Tholus.Core 1

THOLUS.CORE 1 / PLANETARY REBIRTH MISSION ARCHITECTURE FEASIBILITY STUDY

CIRT (INTERNATION COUNCIL FOR TERRAFORMING RESEARCH) ROUTE DE MEYRIN 385, 1217 MEYRIN, SWITZERLAND

CIRT

REVISED 2015.11.03

THOLUS.CORE 1

SOLAR WIND

STRONG MAGNETIC FIELD: SIGNIFICANT/CONSISTENT PROTECTION WEAK ‘UMBRELLA’ MAGNETOSPHERE: INTERMITTENT PROTECTION

EARTH

MARS

1.0

EXECUTIVE SUMMARY

BRIEF

FEASIBILITY

CIRT (THE INTERNATION COUNCIL OF TERRAFORMING RESEARCH) IS A SCIENTIFIC THINK-TANK FOCUSED ON DELIVERING ROBUST, HIGH-QUALITY PROPOSALS UNSOLICITED, AND IRRESPECTIVE OF CURRENT POLITICAL OR ECONOMIC FEASIBILITY. AS SUCH, CIRT HAS TO DATE DEVELOPED SEVERAL

MARS’ CORE (PREDOMINANTLY CONSISTING OF FeS: IRON SULPHIDE AND NICKEL) IS CURRENTLY

MARS TERRAFORMING PROPOSALS.

THE PHENOMENON INVOLVES IRON AND NICKEL PARTICLES ON THE OUTER (COOLER) EDGE OF THE CORE COOLING AND SOLIDIFIYING, INCREASING IN DENSITY AND SINKING GRADUALLY TO THE CENTRE, IN A CONTINUOUS CYCLE. THE PROCESS IS EFFECTIVELY A WEAKER VERSION OF THE CORE DYNAMO EFFECT THAT IS THE GOAL OF THOLUS.CORE 1, SUGGESTING THAT MARS REQUIRES ONLY A CRITICAL ENERGY TO REACH THE DYNAMO THRESHOLD NEEDED FOR REBIRTH.

PARTIALLY LIQUIFIED, IN A PROCESS TERMED THE “SNOWING CORE” PHENOMENON.

UNFORTUNATELY, A MAJOR OBSTACLE TO THE DEVELOPMENT AND REALISATION OF REVOLUTIONARY TERRAFORMING MISSIONS IS THE COMBINATION OF HIGH COST, HIGH TECHNICAL RISK AND A LACK OF POLITICAL SUPPORT. PLANETS OTHER THAN EARTH CANNOT BE MADE HABITABLE WITHOUT INVESTMENT OF HUNDREDS OF BILLIONS OF DOLLARS, OR THE SUPPORT OF GOVERNMENTS REPRESENTING BILLIONS OF PEOPLE. HOWEVER, SUCH AN ENDEAVOUR MAY BECOME FEASIBLE IN THE NEAR FUTURE, PERHAPS DUE TO UNFORESEEN POLITICAL OR ENVIRONMENTAL DEVELOPMENTS. IT IS UNDER THIS PRESUMPTION THAT CIRT HAS UNDERTAKEN A FEASIBILITY STUDY OF TERRAFORMING MARS THROUGH THE REIGNITION OF ITS CORE, AND HENCE THE RE-ESTABLISHMENT OF ITS MAGNETOSPHERE.

COST

THE APPROXIMATE TOTAL COST OF THE THOLUS.CORE 1 PROPOSAL IS $120 TRILLION OVER THE LIFE OF THE PROJECT, THOUGH CIRT CONSIDERS THIS AFFORDABLE IN COMPARISON TO CURRENT

PROPOSAL

EXPENDITURE ON NUCLEAR DECOMMISSIONING ($32 BILLION TO DATE IN THE US ALONE).

CIRT PROPOSES THE REIGINITION OF MARS’ CORE THROUGH THE RELEASE OF SUFFICIENT ENERGY TO RESTART THE CORE DYNAMO EFFECT, VIA AN EXPLOSION NEAR THE CORE EDGE. THE PROPOSAL HAS BEEN NAMED “THOLUS.CORE 1.”

ALTERNATIVES

THE PROPOSED MISSION ARCHITECTURE IS PRESENTED IN DETAIL IN THIS FEASIBILITY STUDY, BUT MAY BE SUMMARISED AS FOLLOWS: 1.

2.

3.

GATHER/REFINE SUFFICIENT EXPLOSIVE MATERIAL. TRANSPORT EXPLOSIVE MATERIAL TO MARS. DRILL HOLE FROM SURFACE TO CORE EDGE.

4.

PLACE EXPLOSIVE MATERIAL NEAR CORE EDGE AND DETONATE.

ACHIEVING THE RESTORATION OF THE MAGNETOSPHERE BY OTHER MEANS IS CONSIDERED INFEASIBLE. ALTERNATIVE METHODS INCLUDE THE GENERATION OF AN ARTIFICIAL MAGNETOSPHERE BY SATELLITES (SHORT-TERM/FALLIBLE) AND THE INSERTION OF AN ADDITIONAL BODY INTO MARS’ ORBIT (SUCH AS AN ASTEROID) TO GENERATE A MAGNTEOSPHERE BY ACTION OF TIDAL FORCES (NOT POSSIBLE WITH CURRENT TECHNOLOGIES).

SUFFICIENT EXPLOSIVE ENERGY EXISTS IN GLOBAL NUCLEAR WEAPONS, POWER GENERATION AND WASTE MATERIALS. CORE REIGNITION MAY BE ACHIEVED THROUGH THE REPURPOSING OF THIS GLOBAL NUCLEAR STOCKPILE. CIRT ESTIMATES 900,000,000TJ IS REQUIRED TO RESUSCITATE THE CORE DYNAMO EFFECT (FOS 1.2).

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FEASIBILITY STUDY

ROUTE DE MEYRIN 385, 1217 MEYRIN, SWITZERLAND

1.0

MISSION ARCHITECTURE

2063

2053

2043

2042

2041

2040

2039

2038

2037

2036

2035

2034

PROPOSED TIMELINE

PRE-LAUNCH: COLLECTION/PROCESSING OF NUCLEAR WEAPONS AND WASTE MATERIAL FOR TRANSPORTATION.

BI-ANNUAL LASER LAUNCH SEQUENCE: 150,000 CAPSULES OF HIGHLY CONCENTRATED NUCLEAR MATERIAL TRANSPORTED FROM EARTH TO MARS IN PREPARATION FOR CORE REIGNITION.

