Gateway To Space ASEN ASTR 2500 Class 18

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Gateway To Space ASEN / ASTR 2500 Class #18 Colorado Space Grant Consortium

Gateway To Space ASEN / ASTR 2500 Class #18 Colorado Space Grant Consortium

Announcements: - Guest Speaker next time – Spacecraft Propulsion - Still waiting to hear

Announcements: - Guest Speaker next time – Spacecraft Propulsion - Still waiting to hear about DV recorders - 18 Days to launch - Still working grade emails - Still reviewing DD Bs - DD C is due 11 -08 -07

CDR General Comments: - Marv Luttges

CDR General Comments: - Marv Luttges

CDR General Comments: - Marv Luttges

CDR General Comments: - Marv Luttges

Announcements:

Announcements:

Announcements:

Announcements:

Announcements:

Announcements:

Announcements:

Announcements:

Before we get started… In Class Exercise

Before we get started… In Class Exercise

Building a Rocket on Paper: - Please wait, everyone will be opening your envelopes

Building a Rocket on Paper: - Please wait, everyone will be opening your envelopes in a minute - Not every rocket design will work. . . - YOU ARE A ROCKET ENGINEER: You make $70, 000. 00 a year and you have a masters degree and drive a company Viper

Building a Rocket on Paper: 1. ) Build a rocket with the right people.

Building a Rocket on Paper: 1. ) Build a rocket with the right people. You will need… n Payload Specialist n Thruster Specialist n Fuel Expert n Structural Engineer

Building a Rocket on Paper: 2. ) Calculate total mass of your rocket, must

Building a Rocket on Paper: 2. ) Calculate total mass of your rocket, must include everything. Total mass = mass of fuel+payload+ structure+thrusters

Building a Rocket on Paper: 3. ) Calculate thrust needed to lift your rocket

Building a Rocket on Paper: 3. ) Calculate thrust needed to lift your rocket off the launch pad Needed thrust = total mass * gravity F = m * a [Newtons, N]) 1 N =1 kg*m/s 2 1 pound-force = 4. 45 N a=gravity=10 m/s 2

Building a Rocket on Paper: 4. ) Calculate the total lift (thrust) capability of

Building a Rocket on Paper: 4. ) Calculate the total lift (thrust) capability of your rockets thrusters 5. ) Does your structure support the total weight of the rocket? 6. ) Do you lift off the ground or did you crash and burn? 7. ) Could you lift off the surface of the moon? g(moon) = 1/6 g(earth)

Ion Engine: Max Thrust Engine/Fuel Mass Max Thrust (minus Engine/Mass) Remaining Mass = 200

Ion Engine: Max Thrust Engine/Fuel Mass Max Thrust (minus Engine/Mass) Remaining Mass = 200 N = 9, 000 kg (90, 000 N) = - 82, 000 N = - 8, 200 kg Ashes (2 kg) Professor (180 kg) Stamps (2 K kg) Water (20 K kg) Tires (200 K kg) Wood = 5 K kg (200 kg) NO NO NO Composite = 9 K kg (20 kg) NO NO NO Iron = 500 K kg (20, 000 kg) NO NO NO Aluminum = 3 M kg (2, 000 kg) NO NO NO Titanium = 5 M kg (2, 000 kg) NO NO NO Comments

Cold Gas Engine: Max Thrust Engine/Fuel Mass Max Thrust (minus Engine/Mass) Remaining Mass =

Cold Gas Engine: Max Thrust Engine/Fuel Mass Max Thrust (minus Engine/Mass) Remaining Mass = 22, 000 N = 1, 700 kg (17, 000 N) = 5, 000 N = 500 kg Ashes (2 kg) Professor (180 kg) Stamps (2 K kg) Water (20 K kg) Tires (200 K kg) Wood = 5 K kg (200 kg) YES NO NO NO Composite = 9 K kg (20 kg) YES NO NO NO Iron = 500 K kg (20, 000 kg) NO NO NO Aluminum = 3 M kg (2, 000 kg) NO NO NO Titanium = 5 M kg (2, 000 kg) NO NO NO Comments

