#1#2WHY GO ANYWHERE?#371 7#4WHY MARS?#5.... Credit: Roberto Ziche, NASA, planetpixelemporium.com, planetscapes.com#6Sun Mercury Venus Earth Mars Jupiter Saturn Uranus Neptune Pluto Eris#7DIAMETER AVERAGE DISTANCE FROM SUN TEMPERATURE RANGE ATMOSPHERIC COMPOSITION FORCE OF GRAVITY (WEIGHT) DAY LENGTH LAND MASS PEOPLE EARTH 12,756 km / 7,926 mi 150,000,000 km / 93,000,000 mi -88C TO 58C / -126F TO 138F 78% N₂, 21% 0₂, 1% OTHER 2" 100 LBS ON EARTH 24 hrs 148.9 MILLION km² 7 BILLION MARS 6,792 km / 4,220 mi 229,000,000 km / 142,000,000 mi -140C TO 30C / -285F TO 88F 96% CO₂, <2% Ar,<2% N₂, <1% Other 38 lbs ON MARS (62.5% LESS GRAVITY) 24 hrs 40 min 144.8 MILLION km² (97% OF EARTH) 0#8FROM EARLY EXPLORATION TO A SELF-SUSTAINING CITY ON MARS#9WANT TO GO NOW CAN AFFORD TO GO COST OF TRIP TO MARS INFINITE MONEY#10USING TRADITIONAL METHODS WANT TO GO CAN AFFORD TO GO COST OF TRIP TO MARS $10 BILLION / PERSON#11WHAT'S NEEDED WANT TO GO CAN AFFORD TO GO COST OF TRIP TO MARS MEDIAN COST OF A HOUSE IN THE UNITED STATES#12IMPROVING COST PER TON TO MARS BY FIVE MILLION PERCENT#13FULL REUSABILITY REFILLING IN ORBIT PROPELLANT PRODUCTION ON MARS RIGHT PROPELLANT#14FULL REUSABILITY#15To make Mars trips possible on a large-enough scale to create a self-sustaining city, full reusability is essential#16Boeing 737 Price Passenger Capability Cost/Person - Single Use Cost/Person - Reusable Cost of Fuel / Person $90M 180 people $500,000 $43 (LA to Las Vegas) $10#17REFILLING IN ORBIT#18Not refilling in orbit would require a 3-stage vehicle at 5-10x the size and cost Spreading the required lift capacity across multiple launches substantially reduces development costs and compresses schedule Combined with reusability, refilling makes performance shortfalls an incremental rather than exponential cost increase#19PROPELLANT ON MARS#20Allows reusability of the ship and enables people to return to Earth easily Leverages resources readily available on Mars Bringing return propellant requires approximately 5 times as much mass departing Earth#21RIGHT PROPELLANT#22VEHICLE SIZE COST OF PROP REUSABILITY MARS PROPELLANT PRODUCTION PROPELLANT TRANSFER ● GOOD OK BAD X VERY BAD C₁₂2H₂2/0₂ 22.4 KEROSENE 12 X H₂/0₂ HYDROGEN/OXYGEN CH₁/0₂ DEEP-CRYO METHALOX#23FULL REUSABILITY REFILLING IN ORBIT PROPELLANT PRODUCTION ON MARS RIGHT PROPELLANT#24SYSTEM ARCHITECTURE SERIES OF TANKERS TO REFILL SHIP EARTH SHIP PREPARES TO LAUNCH 3 TAD TANKERS REFILL SHIP THEN RETURN TO EARTH BOOSTER RETURNS TO LAUNCH AGAIN ww 4 SHIP HEADS TO MARS 7 SHIP RETURNS TO EARTH TARGETED REUSE PER VEHICLE 1,000 uses per booster 100 per tanker 12 uses per ship 5 MARS ARRIVAL MARS 6 IN SITU PROPELLANT PRODUCTION 0000#25VEHICLE DESIGN AND PERFORMANCE#26Carbon-fiber primary structure Densified CH4/02 propellant Autogenous pressurization 650#27VEHICLES BY PERFORMANCE