PHASE 1 LAUNCH: ROBOTIC CREW/ RAPID PROTOTYPING MACHINES + PRIMARY MANUFACTURING EQUIPMENT

REMOTE ESTABLISHMENT PHASE: CONSTRUCTION OF BASE /PRIMARY LIFE SUPPORT SYSTEM (LSS) INFRASTRUCTURE DRILLING + BASE PRODUCTION PHASE: PERIODIC ARRIVAL/DEPARTURE OF CREW MEMBERS (REACHING PEAK OF 100).

LSS PROCESSES FULLY ESTABLISHED/SEMI-AUTOMATED. FOCUS PRIMARILY ON DRILLING + CAPSULE COLLECTION/STORAGE PROCESS.

BASE CONSOLIDATION PHASE: OXYGEN/NUTRIENT SUPPLIES ACCRUED IN PREPARATION FOR ADDITIONAL HUMAN CREW MEMBERS PHASE 2 LAUNCH: PILOT HUMAN CREW + ADDITIONAL MANUFACTURING/LSS EQUIPMENT

3033

2933

2833

2733

2633

2533

2433

2333

2233

2133

2123

2113

2103

2083

2073

2093

TERRAFORMING PHASE 1: ECOPOEISIS (100 YEARS). RESTORATION OF TERRAFORMING PHASE 2: PHOTOSYNTHESIS.(10,000-100,000 YEARS).SELF-PERPETUATING ATMOSPHERIC DENSIFICATION/WARMING ATMOSPHERE (DUE TO PRESENCE OF MAGNETOSPHERE).GROWTH OF (POSITIVE FEEDBACK GREENHOUSE EFFECT). SURFACE WATER. ENDEMIC MICROBIAL LIFE.

PHASE 3 LAUNCH: EVACUATION OF ALL PERSONNEL IN PREPARATION FOR DETONATION/CORE REIGNITION

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MARS VS. EARTH

MARS EARTH LENGTH OF DAY LENGTH OF ORBIT ORBITAL ECCENTRICITY AV. DIST. FROM SUN

24H 39 M 35.2S 687 DAYS 1.36-1.60AU 228,000,000KM

23H 56M 4.1S 365.3 DAYS 0.0167AU 152,000,000KM

SURFACE TEMP. EQUATORIAL AV. TEMP.

-153/+35°C -41°C

-96/+71°C +30°C

ATMOSPHERIC 613 KPA 101.3KPA PRESSURE ATMOSPHERIC O2: 0.145% O2: 0.145% COMPONENTS CO: 0.0557% N2: 78% CO2: 96.0%

AV. WIND SPEED 31.3M/S 19.2M/S 112.7KM/H 69.1KM/H MAX. WIND SPEED 44.7M/S 113.0M/S 160.9KM/H 407.9KM/H GRAVITY 3.7M/S2 9.8M/S2 AXIAL TILT 25.2° 23.5° SATELLITES DEIMOS MOON PHOBOS

DIAMETER 3390KM 6370KM CORE RADIUS 1794KM 1220KM APPROX. MAX. 4000°C 6000°C

MARS GLOBAL SURVEYOR (1996-2006)

MARS EXPRESS (2003-19) VIKING 1 (1975-80)

90°

90° VIKING 2 (1975-78)

MARS RECON. (2006-21)

PHOENIX (2008)

60°

60°

VIKING 1 (1975)

MARS ONE (2024-2029)

30°

30°

PATHFINDER/SOJOURNER (1997)

CURIOSITY (2012-28)

0° OPPORTUNITY (2004-23)

150°

120°

90°

60°

30°

30°

330°

60°

M.O.M. (2014- )

SPIRIT (2004-10)

MAVEN (2014- )

30°

0°

300°

270°

240°

210°

60°

PHOBOS 2 (1988-89)

2001 MARS ODYSSEY (2001-16)

90°

90°

MARINER 9

MARS 2 (1971-72)

(1971-72)

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ROUTE DE MEYRIN 385, 1217 MEYRIN, SWITZERLAND

2.0 GEOLOGICAL/RESOURCES SURVEY BASE LOCATION INVESTIGATION

1

VOLCANIC CONSTRUCTS

1

2

CRATERED PLAINS

2

CRATERED TERRAIN

MAX. WATER CONCENTRATION AT POLES (ICE)`

MAJORITY IRON DEPOSITS IN CHAOTIC TERRAIN

PERMANENT ICE

PLAINS UNDIVIDED

CRATERED TERRAIN

VOLCANIC PLAINS`

PLAINS UNDIVIDED

FORMATIONS

3

WATER

3

IRON

CIRT HAS CONDUCTED A DESK SURVEY OF 3 X POTENTIAL BASE LOCATIONS, IDENTIFIED AS POSSIBLY PROVIDING THE NECESSARY RESOURCE AND ACCESSIBILITY REQUIREMENTS OF THE MISSION. 1. THOLUS PLAIN 2. VALLES MARINERIS 3. HELLAS BASIN CIRT RECOMMENDS THE SITE BE LOCATED IN THE THOLUS PLAIN, A BASIN TO THE WEST OF THARSIS VOLCANIC REGION. FOR COMPLETENESS, A BRIEF SUMMARY OF THE VALLES MARINERIS AND HELLAS

1

BASIN ASSESSMENTS HAS BEEN INCLUDED FOR REFERENCE. VALLES MARINERIS:

2

THE SITE HAS RELATIVELY POOR ACCESS TO WATER, BUT IS -6000M RL, SO PROVIDES A SIGNIFICANTLY DENSER ATMOSPHERE, REDUCING THE BURDEN ON ARTIFICIAL PRESSURISATION SYSTEMS. THE VALLEY IS EQUATORIAL, MAXIMISING OPPORTUNITY FOR SOLAR HARVESTING. NATURAL CAVES ALONG THE VALLEY EDGE MAY ALSO PROVIDE PROTECTION FROM SOLAR RADIATION, THOUGH THE EXISTENCE OF SUCH CAVES REMAINS SPECULATION. HELLAS BASIN: THE POTENTIAL SITE HAS GOOD PROXIMITY TO RESOURCES AND LIES AT -8200M RL, PROVIDING THE DENSEST POSSIBLE ATMOSPHERIC CONDITIONS ON THE MARS SURFACE. HOWEVER, THE BASIN CONTAINS 10-100M OF EXTREMELY UNCOMPACTED/LOOSE SEDIMENTARY DEPOSIT (AEOLIAN DEPOSIT). IN ADDITION, RECENT OBSERVATIONS HAVE LED TO THE CONCLUSION THAT THE MAJORITY OF DUST STORM EVENTS ORIGINATE FROM THE BASIN, SO THE BASE IS LIKELY TO BE ENGULFED IN DUST ON A VERY REGULAR BASIS. THE BASIN IS ALSO FAR SOUTH OF THE EQUATOR, REDUCING THE OPPORTUNITY TO EFFECTIVELY HARVEST SOLAR ENERGY. SIMILARLY TO VALLES MARINERIS, HELLAS BASIN IS ALSO SURROUNDED