Propane Engine: Max Thrust Engine/Fuel Mass Max Thrust (minus Engine/Mass) Remaining Mass = 100,

Propane Engine: Max Thrust Engine/Fuel Mass Max Thrust (minus Engine/Mass) Remaining Mass = 100, 000 N = 8, 000 kg (80, 000 N) = 20, 000 N = 2, 000 kg Ashes (2 kg) Professor (180 kg) Stamps (2 K kg) Water (20 K kg) Tires (200 K kg) Comments Wood = 5 K kg (200 kg) NO NO NO Structural Failure Composite = 9 K kg (20 kg) YES NO NO NO Structural Failure Iron = 500 K kg (20, 000 kg) NO NO NO Aluminum = 3 M kg (2, 000 kg) NO NO NO Titanium = 5 M kg (2, 000 kg) NO NO NO

Liquid Engine: Max Thrust Engine/Fuel Mass Max Thrust (minus Engine/Mass) Remaining Mass = 1,

Liquid Engine: Max Thrust Engine/Fuel Mass Max Thrust (minus Engine/Mass) Remaining Mass = 1, 500, 000 N = 103, 000 kg (1, 030, 000 N) = 470, 000 N = 47, 000 kg Ashes (2 kg) Professor (180 kg) Stamps (2 K kg) Water (20 K kg) Tires (200 K kg) Comments Wood = 5 K kg (200 kg) NO NO NO Structural Failure Composite = 9 K kg (20 kg) NO NO NO Structural Failure Iron = 500 K kg (20, 000 kg) YES YES NO Aluminum = 3 M kg (2, 000 kg) YES YES NO Titanium = 5 M kg (2, 000 kg) YES YES NO

Solid Engine: Max Thrust Engine/Fuel Mass Max Thrust (minus Engine/Mass) Remaining Mass = 3,

Solid Engine: Max Thrust Engine/Fuel Mass Max Thrust (minus Engine/Mass) Remaining Mass = 3, 000 N = 52, 000 kg (520, 000 N) = 2, 480, 000 N = 248, 000 kg Ashes (2 kg) Professor (180 kg) Stamps (2 K kg) Water (20 K kg) Tires (200 K kg) Comments Wood = 5 K kg (200 kg) NO NO NO Structural Failure Composite = 9 K kg (20 kg) NO NO NO Structural Failure Iron = 500 K kg (20, 000 kg) YES YES NO Aluminum = 3 M kg (2, 000 kg) YES YES YES Titanium = 5 M kg (2, 000 kg) YES YES YES

Launch Vehicles Past, Present, Future & Sci-Fi Future

Launch Vehicles Past, Present, Future & Sci-Fi Future

Outline: - Fine Print - Background & Rocket Types - Past - Present -

Outline: - Fine Print - Background & Rocket Types - Past - Present - Future - Sci-Fi Future

Rocket Types: - I don’t know everything about Launch Vehicles - I may not

Rocket Types: - I don’t know everything about Launch Vehicles - I may not be able to answer your questions - This lecture is to expose you to all the different types of launch vehicles - I can quit at any time

Background: - Thrust = the force that moves - Impulse = force over period

Background: - Thrust = the force that moves - Impulse = force over period of time - Specific Impulse = Isp = ratio of impulse to fuel used - Higher Isp usually indicates low thrust but very little fuel used - Will learn more in Propulsion Lecture - Rocket Types include: Solid, liquid, hybrid

Past

Past

Past/Present: Scout Thrust: Fueled Weight: Payload to Orbit: 464, 700 N (104, 500 lb)

Past/Present: Scout Thrust: Fueled Weight: Payload to Orbit: 464, 700 N (104, 500 lb) 21, 750 kg 270 kg LEO # of Flights: 188, 105 successful

Past: Jupiter C Thrust: Fueled Weight: Payload to Orbit: 334, 000 N (75, 090

Past: Jupiter C Thrust: Fueled Weight: Payload to Orbit: 334, 000 N (75, 090 lb) 29, 030 kg 9 kg LEO (14 kg) # of Flights: 6, 4 successful Explorer I

