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    Why mission mars .. from Space X

    Why mission mars .. from Space X

    F5 months ago 361

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    #Sustainability#Elonmuak#Reusablerockets#Spacetravel#Interplanetarymission#Marsexploration
    Why  mission mars .. from Space X  - Page 1
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    WHY GO ANYWHERE?
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    Why  mission mars .. from Space X  - Page 3
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    WHY MARS?
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    HUMANITY’S GREATEST ADVENTURE
Credit: Roberto Ziche, NASA, planetpixelemporium.com, planetscapes.com
    5/61
    Why  mission mars .. from Space X  - Page 6
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    Why  mission mars .. from Space X  - Page 7
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    FROM EARLY EXPLORATION TO A SELF-SUSTAINING CITY ON MARS
    8/61
    COST OF TRIP TO MARS 
= 
INFINITE MONEY
WANT TO GO CAN AFFORD TO GO
NOW
    9/61
    COST OF TRIP TO MARS 
= 
$10 BILLION / PERSON
WANT TO GO CAN AFFORD TO GO
USING TRADITIONAL METHODS
    10/61
    COST OF TRIP TO MARS 
= 
MEDIAN COST OF A HOUSE IN THE UNITED STATES
WANT TO GO CAN AFFORD TO GO
WHAT’S NEEDED
    11/61
    IMPROVING COST PER TON TO MARS BY FIVE MILLION PERCENT
    12/61
    RIGHT PROPELLANT
FULL REUSABILITY
REFILLING IN ORBIT
PROPELLANT PRODUCTION ON MARS
    13/61
    FULL REUSABILITY
    14/61
    To make Mars trips possible on a large-enough scale to 
create a self-sustaining city, full reusability is essential
    15/61
    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
    16/61
    REFILLING IN ORBIT
    17/61
    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
    18/61
    PROPELLANT ON MARS
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    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
    20/61
    RIGHT PROPELLANT
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    HYDROGEN/OXYGEN
H2 /O2
VEHICLE SIZE
COST OF PROP
REUSABILITY
MARS PROPELLANT PRODUCTION
PROPELLANT TRANSFER
GOOD
DEEP-CRYO METHALOX
CH4 /O2
OK
BAD
VERY BAD
KEROSENE
C12H22.4 /O2
    22/61
    RIGHT PROPELLANT
FULL REUSABILITY
REFILLING IN ORBIT
PROPELLANT PRODUCTION ON MARS
    23/61
    TARGETED REUSE PER VEHICLE
1,000 uses per booster
100 per tanker
12 uses per ship
SYSTEM ARCHITECTURE
    24/61
    VEHICLE DESIGN AND PERFORMANCE
    25/61
    Carbon-fiber primary structure 
Densified CH /O2 propellant
Autogenous pressurization
4
    26/61
    VEHICLES
BY PERFORMANCE
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    VEHICLES
BY PERFORMANCE
    28/61
    Why  mission mars .. from Space X  - Page 29
    29/61
    RAPTOR ENGINE
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    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 
Vacuum Nozzle
Expansion Ratio: 200 
Thrust: 3,500 kN 
Isp: 382 s
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    ROCKET BOOSTER
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    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
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    Engine configuration
Outer ring: 21
Inner ring: 14
Center cluster: 7
Outer engines fixed in place 
Only center cluster gimbals
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    INTERPLANETARY SPACESHIP
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    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
    36/61
    SHIP CAPACITY WITH FULL TANKS
    37/61
    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
    38/61
    PROPELLANT PLANT
    39/61
    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
    40/61
    COSTS
    41/61
    FUNDING
Steal Underpants 
Launch Satellites 
Send Cargo and Astronauts to ISS 
Kickstarter 
Profit
    42/61
    TIMELINES
    43/61
    2002
    44/61
    Why  mission mars .. from Space X  - Page 45
    45/61
    FUTURE
    46/61
    NEXT STEPS
    47/61
    RED DRAGON
    48/61
    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
    49/61
    RAPTOR FIRING
    50/61
    Why  mission mars .. from Space X  - Page 51
    51/61
    CARBON FIBER TANK
    52/61
    Why  mission mars .. from Space X  - Page 53
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    Why  mission mars .. from Space X  - Page 54
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    Why  mission mars .. from Space X  - Page 55
    55/61
    Why  mission mars .. from Space X  - Page 56
    56/61
    BEYOND MARS
    57/61
    JUPITER
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    ENCELADUS
    59/61
    EUROPA
    60/61
    SATURN
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    Why mission mars .. from Space X