BY EXTREMELY ROUGH TERRAIN, MAKING TRAVEL/EXPLORATION EFFORTS BEYOND THE BASE INFEASIBLE. THOLUS PLAIN: THOLUS PLAIN IS A REGION OF FORMER OCEANIC CRUST AND HAS THEREFORE BEEN SELECTED TO MINIMISE DRILLING EFFORT (NORTHERN HEMISPHERE CRUST IS DRAMATICALLY THINNER THAN SOUTHERN, DUE TO DIFFERENTIATION TERMED “HEMISPHERIC DICHOTOMY PHENOMENON”: AVERAGE DEPTH APPROX. 50KM) AND RETAIN PROXIMITY TO CRITICAL RESOURCES (WATER, IRON, BASALT, ETC.).

THE SITE IS SURROUNDED BY RELATIVELY TRAVERSABLE TERRAIN AND THE EQUATORIAL LOCATION MAXIMISES LIGHT INTENSITY (BENEFICIAL FOR SOLAR ENERGY HARVESTING). IN ADDITION, THE PRESENCE OF LARGE DEPOSITS OF RARE EARTH ELEMENTS IS HIGHLY LIKELY, DUE TO THE DETECTION OF HIGH LEVELS OF PHOSPHORUS IN THE REGION.

3

PRECISE LOCATION OF PROPOSED SITE: 18.910°N, 192.623°E

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ROUTE DE MEYRIN 385, 1217 MEYRIN, SWITZERLAND

3.0 NUCLEAR TRANSFER STRATEGY LOCATION/QUANTITY OF NUCLEAR MATERIAL: EARTH

RUSSIA ARSENAL: 1600 ACTIVE 6400 INACTIVE 45,000 PEAK U.S.A. ARSENAL: 2100 ACTIVE 5200 INACTIVE 31,000 PEAK

16,400/ 73,800,000TJ NUCLEAR WEAPONS DECLARED GLOBALLY .

ESTIMATED GLOBAL NUCLEAR RESERVES SUFFICIENT TO MORE THAN QUADRUPLE STOCKPILE: 354,200,000TJ. 1390 TONNES HEU (HIGHLY ENRICHED URANIUM).

490 TONNES SEPARATED PLUTONIUM. 45,000 TONNES RADIOACTIVE WASTE. TOTAL EXTANT NUCLEAR ENERGY: APPROX. 830,000,000TJ. FORECAST TOTAL BY 2050: 1,050,000TJ.

POTENTIAL LAUNCH SITES/TRAJECTORIES: EARTH

VIK

CAPE CANAVERAL

CRASH ZONE: LAUNCH OVER WATER/ LOW POPULATED ARES

CARNVARVON

ATACAMA 150,000 TOTAL LAUNCHES REQUIRED. 9 X SITES SELECTED ON THE FOLLOWING CRITERIA: HIGH ALTITUDE, PROXIMITY TO COASTLINE, EXISTING LAUNCH INFRASTRUCTURE

OVERBERG

CIRT RECOMMENDS A STAGED LAUNCH METHODOLOGY, WITH GRADUAL RAMPING UP OF LAUNCH FREQUENCY TO AVOID CATASTROPHIC FAILURE AND POTENTIAL NUCLEAR CONTAMINATION THROUGH VEHICLE CRASH.

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3.0 NUCLEAR TRANSFER STRATEGY EARTH-MARS TRAJECTORY

EARTH AT POSITION 2

NUCLEAR TRANSFER PERIOD

NUCLEAR LAUNCH VEHICLES WILL TRAVELTO MARS VIA THE HOHMANN TRANSFER ELLIPSE (9 MONTH DURATION/400,000,000KM).

MANNED FLIGHTS WILL TRAVEL VIA AN IMPULSIVE TRANSFER, REQUIRING MAX. PROPULSION LOAD (6 MONTH DURATION).

LAUNCH WINDOWS OCCUR APPROX. BIANNUALLY (25 MONTHS) OVER A 2 MONTH DURATION. CIRT ESTIMATES THAT 46. 3 LAUNCH WINDOWS (94 YEARS) ARE REQUIRED TO ACHIEVE THE DELIVERY OF 900,000,000TJ OF NUCLEAR ENERGY TO MARS. THIS TIMELINE ASSUMES AN AVERAGE RATE OF 6 LAUNCHES PER DAY PER SITE (MAXIMUM 10), ALLOWING FOR WEATHER/EQUIPMENT DELAYS.

EARTH AT POSITION 1

POTENTIAL LANDING SITES/TRAJECTORIES: MARS

POTENTIAL NUCLEAR RECOVERY ZONES

THOLUS.CORE 1 BASE

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4.0 NUCLEAR TRANSFER OPERATION EARTH LAUNCH FACILITY

NUCLEAR PROCESSING FACILITY

LAUNCH VEHICLE TRAJECTORY

SOLID FUEL ROCKET ZONE OF INFLUENCE

CAPE CANAVERAL LAUNCH COMPLEX 39B

PRIMARY LASER ZONE OF INFLUENCE

SECONDARY LASER ZONE OF INFLUENCE PRIMARY LASER ARRAY

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ROUTE DE MEYRIN 385, 1217 MEYRIN, SWITZERLAND SECONDARY LASER ARRAY

EXTRA-HABITAT ACTIVITY (EH.A.) SUIT

NOSE CAP: DETACH DURING LANDING/PARACHUTE SEQUENCE

AFT HEAT SHIELD

PAYLOAD CAPACITY 6000KG/114.5TJ. MASS OF VEHICLE (TARE) 720N.

