Mars

WHY GO ANYWHERE?

WHY MARS?

HUMANITY’S GREATEST ADVENTURE Credit: Roberto Ziche, NASA, planetpixelemporium.com, planetscapes.com

FROM EARLY EXPLORATION TO A SELF-SUSTAINING CITY ON MARS

NOW WANT TO GO CAN AFFORD TO GO COST OF TRIP TO MARS = INFINITE MONEY

USING TRADITIONAL METHODS WANT TO GO CAN AFFORD TO GO COST OF TRIP TO MARS = $10 BILLION / PERSON

WHAT’S NEEDED WANT TO GO CAN AFFORD TO GO COST OF TRIP TO MARS = MEDIAN COST OF A HOUSE IN THE UNITED STATES

IMPROVING COST PER TON TO MARS BY FIVE MILLION PERCENT

FULL REUSABILITY REFILLING IN ORBIT PROPELLANT PRODUCTION ON MARS RIGHT PROPELLANT

FULL REUSABILITY

To make Mars trips possible on a large-enough scale to create a self-sustaining city, full reusability is essential

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

REFILLING IN ORBIT

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 exponential cost increase

PROPELLANT ON MARS

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

RIGHT PROPELLANT

C H /O H/O CH/O 12 22.4 2 2 2 4 2 KEROSENE HYDROGEN/OXYGEN DEEP!CRYO METHALOX VEHICLE SIZE COST OF PROP REUSABILITY MARS PROPELLANT PRODUCTION PROPELLANT TRANSFER GOOD OK BAD VERY BAD

FULL REUSABILITY REFILLING IN ORBIT PROPELLANT PRODUCTION ON MARS RIGHT PROPELLANT

SYSTEM ARCHITECTURE TARGETED REUSE PER VEHICLE
 1,000 uses per booster
 100 per tanker
 12 uses per ship

VEHICLE DESIGN AND PERFORMANCE

Carbon-fiber primary structure 
 Densified CH /O2 propellant
 4 Autogenous pressurization

VEHICLES
 BY PERFORMANCE

VEHICLES
 BY PERFORMANCE

RAPTOR ENGINE

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

ROCKET BOOSTER

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 boostback burn and landing Grid fins guide rocket back through atmosphere to precision landing

Engine configuration Outer ring: 21 Inner ring: 14 Center cluster: 7
 Outer engines fixed in place Only center cluster gimbals

INTERPLANETARY SPACESHIP

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+ passengers/ship

SHIP CAPACITY WITH FULL TANKS

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 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

PROPELLANT PLANT

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

COSTS

FUNDING Steal Underpants Launch Satellites Send Cargo and Astronauts to ISS Kickstarter Profit

TIMELINES

2002

FUTURE

NEXT STEPS

RED DRAGON

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

RAPTOR FIRING

CARBON FIBER TANK

BEYOND MARS

JUPITER

ENCELADUS

SATURN

EUROPA