi-Civita p

p Rimae P i Purbach a HUMORUM H Sacrobosco Petavius Liebig l

A i e l Petavius t Phillips LACUS t z Humboldt Neujmin Rupes a a

i s Scaliger M c SOLITUDINIS im Rupes Mercator O R Regiomontanus h Pavlov N K Leeuwenhoek T O Vieta Pitatus Piccolomini Snellius Van de Graaff –30° E O –30° S R Barnard Milne Rima Hesiodus MARE A PALUS R EPIDEMIARUM Thomson E Lagrange Deslandres Walther L Parkhurst Chebyshev M L Bolyai O D I Gemma Frisius Abel Jules Oppenheimer N C O R LACUS Wurzelbauer Verne INGENII Brouwer T E S V Eötvös a Piazzi EXCELLENTIAE Furnerius l l Apollo i s Langmuir Blackett Davisson LACUS TIMORIS MARE B Leibnitz o Surveyor 7 Leibnitz u Brenner Vallis Lundmark v (Jan. 10, 1968) a Buffon r d Orontius Stöfler Maurolycus Roche Vallis Inghirami Lamb Koch Wilhelm Vallis Baade Ty cho Van der Mee AUSTRALE Waals Ryder Schickard Pauli Lagalla Rimae Rheita Von Kármán Janssen Chrétien Janssen Inghirami Lebedev Heraclitus Mendel Longomontanus –50° –50°

Schiller Maginus Lyot Hopmann

Vallis Planck Phocylides Vlacq Bose Hess Lippmann Hommel Minkowski Poincaré Rosenberger Planck –57° –57° 180° 210°E 240°E 270°E 300°E 330°E 0° 30°E 60°E 90°E 120°E 150°E 180° (150°W) (120°W) (90°W) (60°W) (30°W) South

Descriptions of nomenclature used on map are listed at SCALE 1:10 000 000 (1 mm = 10 km) AT 0˚ LATITUDE Prepared on behalf of the Planetary Geology and Geophysics Program, http://planetarynames.wr.usgs.gov/ MERCATOR PROJECTION Solar System Exploration Division, Office of Space Science, National Aeronautics and Space Administration 2000 1000 500 0 500 1000 2000 KILOMETERS Edited by Kate Jacques; digital cartography by Vivian Nguyen Manuscript approved for publication October 28, 2014 57° 57°

40° 40° 20° 20° 0° 0°

Image Map of the Moon

Any use of trade, product, or firm names in this publication is for descriptive purposes only By and does not imply endorsement by the U.S. Government Printed on recycled paper 1 1 1 1 2 For sale by U.S. Geological Survey, Information Services, Box 25286, Federal Center, Trent M. Hare, Rosalyn K. Hayward, Jennifer S. Blue, Brent A. Archinal, Mark S. Robinson, Emerson J. Denver, CO 80225, 1–888–ASK–USGS Digital files available at http://pubs.usgs.gov/sim/3316/ 1U.S. Geological Survey; 2 2 3 3 4 4 Suggested citation: Hare, T.M., Hayward, R.K., Blue, J.S., Archinal, B.A., Robinson, M.S., Speyerer, 2 Robert V. Wagner, David E. Smith, Maria T. Zuber, Gregory A. Neumann, and Erwan Mazarico Arizona State University; Speyerer, E.J., Wagner, R.V., Smith, D.E., Zuber, M.T., Neumann, G.A., and Mazarico, E., 3 ISSN 2329-1311 (print) Massachusetts Institute of Technology; ISSN 2329-132X (online) 2015, Image mosaic and topographic map of the moon: U.S. Geological Survey Scientific 4 2015 NASA Goddard Space Flight Center http://dx.doi.org/10.3133/sim3316 Investigations Map 3316, 2 sheets, http://dx.doi.org/10.3133/sim3316. Crew Configuration Cargo Configuration Cargo + Crew Configuration Rigid Carbon Fiber Frame