Past: Mercury Redstone Thrust: Fueled Weight: Payload to Orbit: 347, 000 N (78, 000

Past: Mercury Redstone Thrust: Fueled Weight: Payload to Orbit: 347, 000 N (78, 000 lb) Not Found kg 9 kg LEO # of Flights: 5, 5 successful Chimp “Ham”, Shepard, and Grissom

Past: Mercury Redstone Video

Past: Mercury Redstone Video

Past: Go to the Moon Video

Past: Go to the Moon Video

Past: Saturn V Thrust: Fueled Weight: Payload to Orbit: 34, 500, 000 N (7,

Past: Saturn V Thrust: Fueled Weight: Payload to Orbit: 34, 500, 000 N (7, 760, 000 lb) 2, 910, 000 kg 127, 000 kg LEO

Past: The F 1 Engine Video

Past: The F 1 Engine Video

Past:

Past:

Past: One Step Video

Past: One Step Video

Past: Lunar Rover Video

Past: Lunar Rover Video

Past: Apollo Astronaut Video

Past: Apollo Astronaut Video

Saturn V: Can it be built today? Not really… According to Prof. Jesco von

Saturn V: Can it be built today? Not really… According to Prof. Jesco von Puttkamer, Program Manager of Future Planning at NASA in 1999… - The blue prints still exist, however only on microfilm. - All the subcontractors and suppliers are no longer around. - The technology is old. We can build much smaller and lighter rockets today.

Present

Present

Present: United States - Shuttle - Atlas - Titan - Delta - Pegasus -

Present: United States - Shuttle - Atlas - Titan - Delta - Pegasus - Athena - Taurus - Falcon - ARES - Dragon (COTS) - Orion Foreign - France - Japan - China - Russia (Ariane) (H-series) (Long March) (Proton, Buran)

Present: Space Shuttle Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per

Present: Space Shuttle Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: SRB Recovery External Tank 28, 200, 000 N (6, 340, 000 lb) 2, 040, 000 kg 24, 400 kg LEO $245, 000 $10, 040

Present: First Shuttle Flight Video

Present: First Shuttle Flight Video

Present: SRB Separation Video

Present: SRB Separation Video

Present: External Tank Video

Present: External Tank Video

Present: Atlas IIAS Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per

Present: Atlas IIAS Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: 2, 980, 000 N (670, 000 lb) 234, 000 kg 8, 390 kg LEO $78, 000 $9, 296

Present: Atlas II Video

Present: Atlas II Video

Present: Titan IV Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per

Present: Titan IV Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: 4, 800, 000 N (1, 080, 000 lb) 860, 000 kg 21, 645 kg LEO $248, 000 $11, 457

Present: Titan IV Video

Present: Titan IV Video

Present:

Present:

Present: Delta II Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per

Present: Delta II Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: 2, 630, 000 N (591, 000 lb) 230, 000 kg 5045 kg LEO 17, 000 kg $60, 000 $11, 892

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Present: Delta IV Height 63 - 77. 2 m (206 - 253. 2 ft)

Present: Delta IV Height 63 - 77. 2 m (206 - 253. 2 ft) Diameter 5 m (16. 4 ft) Mass 249, 500 - 733, 400 kg (550, 000 - 1, 616, 800 lb) Stages 2 Capacity Payload to LEO 8, 600 - 25, 800 kg (18, 900 - 56, 800 lb) Payload to GTO

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Present:

Present: Pegasus Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg:

Present: Pegasus Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: 486, 000 N (109, 000 lb) 24, 000 kg 455 kg LEO $9, 000 $19, 800

Present:

Present:

Present: Pegasus Video

Present: Pegasus Video

Present: Ariane 44 L (France) Thrust: Fueled Weight: Payload to Orbit: Cost per launch:

Present: Ariane 44 L (France) Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: 5, 380, 000 N (1, 210, 000 lb) 470, 000 kg 9, 600 kg LEO $110, 000 $11, 458

Present: Ariane 5 (France) Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost

Present: Ariane 5 (France) Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: 11, 400, 000 N (2, 560, 000 lb) 737, 000 kg 18, 000 kg LEO $120, 000 $6, 666