LOX VENT

AFT SKIRT

FUEL TANK

LASER ENERGY RECEIVERS BOTTOM OF THRUST STRUCTURE

SECONDARY THRUSTERS PRIMARY THRUSTER

3000 NOM.

ABLATIVE LASER PROPULSION CONCEPT

5200 EXT.

ELECTRICAL INSULATOR OUTPUT WINDOW SUPER-CONDUCTING MAGNET

LASER-ELECTRON GUN

GYROTRON: HIGH POWERED LINEAR BEAM VACUUM TUBE. GENERATION OF ELECTROMAGNETIC WAVES

2 X LASER ARRAYS: 200 X A.L.P. UNITS TOTAL

STRUCTURAL SHELL

FIRST DEVELOPEDIN 1972, ABLATIVE LASER PROPULSION (A.L.P.) TECHNOLOGY HAS RECENTLY BECOME THE MOST COST-EFFECTIVE ORBITAL LAUNCH METHOD AVAILABLE WORLDWIDE, OUTPERFORMING BOTH MICROWAVE AND ELECTROMAGNETIC RAIL METHODS. COMBINED WITH CONVENTIONAL LAUNCH SYSTEMS (SOLID FUEL PROPULSION), A.L.P. ALLOWS FOR THE DRAMATIC REDUCTION IN UNIT SIZE AND COST OF THE NUCLEAR LAUNCH VEHICLE (ESTIMATED COST = $550/KG COMPARED TO $10,000-15,000/KG FOR CONVENTION LAUNCH METHOD). TIME FROM LAUNCH TO ORBIT IS APPROX. 8 MINUTES.

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4.0 DRILLING OPERATION MARS DRILL SI`TE

SUBTERRANEAN NUCLEAR STOARGE FACILITY

TELECOMMUNICATIONS TOWERS

SOLAR P.V. ARRAY 2

BIOMASS PRODUCTION UNITS

DRILL STRUCTURE/ MAIN BASE

SOLAR P.V. ARRAY 1

WIND TURBINE ARRAY

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SOLAR RADATION RISK

BASE CONSTRUCTION

THE PRIMARY RISK TO HUMAN HEALTH ON MARS IS INCREASED RISK OF FATAL CANCER DUE TO PROLONGED EXPOSURE TO HIGH LEVELS OF SOLAR ULTRAVIOLET RADIATION. HUMAN CREW ARE EXPOSED TO 2 X TYPES OF RADIATION ON MARS:

THE PROPOSED BASE HAS BEEN DESIGNED TO MITIGATE BOTH THE RADIATION AND WIND/DUST RISK FACTORS. THE THOLUS.CORE 1 BASE COMPLEX IS A SERIES OF AERODYNAMIC DOME STRUCTURES CONSTRUCTED PRIMARILY FROM BASALT, A HIGHLY RADIATION-RESISTANT MATERIAL..

1.

2.

BASALT IS ABUNDANT IN THE THOLUS REGION, AND IS COMPRISED OF PLAGIOCLASE, PYROXENE AND OLIVINE. ASIDE FROM RADIATION-INSULATION, BASALT IS CORROSION RESISTANT AND FIRE-

ACUTE (SHORT-TERM, HIGH-DOSE) SOLAR ENERGETIC PARTICLES (SEP) VIA SOLAR FLARES AND CORONAL MASS EJECTIONS. CHRONIC (LONG-TERM, LOW-DOSE) GALACTIC COSMIS RAYS (GCRS).

ESTIMATED EXPOSURE IS 0.67MSV/DAY ON MARS SURFACE (LOW IN COMPARISON WITH 1.8MSV/DAY EXPOSURE FOR 7 MONTHS IN TRANSIT BETWEEN EARTH AND MARS: EXTREMELY HIGH COMPARED TO 0.2MSV/YEAR ON EARTH.)

RESISTANT. BASALT IS ALSO HYDROPHOBIC, OLEOPHILIC, NON-COMBUSTIBLE, NON-TOXIC AND PERFORMS WELL IF SUBJECTED TO EXPLOSION. BASALT IS ISOTROPIC AND OUTPERFORMS STEEL BY A RATIO OF 9.6:1 (STEEL IS CONSIDERED THE NEXT BEST ALTERNATIVE, BUT IS INFEASIBLE IN THE MARS CONTEXT DUE TO RESOURCE CONSTRAINTS).

EXPOSURE OVER THE COURSE OF MIN. MISSION DURATION FOR INDIVIDUAL CREW MEMBERS (TRAVEL AND 500-DAY SURFACE VISIT: 700 DAYS) INCREASES THE RISK OF FATAL CANCER BY 5%. THIS IS WITHIN ACCEPTABLE RISK LIMIT FOR DEEP SPACE EXPLORATION, BUT WILL BE EXCEEDED ON THE LONG-TERM/PERMANENT MISSION DURATIONS PROPOSED FOR THOLUS.CORE 1.

CIRT PROPOSES THE IMPLEMENTATION OF AN ICE-BERG TYPE BASE TO MITIGATE EXPOSURE OF HUMAN CREW TO HARMFUL SOLAR RADIATION. CIRT ANTICIPATES THAT LOCATING THE INFLATABLE HABITAT AND LABORATORY UNITS ON THE LOWER LEVELS OF THE BASE (BENEATH THE SURFACE L.S.S. AND DRILLING INFRASTRUCTURE, AND SEVERAL LAYERS OF D.M.L.S.BASALT STRUCTURE) WILL SIGNIFICANTLY REDUCE THE CUMULATIVE EXPOSURE OF HUMAN CREW TO SOLAR RADIATION OVER THE DURATION OF THE MISSION.

THE FOLLOWING PROCESS IS RECOMMENDED FOR OBTAINING AND REFINING BASALT IN THE THOLUS REGION: 1.

2.

REGOLITH IS STRIPPED TO REVEAL SURFACE BASALT DEPOSIT. THE BASALT IS HARVESTED BY THE CMM (CONTINUOUS MINING MACHINE), DELIVERED

TO THE BASE AND CRUSHED (JAW CRUSHER).

3.

4.

THE CRUSHED BASALT IS THEN MELTED TO 1400°C AND PROCESSED INTO POWDER FOR “PRINTING”, OR EXTRUDED INTO FIBRE UNDER HYDROSTATIC PRESSURE. RAPID PROTOTYPING MACHINES DEPOSIT THE POWDERED BASALT IN LAYERS BY

DIRECT METAL LASER SINTERING (D.M.L.S.) TO FORM THE BASE STRUCTURES.

HIGH WIND/DUST STORM RISK

SUBTERRANEAN VITAMIN D + PHOTOSYNTHESIS

MARS’ SURFACE IS SUBJECT TO HIGH WINDS AND PROLONGED DUST STORM EVENTS (MAXIMUM OBSERVED DURATION IS 27 DAYS), OBSCURING LIGHT TO THE SURFACE AND THEREFORE POSING A RISK TO ENERGY HARVESTING AND EXPLORATION/RECONNAISSANCE ACTIVITIES.

