WHY GO ANYWHERE?

WHY MARS?

HUMANITY'S GREATEST ADVENTURE



FROM EARLY EXPLORATION TO A SELF-SUSTAINING CITY ON MARS



COST OF TRIP TO MARS

=

INFINITE MONEY

USING TRADITIONAL METHODS



COST OF TRIP TO MARS = $10 BILLION / PERSON

WHAT'S NEEDED



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

Passenger Capability

Cost/Person - Single Use

Cost/Person - Reusable

Cost of Fuel / Person

$90M 180 people $500,000 $43 (LA to Las Vegas) $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

VEHICLE SIZE

COST OF PROP

REUSABILITY

MARS PROPELLANT PRODUCTION

PROPELLANT TRANSFER

GOOD

OK

BAD

VERY BAD

C 12 H 22.4 /O 2

KEROSENE

H 2 /O 2

HYDROGEN/OXYGEN

CH 4 /O 2

DEEP /hyphen.case CRYO METHALOX

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



EARTH

MARS

VEHICLE DESIGN AND PERFORMANCE



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

VEHICLES BY PERFORMANCE


VEHICLES BY PERFORMANCE




HUMAN

RAPTOR ENGINE



Cycle

Oxidizer

Fuel

Chamber Pressure

Throttle Capability

Full-flow staged combustion

Subcooled liquid oxygen

Subcooled liquid methane

300 bar

20% to 100% thrust

Sea-Level Nozzle

Expansion Ratio: 40 Thrust (SL): 3,050 kN Isp (SL): 334 s

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

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77.5 m

Diameter

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12 m

Dry Mass

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275 t

Propellant Mass

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6,700 t

Raptor Engines

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/uni00A0/uni00A0/uni00A0/uni00A0/uni00A0/uni00A0/uni00A0

42

Sea Level Thrust

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/uni00A0/uni00A0/uni00A0/uni00A0/uni00A0/uni00A0/uni00A0/uni00A0

128 MN

Vacuum Thrust

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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

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

SHIP CAPACITY WITH FULL TANKS

EARTH-MARS TRANSIT TIME (DAYS) BY MISSION OPPORTUNITY


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

With full reuse, our overall architecture enables significant reduction in cost to Mars



FUNDING

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

TIMELINES

2002



FUTURE

NEXT STEPS

FALCON HEAVY

CREW DRAGON DEVELOPMENT

RED DRAGON MISSIONS

INTERPLANETARY TRANSPORTATION SYSTEM



LAUNCH WINDOW TO MARS

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

EUROPA

SATURN