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

2. 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

3. - Marv Luttges CDR General Comments:

4. - Marv Luttges CDR General Comments:

5. Announcements:

6. Announcements:

7. Announcements:

8. Announcements:

9. In Class Exercise Before we get started…

10. 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

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

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

13. Building a Rocket on Paper: 3.)Calculate the 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/s2 1 pound-force = 4.45 N a=gravity=10 m/s 2

14. 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)

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

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

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

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

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

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

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

22. 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

23. 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

24. Past

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

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

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

29. Past: Mercury Redstone Video

30. Past: Go to the Moon Video

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

33. Past: The F1 Engine Video

34. Past:

35. Past: One Step Video

36. Past: Lunar Rover Video

37. Past: Apollo Astronaut Video

38. Saturn V: Can it be built today? - 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. Not really… According to Prof. Jesco von Puttkamer, Program Manager of Future Planning at NASA in 1999…

39. Present

40. 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)

41. 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

42. Present: First Shuttle Flight Video

43. Present: SRB Separation Video

44. Present: External Tank Video

45. 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

46. Present: Atlas II Video

47. 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

48. Present: Titan IV Video

49. Present:

50. 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

51. Present:

52. Present:

53. 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

54. Present:

55. 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

56. Present:

57. Present: Pegasus Video

58. 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

59. 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

60. Present: Ariane V Video

61. 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

62. Present:

63. Present: H2 Video

64. 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

65. Yang Liwei

66. 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

68. 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

69. Present:

70. 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

71. Present:

72. Present:

73. Present:

74. Present:

75. Present:

76. Present:

77. 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

78. 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

79. 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

80. Present/Past:

81. Present/Past:

82. Present/Past:

83. Present/Past:

84. Present/Past:

85. Present/Past:

86. Future

87. Future/Past:

88. 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

89. Future:

90. 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)

91. 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)

92. 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

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

94. Future/Past:

95. NASA’s Exploration Roadmap 050607080910111213141516171819202122232425 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

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

97. 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: 184.2 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 –

98. 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 216.5 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

99. 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 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 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

100. NASA’s Exploration Transportation System

101. 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

102. Future/Past:

103. Future/Past:

104. Future/Past:

105. Future/Past:

106. Future/Past:

107. Future/Past:

108. Sci-Fi Future: -$10 Billion

109. Future/Past:

110. Sci-Fi Future:

111. Future/Past:

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

113. Future/Past: X-38 Video

114. Future/Past:

115. Future/Past: -X-33 -VentureStar

116. Future/Past:

117. Future/Past:

118. Future/Past:

119. Future: - Delta IV Heavy

120. Future:

121. Future: -Shuttle Fly-back boosters

122. Future: -Hyper-X Hyper-X

123. Future: - X-37

124. Future: Ion Drive Video

125. Sci-Fi Future

126. Sci-Fi Future:

129. -Anti-matter

130. Sci-Fi Future: -Boussard Ramjet Fusion Propulsion

131. Sci-Fi Future: -Electrodynamic Tether

132. Sci-Fi Future: -Jovian Electrodynamic Tether

133. Sci-Fi Future: -Laser Propulsion

134. Sci-Fi Future: -Beamed Energy Propulsion

135. Sci-Fi Future: -Pulsed Detonation Rocket

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

137. Sci-Fi Future: -Plasma Rocket

138. Sci-Fi Future: -Plasma Rocket

139. 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!

140. 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

141. Sci-Fi Future:

142. -$10 Billion