Colorado Space Grant Consortium Gateway To Space ASEN / ASTR 2500 Class #19 Gateway To Space ASEN / ASTR 2500 Class #19 T-18

One minute:

-Announcements -One Minute Reports -Mid semester Team Evaluation Due -Camera Programming Questions -Rest of Launch Vehicles -Next Classes – Spider (Thur) and Pre-launch inspection (Tues) -> Bring your hardware Today:

- Project help at Space Grant - Most people will help if you schedule a time to get that help - Use Tim May - Hardware? - My next four weeks… Announcements

Announcements

Announcements

Announcements

Announcements

Announcements

Announcements

Announcements

Announcements

One Minute Reports: - What launch vehicle took the Mars Rover to Mars? - Why was China putting that guy in space more important than the X-prize? - What other countries have real serious space programs? - Sea Launch – Private or government? - Cost/kg lower because of Russia/China labor costs? - What is your favorite old rocket? - What made the Saturn V carry so much cargo? - What are some of the reasons rockets blew up? - Do you think Saturn V was a better a launch vehicle to transport humans?

One Minute Reports: - What launch vehicle took the Mars Rover to Mars? - Why was China putting that guy in space more important than the X-prize? - What other countries have real serious space programs? - Sea Launch – Private or government? - Cost/kg lower because of Russia/China labor costs? - What is your favorite old rocket? - What made the Saturn V carry so much cargo? - What are some of the reasons rockets blew up? - Do you think Saturn V was a better a launch vehicle to transport humans?

One Minute Reports: - Why didn’t they pass down the knowledge for the Saturn V? - Which country is the US most likely to work with in the future (space-wise)? - What direction do you think we should take (Augustine report)? - Should we watch the Right Stuff? - Don’t the engineer know that they don’t have enough thrust? - Space elevator replace rockets? - Where do you get to eat under a Saturn V?

One Minute Reports: - Why didn’t they pass down the knowledge for the Saturn V? - Which country is the US most likely to work with in the future (space-wise)? - What direction do you think we should take (Augustine report)? - Should we watch the Right Stuff? - Don’t the engineer know that they don’t have enough thrust? - Space elevator replace rockets? - Where do you get to eat under a Saturn V?

One Minute Reports: - What do we have to have done for preflight inspection? - Can we watch the movie “The Right Stuff?” - If camera stops working, who do we talk to? - How far should we be through our project at this point? - Camera display date and time on picture? - These cameras are evil! - Can we get more hot glue for free? - Why do we use aluminum tape instead of duck tape?

One Minute Reports: - Will we see the results of the team evaluations? - What is the temperature of outer space? - Does our whole group get the same grade? - Will space propulsion be on the test? - What are the three sheets of foam core?

One Minute Reports: - Will we see the results of the team evaluations? - What is the temperature of outer space? - Does our whole group get the same grade? - Will space propulsion be on the test? - What are the three sheets of foam core?

Colorado Space Grant Consortium Launch Vehicles Part 2 Class #18 Launch Vehicles Part 2 Class #18

Present

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

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

Present: First Shuttle Flight Video

Present: SRB Separation Video

Present: External Tank Video

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

Present: Atlas II Video

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

Present: Titan IV Video

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

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Present: Delta IV Height m ( ft) Diameter 5 m (16.4 ft) Mass 249, ,400 kg (550, ,616,800 lb) Stages 2 Capacity Payload to LEO 8, ,800 kg (18, ,800 lb) Payload to GTO

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

Present:

Present: Pegasus Video

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

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

Present: Ariane V Video

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

Present:

Present: H2 Video

Present: Long March CZ2E (China) Thrust:5,922,000 N (1,331,000 lb) Fueled Weight:464,000 kg Payload to Orbit:8,800 kg LEO Cost per launch:$50,000,000 Cost per kg:$5,681

Yang Liwei

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:9,000,000 N (2,000,000 lb) Fueled Weight:689,000 kg Payload to Orbit:20,000 kg LEO Cost per launch:$70,000,000 Cost per kg:$3,500

Present:

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 kN (183 klbf) at liftoff Specific impulse 245 kgf·s/kg (2.40 kN·s/kg) at liftoff Specific impulse 310 kgf·s/kg (3.04 kN·s/kg) in vacuum

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

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 built - Pitchka (Little Bird) - Baikal (Typhoon) All dismantled in 1995

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Future

Future/Past:

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 kN (102 klbf) -Launch video

Future:

Falcon 9: -Length: 54.3 m (178 ft) -Width: 3.6 m (12 ft) -Mass (LEO, 5m fairing): 325,000 kg (716 klb) -Mass (GTO, 4m 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 -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 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