    • 2. WHY GO ANYWHERE?
    • 4. WHY MARS?
    • 5. HUMANITY’S GREATEST ADVENTURE Credit: Roberto Ziche, NASA, planetpixelemporium.com, planetscapes.com
    • 8. FROM EARLY EXPLORATION TO A SELF-SUSTAINING CITY ON MARS
    • 9. COST OF TRIP TO MARS = INFINITE MONEY WANT TO GO CAN AFFORD TO GO NOW
    • 10. COST OF TRIP TO MARS = $10 BILLION / PERSON WANT TO GO CAN AFFORD TO GO USING TRADITIONAL METHODS
    • 11. COST OF TRIP TO MARS = MEDIAN COST OF A HOUSE IN THE UNITED STATES WANT TO GO CAN AFFORD TO GO WHAT’S NEEDED
    • 12. IMPROVING COST PER TON TO MARS BY FIVE MILLION PERCENT
    • 13. RIGHT PROPELLANT FULL REUSABILITY REFILLING IN ORBIT PROPELLANT PRODUCTION ON MARS
    • 14. FULL REUSABILITY
    • 15. To make Mars trips possible on a large-enough scale to create a self-sustaining city, full reusability is essential
    • 16. 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
    • 17. REFILLING IN ORBIT
    • 18. 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
    • 19. PROPELLANT ON MARS
    • 20. 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
    • 21. RIGHT PROPELLANT
    • 22. HYDROGEN/OXYGEN H2 /O2 VEHICLE SIZE COST OF PROP REUSABILITY MARS PROPELLANT PRODUCTION PROPELLANT TRANSFER GOOD DEEP-CRYO METHALOX CH4 /O2 OK BAD VERY BAD KEROSENE C12H22.4 /O2
    • 23. RIGHT PROPELLANT FULL REUSABILITY REFILLING IN ORBIT PROPELLANT PRODUCTION ON MARS
    • 24. TARGETED REUSE PER VEHICLE 1,000 uses per booster 100 per tanker 12 uses per ship SYSTEM ARCHITECTURE
    • 25. VEHICLE DESIGN AND PERFORMANCE
    • 26. Carbon-fiber primary structure Densified CH /O2 propellant Autogenous pressurization 4
    • 27. VEHICLES BY PERFORMANCE
    • 28. VEHICLES BY PERFORMANCE
    • 30. RAPTOR ENGINE
    • 31. 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 Vacuum Nozzle Expansion Ratio: 200 Thrust: 3,500 kN Isp: 382 s
    • 32. ROCKET BOOSTER
    • 33. 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
    • 34. Engine configuration Outer ring: 21 Inner ring: 14 Center cluster: 7 Outer engines fixed in place Only center cluster gimbals
    • 35. INTERPLANETARY SPACESHIP
    • 36. 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
    • 37. SHIP CAPACITY WITH FULL TANKS
    • 38. 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
    • 39. PROPELLANT PLANT
    • 40. 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
    • 41. COSTS
    • 42. FUNDING Steal Underpants Launch Satellites Send Cargo and Astronauts to ISS Kickstarter Profit
    • 43. TIMELINES
    • 44. 2002
    • 46. FUTURE
    • 47. NEXT STEPS
    • 48. RED DRAGON
    • 49. 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
    • 50. RAPTOR FIRING
    • 52. CARBON FIBER TANK
    • 57. BEYOND MARS
    • 58. JUPITER
    • 59. ENCELADUS
    • 60. EUROPA
    • 61. SATURN


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