Present: Ariane V Video

Present: Ariane V Video

Present: H-2 (Japan) Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per

Present: H-2 (Japan) Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: Video 3, 959, 200 N (890, 060 lb) 260, 000 kg 10, 500 kg LEO $190, 000 $18, 095

Present:

Present:

Present: H 2 Video

Present: H 2 Video

Present: Long March CZ 2 E (China) Thrust: Fueled Weight: Payload to Orbit: Cost

Present: Long March CZ 2 E (China) Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: 5, 922, 000 N (1, 331, 000 lb) 464, 000 kg 8, 800 kg LEO $50, 000 $5, 681

Yang Liwei

Yang Liwei

Present: Sea Launch / Zenit Widest Diameter: 14 feet Overall length: Approximately 200 feet

Present: Sea Launch / Zenit Widest Diameter: 14 feet Overall length: Approximately 200 feet All stages are kerosene/liquid oxygen fueled Capacity to geosynchronus transfer orbit: 6, 000 kg

Present: Proton D-1 (Russia) Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost

Present: Proton D-1 (Russia) Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: 9, 000 N (2, 000 lb) 689, 000 kg 20, 000 kg LEO $70, 000 $3, 500

Present:

Present:

Soyuz: Gross mass: 98, 100 lbm Propellant: 86, 400 lbm Diameter: 8 ft 10

Soyuz: Gross mass: 98, 100 lbm Propellant: 86, 400 lbm Diameter: 8 ft 10 in Length: 64 ft 4 in Burn time: 118 s Thrust 813 k. N (183 klbf) at liftoff Specific impulse 245 kgf·s/kg (2. 40 k. N·s/kg) at liftoff Specific impulse 310 kgf·s/kg (3. 04 k. N·s/kg) in vacuum

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Present/Past: Energia (Russia) Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per

Present/Past: Energia (Russia) Thrust: Fueled Weight: Payload to Orbit: Cost per launch: Cost per kg: 34, 800, 000 N (7, 820, 000 lb) 2, 400, 000 kg 90, 000 kg LEO $764, 000? $Not Known

Present/Past: Buran “Snowstorm” (Russia) First and only launch November 15, 1988 No one on

Present/Past: Buran “Snowstorm” (Russia) First and only launch November 15, 1988 No one on board - Life support not tested - CRT’s did not have software Only 2 orbits - This was limited because of computer memory Landed by autopilot

Present/Past: Aero Buran was test unit Had 24 test flights 3 others were being

Present/Past: Aero Buran was test unit Had 24 test flights 3 others were being built - Pitchka (Little Bird) - Baikal (Typhoon) All dismantled in 1995

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Future

Future

Future/Past:

Future/Past:

Falcon 1: - Length: 21. 3 m (70 ft) - Width: 1. 7 m

Falcon 1: - Length: 21. 3 m (70 ft) - Width: 1. 7 m (5. 5 ft) - Mass: 38, 555 kg (85 klbs) - Thrust on liftoff: 454 k. N (102 klbf) - Launch video

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Future:

Falcon 9: - Length: 54. 3 m (178 ft) - Width: 3. 6 m

Falcon 9: - Length: 54. 3 m (178 ft) - Width: 3. 6 m (12 ft) - Mass (LEO, 5 m fairing): 325, 000 kg (716 klb) - Mass (GTO, 4 m fairing): 323, 000 kg (713 klb) - Thrust (vacuum): 4. 4 MN (1 M lb)

Dragon: - Fully autonomous rendezvous and docking with manual override capability in crewed configuration

Dragon: - Fully autonomous rendezvous and docking with manual override capability in crewed configuration - Pressurized Cargo/Crew capacity of >2500 kg and 14 cubic meters - Down-cargo capability (equal to up-cargo)

Dragon: - Supports up to 7 passengers in Crew configuration - Reaction control system

Dragon: - Supports up to 7 passengers in Crew configuration - Reaction control system - 1200 kg of propellant from sub-orbital insertion to ISS rendezvous to reentry - Designed for water landing under parachute for ocean recovery