Future/Past:

NASA’s Exploration Roadmap Lunar Lander Development Ares V Development Earth Departure Stage Development Surface Systems Development Orion CEV Development Ares I Development Space Shuttle Ops Lunar Outpost Buildup Initial Orion Capability Ares/Orion Production and Operations Lunar Robotic Missions Science Robotic Missions 1st Human Orion Flight 7th Human Lunar Landing Early Design Activity Demonstrate Commercial Crew/Cargo for ISS Demonstrate Commercial Crew/Cargo for ISS Mars Expedition Design

Ares I Crew Launch Vehicle Earth Departure Stage Orion Crew Exploration Vehicle Lunar Lander ELO Ambassador Briefing – 78 Ares V Cargo Launch Vehicle Our Exploration Fleet

Crew Lander S-IVB (1 J-2 engine) 240k lb LOx/LH 2 S-II (5 J-2 engines) 1M lb LOx/LH 2 S-IC (5 F-1 engines) 3.9M lb LOx/RP Lunar Lander Earth Departure Stage (EDS) (1 J-2X) 499k lb LOx/LH 2 Core Stage (5 RS-68 Engines) 3.1M lb LOx/LH 2 Upper Stage (1 J-2X) 280k lb LOx/LH 2 5-Segment Reusable Solid Rocket Booster (RSRB) Space Shuttle Ares I Ares VSaturn V Height: ft Gross Liftoff Mass: 4.5M lb 55k lbm to LEO Height: 321 ft Gross Liftoff Mass: 2.0M lb 48k lbm to LEO Height: 358 ft Gross Liftoff Mass: 7.3M lb 117k lbm to TLI 144k lbm to TLI in Dual- Launch Mode with Ares I 290k lbm to LEO Height: 364 ft Gross Liftoff Mass: 6.5M lb 99k lbm to TLI 262k lbm to LEO Two 5-Segment RSRBs Orion CEV Building on a Foundation of Proven Technologies – Launch Vehicle Comparisons –

Ares I Elements Stack Integration ~25 mT payload capacity 2 Mlb gross liftoff weight 315 ft in length NASA-led Stack Integration ~25 mT payload capacity 2 Mlb gross liftoff weight 315 ft in length NASA-led Upper Stage 280 klb LOx/LH 2 stage in. (5.5 m) diameter Aluminum-Lithium (Al-Li) structures Instrument unit and interstage Reaction Control System (RCS) / roll control for 1st stage flight Primary Ares I avionics system NASA Design / Contractor Production 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-2X) Expendable Pratt and Whitney Rocketdyne Orion 198 in. (5 m) diameter Orion 198 in. (5 m) diameter Interstage Cylinder Interstage Cylinder LAS Spacecraft Adapter Instrument Unit

Ares V Elements Stack Integration 65 mT payload capacity 7.3 Mlb gross liftoff weight 358 ft in length NASA-led Stack Integration 65 mT payload capacity 7.3 Mlb gross liftoff weight 358 ft in length NASA-led Earth Departure Stage TBD klb LOx/LH 2 stage in (5.5-m) diameter Aluminum-Lithium (Al-Li) structures Instrument unit and interstage Primary Ares V avionics system NASA Design / Contractor Production Core Stage Two recoverable five-segment PBAN-fueled boosters (derived from current Shuttle RSRM/B). Five Delta IV-derived RS-68 LOx/LH 2 engines (expendable). LSAM TBD LSAM TBD Spacecraft Adapter Interstage

NASA’s Exploration Transportation System

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

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Sci-Fi Future: -$10 Billion

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Sci-Fi Future:

Future/Past:

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

Future/Past: X-38 Video

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Future/Past: -X-33 -VentureStar

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Future: - Delta IV Heavy

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Future: -Shuttle Fly-back boosters

Future: -Hyper-X Hyper-X

Future: - X-37

Future: Ion Drive Video

Sci-Fi Future

Sci-Fi Future:

-Anti-matter

Sci-Fi Future: -Boussard Ramjet Fusion Propulsion

Sci-Fi Future: -Electrodynamic Tether

Sci-Fi Future: -Jovian Electrodynamic Tether

Sci-Fi Future: -Laser Propulsion

Sci-Fi Future: -Beamed Energy Propulsion

Sci-Fi Future: -Pulsed Detonation Rocket

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

Sci-Fi Future: -Plasma Rocket

Sci-Fi Future: -Plasma Rocket

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 - Lower end just inside atmosphere - Space plane flies to lower end for cargo times the cargo lifted by SSTO - GEO: YR Time Frame: Years for enabling technologies - YR for actual construction

Sci-Fi Future:

-$10 Billion