THE LACK OF NATURAL LIGHT (HOWEVER HARMFUL) IS AN OBVIOUS OBSTACLE TO ESTABLISHING A BASE PARTIALLY BURIED BENEATH THE SURFACE. THEREFORE, CIRT PROPOSES THE IMPLEMENTATION OF SOLAR HARVESTING VIA REMOTE SKYLIGHT (HELIOTUBE) TECHNOLOGY.

THE DUST STORM SEASON TYPICALLY LASTS FROM SOL 370 TO 699, DURING THE SOUTHERN

HELIOTUBES DELIVER A RADIATION-FREE SOURCE OF LIGHT TO THE SUBTERRANEAN CHAMBERS

HEMISPHERE SPRING/SUMMER. STORM EVENTS ARE THOUGHT TO BE INITIATED BY SOLAR HEATING AND STRONG WINDS, AND DUST REMAINS SUSPENDED IN THE ATMOSPHERE FOR PROLONGED DURATIONS DUE TO LOW ATMOSPHERIC PRESSURE/DENSITY. LARGE STORM EVENTS MAY ENVELOPE

OF THE THOLUS.CORE 1 BASE VIA FIBRE OPTIC CONDUIT, PROVIDING ADEQUATE LIGHT FOR VITAMIN D ABSORPTION (FOR THE HUMAN CREW) AND PHOTOSYNTHESIS (AN OPPORTUNITY FOR SUBTERRANEAN ORNAMENTAL PLANT CULTIVATION).

ENTIRE PLANET.

84,600 DIA. 15,800 MAX. HT.

EXPOSURE TO EXTERIOR CONDITIONS (RADIATION, EXTREME TEMP. + WIND HAZARD: 4% MISSION DURATION SKYLIGHT: U.V. FILTRATION -4023m M.H.D. STRUCTURAL SHELL (D.M.L.S. BASALT): RADIATION EXPOSURE LOW-TO-MODERATE

DRILLING OPERATION, I.S.R.U. PROCESSING + PRIMARY MANUFACUTRING (PREDOMINANTLY AUTOMATED TO MINIMISE RISK TO HUMAN CREW).: 12% MISSION DURATION

HELIO TUBE/RADIATION FILTER: FIBRE OPTIC CONDUIT DELIVERS SUFFICIENT LIGHT TO BASE INTERIOR FOR VITAMIN D ABSORPTION/PHOTOSYNTHESIS

VAULTED ARCHES SUPPORTING FLOOR PLATES (D.M.L.S. BASALT) PLANNING + LABORATORY HABS, SECONDARY MANUFACTURING: 45% MISSION DURATION -4043m M.H.D.

RECREATION, SLEEPING + HYGIENE HABS: 39% MISSION DURATION

-4059m M.H.D.

WASTE TREATMENT PLANT -4078m M.H.D.

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THERMAL DRILLING CONCEPT

SUPERINSULATED ELECTRICITY + DRILL FLUID SUPPLY CABLES

DUE TO THE RELATIVELY LOW GRAVITY, DRILLING EFFORT ON THE MARS SURFACE IS 2.6 X THE EQUIVALENT OPERATION ON EARTH. THEREFORE, CONVENTIONAL MECHANICAL DRILLING TECHNIQUES (ELECTRICAL, PNUEMATIC, ROTARY AND PERCUSSION) ARE DEEMED UNSUITABLE FOR DEPLOYMENT ON MARS. HOWEVER, THERMAL OR CHEMICAL DRILLING TECHNIQUES DO NOT RELY ON AXIAL FORCE TO DRILL THROUGH SUBSTRATE MATERIAL, AND SO ARE FAR MORE EFFECTIVE IN LOW-GRAVITY ENVIRONMENTS.

STRUCTURAL SHELL

THERMAL DRILLING IS MORE SUITED TO EXTREME DEPTHS (>300KM), AS THE METHOD DOES NOT DEPEND ON FLUIDS REACHING THE DRILL HEAD DURING OPERATION (NOT POSSIBLE AT THE HIGH TEMPERATURE AND PRESSURE ENCOUNTERED AT EXTREME DEPTH). THEREFORE, CIRT RECOMMENDS THERMAL DRILLING FOR THE THOLUS.CORE_1 OPERATION.

THERMAL DRILLING MAY BE ACHIEVED THROUGH EITHER SPALLING OR VAPORISATION. THERMAL DRILLING (SPALLING) INVOLVES DISPLACEMENT OF SUBSTRATE AND OCCURS AT MUCH LOWER TEMPERATURES (400-600C). THERMAL DRILLING (VAPORISATION) INVOLVES SUPERHEATING SURROUNDING ROCK/SUBSTRATE MATERIAL (1100-2900C), CAUSING THE ROCK TO MELT (GLASSIFY), BECOME MALEABLE AND REDUCE IN VOLUME, CREATING A PATH FOR THE DRILL HEAD TO MOVE DOWN THROUGH. VAPORISATION IS THE PREFERRED TECHNIQUE FOR THIS APPLICATION. GLASS-FORMING SECTION

HIGH-GRADE TUNGSTEN IS RECOMMENDED AS THE PRIMARY MATERIAL FOR THE DRILL HEAD, AS THE MELTING POINT (3414C) FAR EXCEEDS THE ESTIMATE TEMPERATURE AT MANTLE EDGE (CORE TEMPERATURE EST. 2760C).

KERF MELTER

IT IS ANTICIPATED THAT LIQUID GROUND WATER (SALINE) WILL BE ENCOUNTERED AT DEPTH, DUE TO THE INCREASED PRESSURE AND THE POTENTIAL FOR AQUIFER TO BE ISOLATED FROM THE SURFACE BY IMPERMEABLE ROCK FORMATIONS.

THERMAL PENETRATOR

8000 NOM.

DRILLING INFRASTRUCTURE

DRILL FLUID PUMPS

ELECTRICITY TRANSFORMERS

CABLE ROLL PRIMARY + RESERVE KELLY ROTARY MOTORS CALF WHEEL KELLY

SUPERINSULATED ELECTRICITY + DRILL FLUID SUPPLY CABLE

DRILL FLUID RESERVOIR

CABLE ROLL ROTARY MOTOR

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4.0 MISSION INFRASTRUCTURE IN-SITU RESOURCE UTILISATION (I.S.R.U.)