Foldable Carbon Fiber Structure

1500 mm

3215 mm

Truss Design Widest Point: 1600 mm 1600 mm Tallest Point: 1500 mm 90 mm Folded Length: 90 mm Deployed Length: 3215 mm

Fuel Tank Common Dome Cargo Bay 2 Holds 240 tons of CH4 Separates CH4 and 0 Pressurized to unpressurized volume

Header Tank Oxygen Tank Crew Cabin Holds landing propellant during transit Holds 860 tons of liquid 02 Pressurized volume 3D Printing Material (AlSiC) ISRU Collector & Processor

NASA Chariot Chassis

Feeder Hatch for 3D Graphite Processor Printer Hatch

Silicone Collector Dozer Blade

Graphite Camera Collector Silicone Camera Processor Hatch

Tensile Melting Young’s Content Strength Density Point Modulus Key Advantages

Aluminum 40% Silicon Carbide, 570 MPa 2.90 g/cm³ 400°C 40 GPa Wear resistance, Low coefficient of thermal Silicon Carbide 60% Aluminum expansion, crack-resistance, class 1 grade (AMC640XA) material by ESA testing, very high chemical and corrosion resistance, no porosity. 3D Printer Rover ISRU to 3D Printer Transfer

Packed Truss Material Transfer Arm Mounting plate for horizontal truss 3D Printer Head

Camera Heat Panels 3D Printer Truss

Foldable Carbon Fiber Structure

1562 mm

3215 mm

1804 mm 90 mm Heat Panels Truss Design Made of Minco Polyimide Thermofoil, which work in (-200)°C to 1 unit (as drawn to the right) 200°C temperature ranges and are NASA approved. The panels Volume: 8,714.78 cm3 require 17.49 watts per 1 unit (as drawn) to heat to 130°C, the Total Weight: 15.60 kg necessary temp to cause the carbon fiber to revert to its original 22 meter length (20 meter structure): 0.630 meters folded (7 Units) position. It takes 15 minutes for each section to be deployed. Total Weight: 109.20 kg Heat Panels 3D Printer Truss

Foldable Carbon Fiber Structure

1562 mm

3215 mm

Foldable Carbon Fiber Structure

1562 mm

3215 mm

41 m 70° Foldable Carbon Fiber Structure

1562 mm

30 m 3215 mm

1804 mm 90 mm Heat Panels Truss Design Made of Minco Polyimide Thermofoil, which work in (-200)°C to 1 unit (as drawn to the right) 200°C temperature ranges and are NASA approved. The panels Volume: 8,714.78 cm3 require 17.49 watts per 1 unit (as drawn) to heat to 130°C, the Total Weight: 15.60 kg necessary temp to cause the carbon fiber to revert to its original 30 meter length (20 meter structure): 0.630 meters folded (7 Units) position. It takes 15 minutes for each section to be deployed. Total Weight: 109.20 kg Science Hygiene Maintenance & EVA

Life Support Power Supply Public & Private Areas

Air & Water Contaminant Laundry Medical Facility Exercise Chamber Food Production Workshop EVA Vehicles Detectors 5 square meters 35 square meters 50 square meters 200 square meters 50 square meters 100 square meters 5 square meters

Waste Recovery and 3 Toilets Recreation Galley + Dining General Laboratory Equipment Storage Airlock Nodes Treatment 15 square meters 30 square meters 120 square meters 50 square meters 20 square meters 10 square meters 10 square meters

Thermal Control and Humidity Control 2 Hand Washing Base Operations Control 2 Shower + 2 Hand ISRU Collection (Water) Waste Heat Rejection 5 square meters Stations + 4 Shower Room Washing Stations 10 square meters 15 square meters 40 square meters 60 square meters 20 square meters

Crew Quarters Astronomical Food Storage Portable Water Supply 100 square meters Observatory 40 square meters 40 square meters 20 square meters

Fuel Depot Solar Array Field 100 square meters 550 square meters Total Volume 23000 m3 36 m

