Gateway To Space ASEN ASTR 2500 Class 19

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

One minute:

Today: - 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

Announcements - 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 - My next four weeks…

Announcements - My next four weeks…

Announcements - My next four weeks…

Announcements - My next four weeks…

Announcements - My next four weeks…

Announcements - My next four weeks…

Announcements - My next four weeks…

Announcements - My next four weeks…

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 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 three sheets of foam core?

Launch Vehicles Part 2 Class #18 Colorado Space Grant Consortium

Present

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 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: SRB Separation Video

Present: External Tank Video

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: 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:

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

Present:

Present:

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

Present:

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: Pegasus Video

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 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: 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: H 2 Video

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

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 per kg: 9, 000 N (2, 000 lb) 689, 000 kg 20, 000 kg LEO $70, 000 $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 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 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 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 k. N (102 klbf) - Launch video

Future:

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 - 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 - 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

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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 Vehicle Lunar Lander Ares I Crew Launch Vehicle ELO Ambassador Briefing – 78

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 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 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

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

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Sci-Fi Future:

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

Future/Past: X-38 Video

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

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Future: - Delta IV Heavy

Future: - Delta IV Heavy

Future: - Shuttle Fly-back boosters

Future: - Hyper-X

Future: - X-37

Future: Ion Drive Video

Sci-Fi Future

Sci-Fi Future:

Sci-Fi Future:

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 - 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: - $10 Billion