VEHICLE NAME PAYLOAD TO LEO (KG) INDIA GSLV 5,000 ANTARES 7,000 SOYUZ 2-1B 8,200 CHINA LM7 13,500 ATLAS V 551 18,850 JAPAN H-IIB 19,000 ARIANE 5 20,000 PROTON M/ BREEZE M 22,000 FALCON 9 22,800 DELTA IV HEAVY 28,300 FALCON HEAVY 54,400 I SATURN V 135,000 MARS VEHICLE 550,000#28VEHICLES BY PERFORMANCE VEHICLE NAME PAYLOAD TO LEO (KG) INDIA GSLV 5,000 ANTARES 7,000 SOYUZ 2-1B 8,200 CHINA LM7 13,500 ATLAS V 551 18,850 JAPAN H-IIB 19,000 ARIANE 5 20,000 PROTON M/ BREEZE M 22,000 FALCON 9 22,800 U DELTA IV HEAVY 28,300 FALCON HEAVY 54,400 SATURN V 135,000 MARS VEHICLE 550,000#29GROSS LIFT-OFF MASS (t) LIFT-OFF THRUST (MN) LIFT-OFF THRUST (t) VEHICLE HEIGHT (m) TANK DIAMETER (m) EXPENDABLE LEO PAYLOAD (t) FULLY REUSABLE LEO PAYLOAD (t) MARS VEHICLE 10,500 128 13,033 122 12 550 300 SATURN V 3,039 35 3,579 111 10 135 RATIO 3.5 3.6 3.6 1.1 1.2 4.1 I HUMAN W USA#30RAPTOR ENGINE#31Cycle Oxidizer Fuel Chamber Pressure Throttle Capability Sea-Level Nozzle Full-flow staged combustion Subcooled liquid oxygen Subcooled liquid methane 300 bar 20% to 100% thrust Expansion Ratio: 40 Thrust (SL): 3,050 kN Isp (SL): 334 s Vacuum Nozzle Expansion Ratio: 200 Thrust: 3,500 kN Isp: 382 s#32ROCKET BOOSTER#33Length Diameter Dry Mass Propellant Mass Raptor Engines Sea Level Thrust Vacuum Thrust 77.5 m 12 m 275 t 6,700 t 42 128 MN 138 MN Booster accelerates ship to staging velocity, traveling 8,650 km/h (5,375 mph) at separation Booster returns to landing site, using 7% of total booster prop load for boostback burn and landing Grid fins guide rocket back through atmosphere to precision landing#34Engine configuration Outer ring: 21 Inner ring: 14 Center cluster: 7 Outer engines fixed in place Only center cluster gimbals#35INTERPLANETARY SPACESHIP#360 0 CO Length Max Diameter Raptor Engines Vacuum Thrust Propellant Mass Dry Mass Cargo/Prop to LEO Cargo to Mars 49.5 m 17 m 3 Sea-Level - 361s Isp 6 Vacuum - 382s Isp 31 MN Ship: 1,950 t Tanker: 2,500 t Ship: 150 t Tanker: 90 t Ship: 300 t Tanker: 380 t 450 t (with transfer on orbit) Long term goal of 100+ passengers/ship#37SHIP CAPACITY WITH FULL TANKS EARTH-MARS TRANSIT TIME (DAYS) BY MISSION OPPORTUNITY YEAR 2020 2022 2024 2027 2029 2031 2033 2035 2037 AVERAGE TRIP TIME (d) 90 120 140 150 140 110 90 80 100 115 TMI DELTA V: 6 km/s Mars Entry Velocity: 8.5 km/s DELTA-V CAPABILITY (km/s) 10 8 N 0 100 TOTAL DELTA-V CAPABILITY EARTH-MARS OUTBOUND 200 300 PAYLOAD (t) 400 RESERVED FOR MARS LANDING DELTA-V PRIOR TO MARS ENTRY 500 600#38ARRIVAL From interplanetary space, the ship enters the atmosphere, either capturing into orbit or proceeding directly to landing Aerodynamic forces provide the majority of the deceleration, then 3 center Raptor engines perform the final landing burn Using its aerodynamic lift capability and advanced heat shield materials, the ship can