61 slides from Space Exploration Technologies's conference presentation, September 2016
Slide 1: Slide 1
Slide 2: Why Go Anywhere?
WHY GO ANYWHERE?
Slide 3: Cae exw
Cae exw i > me prea
Slide 4: Why Mars?
WHY MARS?
Slide 5: Humanity's Greatest Adventure
HUMANITY’S GREATEST ADVENTURE Credit: Roberto Ziche, NASA, planetpixelemporium.com, planetscapes.com
Slide 6: Solar system planets
°° @€ @e @;:; Sun Mercury Venus Earth = Mars Jupiter Saturn Uranus Neptune Pluto Eris
Slide 7: Earth and Mars comparison
DIAMETER 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% N,, 21% O,, 1% OTHER 100 LBS ON EARTH 24hrs 148.9 MILLION km? 7 BILLION MARS 6,.
Slide 8: From Early Exploration to a Self-Sustaining City on Mars
FROM EARLY EXPLORATION TO A SELF-SUSTAINING CITY ON MARS
Slide 9: Now
NOW WANT TO GO CAN AFFORD TO GO COST OF TRIP TO MARS = INFINITE MONEY
Slide 10: Using Traditional Methods
USING TRADITIONAL METHODS WANT TO GO CAN AFFORD TO GO COST OF TRIP TO MARS = $10 BILLION / PERSON
Slide 11: What's Needed
WHAT’S NEEDED WANT TO GO CAN AFFORD TO GO COST OF TRIP TO MARS = MEDIAN COST OF A HOUSE IN THE UNITED STATES
Slide 12: Improving Cost per Ton to Mars by Five Million Percent
IMPROVING COST PER TON TO MARS BY FIVE MILLION PERCENT
Slide 13: Full Reusability, Refilling, Propellant Production, Right Propellant
FULL REUSABILIT Y REFILLING IN ORBIT PROPELLANT PRODUCTION ON MARS RIGHT PROPELLANT
Slide 14: Full Reusability
FULL REUSABILIT Y
Slide 15: Full reusability is essential
To make Mars trips possible on a large-enough scale to create a self-sustaining city, full reusability is essential
Slide 16: Boeing 737 cost comparison
Boeing 737 Price $90M Passenger Capability 180 people Cost/Person - Single Use $500,000 Cost/Person - Reusable $43 (LA to Las Vegas) Cost of Fuel / Person $10
Slide 17: Refilling in Orbit
REFILLING IN ORBIT
Slide 18: Refilling in orbit benefits
Not 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
Slide 19: Propellant on Mars
PROPELLANT ON MARS
Slide 20: Propellant on Mars benefits
Allows 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
Slide 21: Right Propellant
RIGHT PROPELLANT
Slide 22: Propellant comparison
C H /O 12 22.4 2 H /O 2 2 CH /O 4 2 KEROSENE HYDROGEN/OXYGEN DEEP-CRYO METHALOX VEHICLE SIZE COST OF PROP REUSABILITY MARS PROPELLANT PRODUCTION PROPELLANT TRANSFER GOOD OK BAD VERY BAD
Slide 23: Four key elements
FULL REUSABILIT Y REFILLING IN ORBIT PROPELLANT PRODUCTION ON MARS RIGHT PROPELLANT
Slide 24: System Architecture
SYSTEM ARCHITECTURE TARGETED REUSE PER VEHICLE 1,000 uses per booster 100 per tanker 12 uses per ship
Slide 25: Vehicle Design and Performance
VEHICLE DESIGN AND PERFORMANCE
Slide 26: Carbon-fiber structure, densified methane/oxygen
Carbon-fiber primary structure Densified CH4 /O2 propellant Autogenous pressurization
Slide 27: Vehicles by Performance
VEHICLES BY PERFORMANCE VEHICLE NAME INDIA GSLY 5.000 ANTARES: 7,000 SOYUZ 2-18 200 1 | CHINA LM7 ATLAS V551 188 0 JAPAN H-IIB 19.000 ARIANE 5 20.000 PROTONM/ BREEZEM 22,000 FALCON 9 22,800 DELTAIV HEAVY 200 FALCON HEAVY 34.400 SATURN V 136,000 MARS VEHICLE 360,000
Slide 28: Vehicles by Performance