ELECTROLYSIS BY-PRODUCT: HYDROGEN FUEL FOR E.R.V. (EARTH RETURN VEHICLE) AND TERRAIN VEHICULAR ACTIVITY

PRIMARY OXYGEN PRODUCTION UNITS: ELECTROLYSIS/SABATIER REACTOR

SECONDARY OXYGEN PRODUCTION UNIT: SOIL PROCESSOR. SUPERHEAT REGOLITH TO 2500°C IN VACUUM TO RELEASE OXYGEN/WATER/ETC. 20% SAMPLE VOLUME CONVERTED.

“SAND” WASHING MACHINE: DE-CONTAMINATION OF RAW MATERIAL.

BASALT EXTRUSTION/FIBRE PRODUCTION UNIT: FURNACE + BUSHING. MELTING POINT 1400-1600°C. BUSHING DIAMETER 12 MICRONS. HORIZONTAL SHAFT IMPACT CRUSHER: SECONDARY CRUSHING (BASALT).

CIRCULAR VIBRATING SCREEN: SECONDARY PARTICLE SIZE DISTRIBUTION (BASALT)

EXTERNAL DELIVERY UNIT: BASALT + SOIL. JAW CRUSHER. PRIMARY CRUSHING OF RAW MATERIAL. COARSE SCREEN. PRIMARY PARTICLE SIZE DISTRIBUTION.

RAPID MANUFACTURING INFRASTRUCTURE

FUSED DEPOSITION MODELLING (FDM) MACHINE:

FIXED RAPID PROTOTYPE ARM. (ROVER MOUNTED-RAPID PROTOTYPE ARM: BASE MAINENANCE WORKS)

RAIL-MOUNTED DIRECT METAL LASER SINTERING (DMLS) ARM.

3D SCANNER-REPLICATORS

ELECTRON BEAM MELTING (EBM) MACHINE: MANUFACUTRING OF EXTREMELY DETAILED COMPONENTS

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INFLATABLE HABITAT

PLANNING, LABORATORY, RECREATION + SLEEPING/HYGIENE MODULES IMPORTED FROM EARTH (STERILE).

TESTS HAVE DETECTED SUPEROXIDES IN THE MARS SOIL. SUPEROXIDES ARE COMPOUNDS THAT WILL RELEASE ADDITIONAL OXYGEN ON CONTACT WITH WATER, AUGMENTING OXYGEN PRODUCTION ALREADY UNDERTAKEN

BY PLANT MATTER WITHIN THE BPC SYSTEM. 1 X SUPEROXIDE MOLECULE (PERCHLORATE ClO4: 1% SOIL CONTENT) BREAKS DOWN ORGANIC MOLECULES IF EXPOSED TO SOLAR ULTRAVIOLET RADIATION. PERCHLORATE IS THEREFORE A POTENTIAL ENERGY SOURCE FOR AN IMPORTED MICROBIAL COLONY, BUT ALSO RESULTS IN POSSIBLE TISSUE DAMAGE TO HUMAN CREW (THYROID DEGRADATION). THEREFORE, CIRT PROPOSES THE IMPLEMENTATION OF THE “SUIT-DOCK” SYSTEM, EFFECTIVELY ELMINATING THE EXPOSURE OF HUMANS TO MARS SOIL/SUPEROXIDES (SEE INFLATABLE HABITAT).

PERCHLORATE (IN THE FORM OF AMMONIUM PERCHLORATE) IS ALSO A SOURCE OF ENERGY AS SOLID ROCKET FUEL. CIRT PROPOSES THE INVESTIGATION OF PERCHLORATE EXTRACTION FROM THE MARS SOIL.

SUIT-DOCK SYSTEM: DIRECT REAR ACCESS TO STERILE INTERIOR. MITIGATE CONTACT WITH SOIL PERCHLORATES.

EXTRA-HABITAT ACTIVITY (EH.A.) SUIT

SUIT-DOCK SYSTEM: DIRECT REAR ACCESS TO STERILE INTERIOR. MITIGATE CONTACT WITH SOIL PERCHLORATES.

HIGH PERFORMANCE POLYCARBONATE HELMET

BATTERY PACK: GRAPHENE SUPERCAPACITOR RIGID FIBREGLASS TORSO: INTEGRATED ELECTROLUMINESCENT WIRE. NYLON TRICOT/SPANDEX (INNER LAYER).

URETHANE-COATED NYLON (PRESSURISATION LAYER).

DACRON, NEOPRENE, ALUMINIZED MYLAR, GORTEX, KEVLAR, AND NOMEX (PRESSURE-RETENTION LAYER).

LITHIUM HYDROXIDE CO2 + VAPOUR FILTER

AV. HUMAN RESOURCE CONSUMPTION: ENERGY 9000KJ/DAY. WATER 3L/DAY. OXYGEN 550L/DAY (AIR 11000L/DAY).

TOTAL SUIT MASS: 4.7N (EQ. 17.9KG MARS SURFACE ENVIRONMENT)

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BIOMASS PRODUCTION CHAMBER

BIOMASS PRODUCTION CHAMBER (B.P.C.): HYPOBARIC GLAZED DOME. MIN. 20KPA FOR FIRE SAFETY (MIN. 10KPA REQUIRED FOR PLANT CULTIVATION).

PRESSURE SUIT REQUIRED.

SEVERAL BIOMASS PRODUCTION CHAMBERS WILL PROVIDE THE NUTRIENT REQUIREMENTS OF THE HUMAN CREW MEMBERS AND SERVE AS SUPPLEMENTARY OXYGEN PRODUCTION, WATER PURIFICATION AND ORGANIC WASTE TREATMENT SYSTEM. SPECIES RECOMMENDED FOR EXTRATERRESTRIAL CULTIVATION INCLUDE DWARF WHEAT, POTATO, KUMARA, BEAN, LETTUCE, TOMATO, RED BEET, SPINACH, RADISH, STRAWBERRY, SOYBEAN, PEANUT. ORNAMENTAL PLANTS ALSO RECOMMENDED TO MAINTAIN CREW MORALE. STOCK PLANTS TRANSPORTED TO MARS WITH ROOTS ENCASED IN BIOFOAM (BIODEGRADABLE CONDUIT FOR NUTRIENTS AND WATER) AND LIGHT SUPPLIED BY MONOCHROMATIC LEDS (2 X WAVELENGTH: OPTIMAL PHOTOSYNTHESIS/ELECTRICITY CONSUMPTION).

AGRICULTURAL LOADING IS ESTIMATED TO BE EQUIVALENT TO 200M2 (CONSUMING 100W/DAY) PER CREW MEMBER (F.O.S. 2.0).