Dragon: - Lifting re-entry for landing precision & low-g’s - Ablative, high-performance heat shield

Dragon: - Lifting re-entry for landing precision & low-g’s - Ablative, high-performance heat shield

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NASA’s Exploration Roadmap 1 st Human Orion Flight 05 06 07 08 09 10

NASA’s Exploration Roadmap 1 st Human Orion Flight 05 06 07 08 09 10 11 12 13 14 15 16 17 18 19 20 Initial Orion Capability 21 22 23 24 25 Lunar Outpost Buildup 7 th Human Lunar Landing Lunar Robotic Missions Science Robotic Missions Demonstrate Commercial Crew/Cargo for ISS Mars Expedition Design Space Shuttle Ops Orion CEV Development Ares I Development Ares/Orion Production and Operations Early Design Activity Lunar Lander Development Ares V Development Earth Departure Stage Development Surface Systems Development

Our Exploration Fleet Earth Departure Stage Orion Crew Exploration Vehicle Ares V Cargo Launch

Our Exploration Fleet Earth Departure Stage Orion Crew Exploration Vehicle Ares V Cargo Launch Vehicle Lunar Lander Ares I Crew Launch Vehicle ELO Ambassador Briefing – 96

Building on a Foundation of Proven Technologies – Launch Vehicle Comparisons – Crew Lunar

Building on a Foundation of Proven Technologies – Launch Vehicle Comparisons – Crew Lunar Lander Orion CEV Lander Earth Departure Stage (EDS) (1 J-2 X) 499 k lb LOx/LH 2 Upper Stage (1 J-2 X) 280 k lb LOx/LH 2 S-IVB (1 J-2 engine) 240 k lb LOx/LH 2 S-II (5 J-2 engines) 1 M lb LOx/LH 2 Core Stage (5 RS-68 Engines) 3. 1 M lb LOx/LH 2 5 -Segment Reusable Solid Rocket Booster (RSRB) Two 5 -Segment RSRBs S-IC (5 F-1 engines) 3. 9 M lb LOx/RP Space Shuttle Ares I Ares V Saturn V Height: 184. 2 ft Gross Liftoff Mass: 4. 5 M lb Height: 321 ft Gross Liftoff Mass: 2. 0 M lb Height: 358 ft Gross Liftoff Mass: 7. 3 M lb Height: 364 ft Gross Liftoff Mass: 6. 5 M lb 55 k lbm to LEO 48 k lbm to LEO 117 k lbm to TLI 144 k lbm to TLI in Dual. Launch Mode with Ares I 290 k lbm to LEO 99 k lbm to TLI 262 k lbm to LEO

Ares I Elements Orion • 198 in. (5 m) diameter LAS Instrument Unit Spacecraft

Ares I Elements Orion • 198 in. (5 m) diameter LAS Instrument Unit Spacecraft Adapter Upper Stage • 280 klb LOx/LH 2 stage • 216. 5 in. (5. 5 m) diameter • Aluminum-Lithium (Al-Li) structures • Instrument unit and interstage • Reaction Control System (RCS) / roll control for 1 st stage flight • Primary Ares I avionics system • NASA Design / Contractor Production Stack Integration • ~25 m. T payload capacity • 2 Mlb gross liftoff weight • 315 ft in length • NASA-led Interstage Cylinder First Stage • Derived from current Shuttle RSRM/B • Five segments/Polybutadiene Acrylonitrile (PBAN) propellant • Recoverable • New forward adapter • Avionics upgrades • ATK Launch Systems Upper Stage Engine • Saturn J-2 derived engine (J-2 X) • Expendable • Pratt and Whitney Rocketdyne

Ares V Elements LSAM • TBD Stack Integration • • 65 m. T payload

Ares V Elements LSAM • TBD Stack Integration • • 65 m. T payload capacity 7. 3 Mlb gross liftoff weight 358 ft in length NASA-led Core Stage Earth Departure Stage Spacecraft Adapter • TBD klb LOx/LH 2 stage • 216. 5 in (5. 5 -m) diameter • Aluminum-Lithium (Al-Li) structures • Instrument unit and interstage • Primary Ares V avionics system • NASA Design / Contractor Production Interstage • Two recoverable five-segment PBAN-fueled boosters (derived from current Shuttle RSRM/B). • Five Delta IV-derived RS-68 LOx/LH 2 engines (expendable).