VEHICLES BY PERFORMANC Lotht tat | ll VEHICLE INDIA GSLY ANTARES SOYUZ2-1B CHINALM7 = ATLASV551JAPANH-IIB_ = ARIANES PROTONM/ FALCON DELTAIV FALCON SATURN MARS NAME BREEZE M HEAVY HEAVY VEHICLE rar.o Ura 5,000 7000 8.200 133500 18.860 00 20,000 22,000 22,800 28,300 54.400 135,000 550,000,
Slide 29: Mars Vehicle vs Saturn V
GROSS 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 13,033 122 550 300 SATURN V 3,039 35 3,579 111 135 RATIO 3.5 3.6 3.6 4d HUMAN
Slide 30: Raptor Engine
RAPTOR ENGINE
Slide 31: Raptor engine specifications
Cycle Full-flow staged combustion Oxidizer Subcooled liquid oxygen Fuel Subcooled liquid methane Chamber Pressure 300 bar Throttle Capability 20% to 100% thrust Sea-Level Nozzle Expansion Ratio: 40 Thrust (SL): 3,050 kN Isp (SL): 334 s Vacuum Nozzle Expansion Ratio: 200 Thrust: 3,500 kN Isp: 382 s
Slide 32: Rocket Booster
ROCKET BOOSTER
Slide 33: Booster specifications
Length 77.5 m Diameter 12 m Dry Mass 275 t Propellant Mass 6,700 t Raptor Engines 42 Sea Level Thrust 128 MN Vacuum Thrust 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 boos
Slide 34: Engine configuration
Engine configuration Outer ring: 21 Inner ring: 14 Center cluster: 7 Outer engines fixed in place Only center cluster gimbals
Slide 35: Interplanetary Spaceship
INTERPLANETARY SPACESHIP
Slide 36: Spaceship specifications
Length 49.5 m Max Diameter 17 m Raptor Engines 3 Sea-Level - 361s Isp 6 Vacuum - 382s Isp Vacuum Thrust 31 MN Propellant Mass Ship: 1,950 t Tanker: 2,500 t Dry Mass Ship: 150 t Tanker: 90 t Cargo/Prop to LEO Ship: 300 t Tanker: 380 t Cargo to Mars 450 t (with transfer on orbit) Long term goal of 100
Slide 37: Ship Capacity with Full Tanks
SHIP CAPACITY WITH FULL TANKS
Slide 38: Arrival
ARRIVAL 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
Slide 39: Propellant Plant
PROPELLANT PLANT
Slide 40: Propellant plant on Mars
First 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
Slide 41: Costs
COSTS With full reuse, our overall architecture enables significant reduction in cost to Mars BOOSTER TANKER SHIP FABRICATION COST $230M $130M 200M LIFETIME LAUNCHES 1,000 100 2 LAUNCHES PER MARS TRIP é 5 1 AVERAGE MAINTENANCE COST PER USE $0.2 $05M $10M TOTAL COST PER ONE MARS TRIP 511M 8M $43 Amor
Slide 42: Funding
FUNDING Steal Underpants Launch Satellites Send Cargo and Astronauts to ISS Kickstarter Profit
Slide 43: Timelines
TIMELINES
Slide 44: 2002
2002
Slide 45: Company milestones 2002-2016
besaltid 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, 0 tons ta LEO, expendable, Dragon spacecraft to orbit and back 2012 Dragon spacecraft delivers and returns, cargo from spa
Slide 46: Future
FUTURE
Slide 47: Next Steps
NEXT STEPS FALCON HEAVY ‘CREW DRAGON DEVELOPMENT RED DRAGON MISSIONS INTERPLANETARY TRANSPORTATION SYSTEM ORBITAL TESTING SHIP TESTING [eARSGRUTETS ‘STRUCTURES DEVELOPMENT PROPULSION DEVELOPMENT BOOSTER TESTING 1 L n L L 1 Ll L 1 1 1 2016 2017 2018 2019 2020 2021 2022 2023, 2024 2025 2026 2027 LAUNC
Slide 48: Red Dragon
RED DRAGON
Slide 49: Mission Objectives
Mission 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
Slide 50: Raptor Firing
RAPTOR FIRING
Slide 51: Slide 51
Slide 52: Carbon Fiber Tank
CARBON FIBER TANK
Slide 53: Slide 53
Slide 54: Slide 54
Slide 55: Slide 55
Slide 56: Slide 56
Slide 57: Beyond Mars
BEYOND MARS
Slide 58: Jupiter
JUPITER
Slide 59: Enceladus
ENCELADUS
Slide 60: Europa
EUROPA
Slide 61: Saturn
SATURN