22 m

CBM Hatch 2

Bay Door

CBM Hatch 1

Total Volume 293 m3 UHT Transmitters & Satellite uplinks

Power + Comms 3.7 m Bay Door Penetration Fluid Transfer Penetration ECLSS & Subsystems

CO2 Scrubber

Water Filtration Unit

Water Tank Power and Data boxes Floor Panels + Levels

4m 3m 2m 2m 2m

1 m Connection Method 1 Connection Method 2 Columns + Levels

4m 3m 2m 2m 2m Interior Perspectives

Thank You Future and Current Rocket Arsenal

Ariane 5 Proton Briz-M Falcon 9 Delta IV Heavy Falcon Heavy SLS Block IB Glenn 3 SLS Block II BFR Cargo Variant deliverable to LEO (kg) 20,000 22,226 22,800 28,790 63,800 70,000 86,350 130,000 500,000 deliverable to Moon (kg) 10,000 6,320 8,300 14,220 26,700 35,000 38,600 65,000 150,000 fairing size (m) 5.4 x 17 4.35 x 9.75 5.2 x 13.1 5 x 19.1 5.1 x 13.7 8.4 x 31 5.4 x tbd 10 x 31 9.6 x ~17 Examined Materials Chart

Proposed Material Tensile Melting Young’s Key Key Characteristics Content Strength Density Point Modulus Advantages Disadvantages 5 Aluminum 97-98% Aluminum, 2-3% 710 MPa 2.66 g/cm³ 600-655°C 69 GPa Proven for space applications, has been selected Does not take blunt forces well. Lithium as metal of choice of Orion capsules. Corrosive Medium weight (Weldalite 049-T8) resistant. Lightest structural material. Used when high Temperatures as low as 200 °F Aluminum Aluminum, Magnesium, 230 MPa 1.80 g/cm³ 436°C 48 GPa strength is not necessary, but where a thick, (93 °C) produce considerable Silicon Magnesium Silicon light form is desired, or if higher stiffness is reduction in the yield strength. Alloy needed.

Carbon Fiber 95% carbon, 5% resin 3310 MPa 1.79 g/cm³ 3652°C 30 GPa Does not fatigue, high stiffness, high tensile At temperatures above 66°C, (IM10) Resin: strength, low weight, high chemical resistance, carbon fiber resin strength will 260°C high temperature tolerance and low thermal be reduced. Cannot easily handle expansion, non poisonous, biologically Inert and Isotrophic force, strength focused is a shape-memory polymer, non-corrosive. on direction of fiber.

Aluminum 6061 1-4% Magnesium, 290 MPa 2.70 g/cm³ 585°C 68.9 GPa Great tension strength, very common aluminum Not very strong against brunt <1% Silicon, 95-98% product in aircraft structures. Corrosion forces. Aluminum resistant. Very wieldable. Verified as stable in ultra-high vacuum chambers. Aluminum 7075 2-3% Magnesium, <1% 572 MPa 2.81 g/cm³ 635°C 72 GPa Corrosion resistance, no exhibit age hardening, Machinability is only fair to poor. Magnese, 98-97% nor does it need a precipitation heat treatment Aluminum to promote hardening. Weldability is good.

Aluminum 40% Silicon Carbide, 570 MPa 2.90 g/cm³ 400°C 40 GPa Wear resistance, Low coefficient of thermal Very new material that hasn’t Silicon Carbide 60% Aluminum expansion, crack-resistance, class 1 grade been used in space structurally (AMC640XA) material by ESA testing, very high chemical and yet. corrosion resistance, no porosity.

Ferrosilicon Silicon, Iron 1,586 MPa 6.70 g/cm³ 4892°C 206 GPa Lighter than aluminum based alloys, Very prone to get rusty, requires resin to protect it. Not a strong tensile material, flamable, not bendable.

Unit Legend Mpa: Megapascals GPa: Gigapascals mm: Millimeters cm: Centimeters g: Grams °C: Celsius