NASA’s Exploration Transportation System

NASA’s Exploration Transportation System

Our Nationwide Team ATK Launch Systems Marshall Ames Goddard Glenn Langley Dryden Kennedy Pratt

Our Nationwide Team ATK Launch Systems Marshall Ames Goddard Glenn Langley Dryden Kennedy Pratt and Whitney Rocketdyne Jet Propulsion Laboratory Johnson Michoud Assembly Facility Stennis

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Sci-Fi Future: - $10 Billion

Sci-Fi Future: - $10 Billion

Future/Past:

Future/Past:

Sci-Fi Future:

Sci-Fi Future:

Future/Past:

Future/Past:

Future/Past: - Crew Return Vehicle - X-38

Future/Past: - Crew Return Vehicle - X-38

Future/Past: X-38 Video

Future/Past: X-38 Video

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Future/Past: - X-33 - Venture. Star

Future/Past: - X-33 - Venture. Star

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Future: - Delta IV Heavy

Future: - Delta IV Heavy

Future: - Delta IV Heavy

Future: - Delta IV Heavy

Future: - Shuttle Fly-back boosters

Future: - Shuttle Fly-back boosters

Future: - Hyper-X

Future: - Hyper-X

Future: - X-37

Future: - X-37

Future: Ion Drive Video

Future: Ion Drive Video

Sci-Fi Future

Sci-Fi Future

Sci-Fi Future:

Sci-Fi Future:

Sci-Fi Future:

Sci-Fi Future:

Sci-Fi Future:

Sci-Fi Future:

Sci-Fi Future: - Anti-matter

Sci-Fi Future: - Anti-matter

Sci-Fi Future: - Boussard Ramjet Fusion Propulsion

Sci-Fi Future: - Boussard Ramjet Fusion Propulsion

Sci-Fi Future: - Electrodynamic Tether

Sci-Fi Future: - Electrodynamic Tether

Sci-Fi Future: - Jovian Electrodynamic Tether

Sci-Fi Future: - Jovian Electrodynamic Tether

Sci-Fi Future: - Laser Propulsion

Sci-Fi Future: - Laser Propulsion

Sci-Fi Future: - Beamed Energy Propulsion

Sci-Fi Future: - Beamed Energy Propulsion

Sci-Fi Future: - Pulsed Detonation Rocket

Sci-Fi Future: - Pulsed Detonation Rocket

Sci-Fi Future: - Space Based Laser Re-boost

Sci-Fi Future: - Space Based Laser Re-boost

Sci-Fi Future: - Plasma Rocket

Sci-Fi Future: - Plasma Rocket

Sci-Fi Future: - Plasma Rocket

Sci-Fi Future: - Plasma Rocket

Sci-Fi Future: - Space Elevator - Original concept as old as Mesopotamia: Biblical “Tower

Sci-Fi Future: - Space Elevator - Original concept as old as Mesopotamia: Biblical “Tower of Babel” and “Jacob’s Ladder” - Five Critical Technologies (Source: MSFC Study) - High Strength Materials - Tension Structures - Compression Structures - EM Propulsion - Supporting Infrastructure - May Lower Launch Costs to <$10/kg!

Sci-Fi Future: - $10 Billion - To LEO or GEO? - LEO: Possible Today

Sci-Fi Future: - $10 Billion - To LEO or GEO? - LEO: Possible Today - Lower end just inside atmosphere - Space plane flies to lower end for cargo - 10 -12 times the cargo lifted by SSTO - GEO: YR 2050+ - Time Frame: - 10 -20 Years for enabling technologies - YR 2050 + for actual construction

Sci-Fi Future:

Sci-Fi Future:

Sci-Fi Future: - $10 Billion

Sci-Fi Future: - $10 Billion