decelerate from entry velocities in excess of 8.5 km/s at Mars and 12.5 km/s at Earth G-forces (Earth-referenced) during entry are approximately 4-6 g's at Mars and 2-3 g's at Earth Heating is within the capabilities of the PICA-family of heat shield materials used on our Dragon spacecraft PICA 3.0 advancements for Dragon 2 enhance our ability to use the heat shield many times with minimal maintenance#39PROPELLANT PLANT#40First ship will have small propellant plant, which will be expanded over time Effectively unlimited supplies of carbon dioxide and water on Mars 5 million cubic km ice 25 trillion metric tons CO2 ISRU ATM WATER MINING CO2 COLLECTION 2H₂0 сог + 4H₂0 2H₂0 2H₂O + CO₂ ELECTROLYSIS SABATIER 20₂ + CH 4H₂2 202 CH LIQUEFACTION + STORAGE LIQUEFACTION + STORAGE#41COSTS With full reuse, our overall architecture enables significant reduction in cost to Mars BOOSTER TANKER $230M $130M $200M 1,000 100 12 6 501 $0.2M $0.5M $10M $11M $8M $43 Sum Of Costs: $62 M Cargo Delivered: 450 T Cost/ton to Mars: <$140,000 FABRICATION COST LIFETIME LAUNCHES LAUNCHES PER MARS TRIP AVERAGE MAINTENANCE COST PER USE TOTAL COST PER ONE MARS TRIP (Amortization, Propellant, Maintenance) Cost Of Propellant: $168/t Launch Site Costs: $200,000/launch Discount Rate: 5% SHIP $ per kg 550 440 385 330 220 165 110 1 2 O O Ship Lifetime Flights O 5 O 6 O 7 o O o 9 10 11 12#42FUNDING Steal Underpants Launch Satellites Send Cargo and Astronauts to ISS Kickstarter Profit#43TIMELINES Bly#442002#452006 First Flight attempt, NASA cargo transport partnership 2008 Falcon 1, 0.5 ton to Low Earth Orbit (LEO), fully expendable. First NASA cargo contract 2010 Falcon 9 v1.0, 10 tons to LEO, expendable. Dragon spacecraft to orbit and back. 2012 Dragon spacecraft delivers and returns cargo from space station 2013 Grasshopper test rig demonstrates vertical take-off and landing 2014 First orbital booster to return from space for ocean landing. Falcon 9 v1.1, 13 tons to LEO, expendable 2015 First orbital booster to return from space and land on land. Upgraded Falcon 9, 22.8 tons to LEO, expendable 2016 First droneship landing for orbital boosters#46FUTURE#47NEXT STEPS FALCON HEAVY CREW DRAGON DEVELOPMENT INTERPLANETARY TRANSPORTATION SYSTEM STRUCTURES DEVELOPMENT PROPULSION DEVELOPMENT 2016 2017 RED DRAGON MISSIONS 2018 SHIP TESTING 2019 LAUNCH WINDOW TO MARS ORBITAL TESTING BOOSTER TESTING 2020 2021 2022 MARS FLIGHTS 2023 2024 2025 2026 2027#48RED DRAGON#49Mission Objectives Learn how to transport and land large payloads on Mars Identify and characterize potential resources such as water Characterize potential landing sites, including identifying surface hazards Demonstrate key surface capabilities on Mars#50RAPTOR FIRING#51#52CARBON FIBER TANK#53#54XXXXXX#55FFT.#56B1#57BEYOND MARS#58JUPITER#59ENCELADUS#60XXX EUROPA#61SATURN