ACCORDING TO DATA GATHERED BY RECONNAISSANCE GEOLOGISTS, MARS SOIL HAS AN AVERAGE PH OF 7.7 (SLIGHTLY ALKALINE) AND DEFICIENCIES IN CARBON AND NITROGEN. POTASSIUM AND PHOSPHORUS EXIST IN ABUNDANCE. THEREFORE, CIRT RECOMMENDS IRRIGATION WITH AERATED WATER (WITH INCREASED CO2 CONTENT: CARBONIC ACID) TO DECREASE THE PH AND INCREASE CARBON LEVELS. NITROGEN FERTILISER (AMMONIUM NITRATE) IS SUFFICIENT TO TREAT NITROGEN DEFFICIENCY.

HYDROPONIC CELL FERTILISED SOIL CELL

WASTE TREATMENT INFRASTRUCTURE

BIOLOGICAL COMBUSTION UNITS: FERMENTATION OF ORGANIC MATERIAL AT 80-100째C + 20KPA

SODIUM LEECHING VATS: ALGAL COLONY

ACTIVATED CARBON FILTRATION SYSTEM

OZONE GENERATOR

SODIUM LEECHING SYSTEM REQUIRED TO MITIGATE POSITIVE NUTRIENT FEEDBACK LOOP DUE TO HUMAN EXCRETA CONTAINING INCREASED SODIUM RELATIVE TO POTASSIUM. THE SYSTEM REMOVES EXCESS SODIUM (REPLACEMENT WITH POTASSIUM) VIA IMPORTED MARINE ALGAE COLONY (EXTREMOPHILES). THE ALGAE EXIST ON A DIET OF MANUFACTURED BRINE.

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RENEWABLE ENERGY HARVESTING

TURBINE BLADES

10 X 5 SOLAR ARRAY: 7500M2 P.V. SURFACE AREA

UPRIGHT STANCHION

ELECTRICAL LOADING FOR THE MAXIMUM ANTICIPATED CREW/OPERATIONAL CONFIGURATION IS APPROXIMATE 400KWE. SOLAR LIGHT INTENSITY ON THE MARS SURFACE IN THE EQUATORIAL ZONE IS APPROXIMATELY 43% OF THE INTENSITY ON EARTH (590W/M2). HOWEVER, RECENT ADVANCES IN PHOTOVOLTAIC TECHNOLOGY (MULTI-JUNCTION CELLS CONTAINING GALLIUM ARSENIDE AND SILICON, WITH CARBON NANOTUBE SURFACE TREATMENT TO INCREASE SURFACE AREA/DECREASE REFLECTANCE) RESULT IN A SOLAR P.V. AREA OF 15,000M2. CIRT RECOMMENDS THE P.V. UNITS ARE INSTALLED IN 2 X SEPARATE ARRAYS, AS A PRECAUTION AGAINST FAULT OF ACCIDENT. TO ALLOW FOR UNFORESEEN EXPANSION IN OPERATIONS OR FAILURE IN SOLAR P.V. SYSTEM TO DELIVER REQUIRED BASE LOAD POWER, A WIND TURBINE ARRAY (18 X 10KW VERTICAL TURBINES) IS RECOMMENDED. THE TURBINE ARRAY IS ABLE TO PROVIDE BASE LOAD IN CASE OF EXTENDED DUST STORM EVENTS AND EXPLOITS THE RELATIVELY HIGH WIND SPEEDS OBSERVED ON THE MARS SURFACE. AS AN ADDITIONAL SAFETY MEASURE, CIRT RECOMMENDS THE BASE BE FITTED WITH A RADIOISOTOPE THERMOELECTRIC GENERATOR (RTG) IN CASE OF CATASTROPHIC FAILURE OF RENEWABLE ENERGY SYSTEMS.

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GEARBOX + GENERATOR

7200

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5.0 CLOSING REMARKS

THE THOLUS.CORE 1 PROPOSAL REACHES THE LIMITS OF CURRENT SPACE EXPLORATION TECHNOLOGY AND EXCEEDS THE CURRENT FINANCIAL COMMITMENT TO SUCH PROGRAMS. HOWEVER, CIRT BELIEVES THIS STUDY DEMONSTRATES THAT THE CREATION OF A SECOND HABITABLE PLANET WITHIN OUR SOLAR SYSTEM IS FEASIBLE AS A LONG-TERM GOAL. THE QUESTION IS NOT NOW ONE OF MISSION ARCHITECTURE, BUT VISION.

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REFERENCES

KEY SOURCES

HTTP://WWW.NASA.GOV/ HTTP://WWW.MARSSOCIETY.ORG/

HTTP://WWW.THESPACEREVIEW.COM/

“TERRAFORMING: ENGINEERING PLANETARY ENVIRONMENTS” BY MARTYN J. FOGG EXPLORATION HTTP://WWW.ASTRONOMYCAST.COM/2007/09/EPISODE-52-MARS/

HTTP://CARS9.UCHICAGO.EDU/GSECARS/LVP/PUBLICATION/NEWS/X-RAYS%20REVEAL%20SECRETS%20OF%20MARS’%20CORE.HTM CORE HTTP://CARS9.UCHICAGO.EDU/GSECARS/LVP/PUBLICATION/NEWS/X-RAYS%20REVEAL%20SECRETS%20OF%20MARS’%20CORE.HTM

HTTP://WWW.SPACE.COM/3874-MARS-GOOEY-CORE-FREEZING.HTML HTTP://SPACECOLONIZATION.WIKIA.COM/WIKI/TERRAFORMING_OF_MARS HTTP://WWW.THESPACEREVIEW.COM/ARTICLE/65/1 MAGNETOSPHERE HTTP://WWW.SPACE.COM/3632-MARS-CAVES-TARGETS-SEARCH-LIFE.HTML

HTTP://WWW.EVOLO.US/COMPETITION/RHIZOME-TOWER-A-THOUSAND-UNDERGROUND-PLATEAUS/

NUCLEAR

HTTP://WWW.NASA.GOV/MISSION_PAGES/THEMIS/MAIN/#.U_5QHVMSYSO HTTP://CSELIGMAN.COM/TEXT/PLANETS/MAGNETISM.HTM HTTP://EXPERTS.FOREIGNPOLICY.COM/POSTS/2009/04/13/WHERE_NUCLEAR_WEAPONS_GO_TO_DIE HTTP://WWW.WASHINGTONPOST.COM/WORLD/NATIONAL-SECURITY/THE-EXPLOSIVE-COST-OF-DISPOSING-OF-NUCLEAR-WEAPONS/2013/07/03/64F896E0-E287-11E2-80EB-3145E2994A55_STORY.HTML HTTP://FAS.ORG/ISSUES/NUCLEAR-WEAPONS/STATUS-WORLD-NUCLEAR-FORCES/

HTTP://RT.COM/NEWS/ISRAEL-NUCLEAR-WEAPONS-MASS-DESTRUCTION-899/ HTTP://WWW.FISSILEMATERIALS.ORG/

HTTP://EXPERTS.FOREIGNPOLICY.COM/POSTS/2009/04/13/WHERE_NUCLEAR_WEAPONS_GO_TO_DIE

HTTP://WWW.WASHINGTONPOST.COM/WORLD/NATIONAL-SECURITY/THE-EXPLOSIVE-COST-OF-DISPOSING-OF-NUCLEAR-WEAPONS/2013/07/03/64F896E0-E287-11E2-80EB-3145E2994A55_STORY.HTML MARS COLONY HTTP://WWW.THESPACEREVIEW.COM/ARTICLE/437/2’

HTTP://WWW.SPACEDAILY.COM/NEWS/LASER-97B.HTML

TRAJECTORY

HTTP://WWW.SPACE.COM/26705-NASA-2020-ROVER-MARS-COLONY-TECH.HTML HTTP://WWW.MARSJOURNAL.ORG/CONTENTS/2007/0002/FILES/WOOSTER_MARS_2007_0002.PDF HTTP://WWW.PHY6.ORG/STARGAZE/SMARS3.HTM

HYDROGEN FUEL

HTTP://WWW.UNIVERSETODAY.COM/14841/HOW-LONG-DOES-IT-TAKE-TO-GET-TO-MARS/ HTTP://WWW.GLOBAL-HYDROGEN-BUS-PLATFORM.COM/TECHNOLOGY/HYDROGENPRODUCTION/ELECTROLYSIS

HTTP://WWW.NASA.GOV/TOPICS/TECHNOLOGY/HYDROGEN/HYDROGEN_FUEL_OF_CHOICE.HTML HTTP://WWW.NSS.ORG/SETTLEMENT/NASA/SPACERESVOL4/HUMAN.HTML

HTTP://WWW.NEWMARS.COM/FORUMS/VIEWTOPIC.PHP?ID=6238 LASER LAUNCH

HTTP://WWW.THESPACEREVIEW.COM/ARTICLE/437/2’ HTTP://WWW.SPACEDAILY.COM/NEWS/LASER-97B.HTML HTTP://WWW.SPACE.COM/7067-LASER-PROPULSION-WILD-IDEA-FINALLY-SHINE.HTML

HTTP://WWW.DARKGOVERNMENT.COM/LASERCRAFT.HTML

HTTP://WWW.ASTROBIO.NET/NEWS-EXCLUSIVE/BEAMING-ROCKETS-INTO-SPACE/

CAVES

HTTP://WWW.WIRED.CO.UK/NEWS/ARCHIVE/2012-05/08/MARS-AUSTRIAN-ICE-CAVES HTTP://WWW.GUTENBERG.ORG/FILES/32360/32360-H/32360-H.HTM

HTTP://WWW.SPACE.COM/3891-DEEP-HOLE-MARS.HTML

HTTP://WWW.WIRED.COM/2014/07/NEW-GEOLOGIC-MAP-MARS-USGS/ HYDROPONICS HTTP://WWW.HYDROPONICS.COM.AU/ISSUE-58-THE-NEXT-STEP-MARS-OR-BUST/ HTTP://WWW.NASA.GOV/CENTERS/MARSHALL/NEWS/BACKGROUND/FACTS/BPS.HTML MARS CLIMATE HTTP://WWW.MSSS.COM/HTTP/PS/SEASONS/SEASONS.HTML

TOXIC DUST SPACE SUITS

HTTP://WWW-MARS.LMD.JUSSIEU.FR/MARS/TIME/SOLAR_LONGITUDE.HTML HTTP://WWW.ASTRONOMYCAST.COM/2008/06/EP-91-THE-SEARCH-FOR-WATER-ON-MARS/ HTTP://WWW.SPACE.COM/21554-MARS-TOXIC-PERCHLORATE-CHEMICALS.HTML HTTP://WWW.GIZMAG.COM/Z-1-PROTOTYPE-SPACESUIT/23408/ HTTP://WWW.WIRED.COM/2014/04/RADIATION-RISK-ISS-MARS/

ROVERS

SOLAR RADIATION

3D PRINTING

HTTP://MARS.JPL.NASA.GOV/PROGRAMMISSIONS/MISSIONS HTTP://WWW.SPACE.COM/24731-MARS-RADIATION-CURIOSITY-ROVER.HTML HTTP://WWW.SCI-NEWS.COM/SPACE/SCIENCE-MARS-RADIATION-MEASUREMENTS-SURFACE-01629.HTML HTTP://WWW.SPACE.COM/21353-SPACE-RADIATION-MARS-MISSION-THREAT.HTML HTTP://WWW.SPACE.COM/23059-3D-PRINTING-MARS-COLONY.HTML

SELF-DEPLOYING HAB.

SPACE ARCH.

HTTP://WWW.CSIRO.AU/ORGANISATION-STRUCTURE/FLAGSHIPS/FUTURE-MANUFACTURING-FLAGSHIP/TI-TECHNOLOGIES/ARCAM.ASPX HTTP://WWW.EXTREMETECH.COM/EXTREME/143552-3D-PRINTING-WITH-METAL-THE-FINAL-FRONTIER-OF-ADDITIVE-MANUFACTURING HTTP://WWW.DEZEEN.COM/2012/08/22/STONE-SPRAY-ROBOT-BY-ANNA-KULIK-INDER-SHERGILL-AND-PETR-NOVIKOV/ HTTP://WWW.HPEE.ORG/ HTTP://WWW.ACADEMIA.EDU/3356911/LIVING_BEYOND_EARTH_THE_ARCHITECTURAL_FEATURES_OF_HUMAN_HABITATS_IN_EXTREME_ENVIRONMENTS_OF_SPACE_AND_OTHER_PLANETARY_SURFACES HTTP://SPACEARCHITECT.ORG/PORTFOLIOS/MEDUSA-FROM-SUBSEA-TO-THE-MOON/

BASALT

HTTPS://WWW.YOUTUBE.COM/WATCH?V=N18HCPFKV1E

FUTURE NOW / PLANETARY REBIRTH. JIL RALEIGH.