Launch Vehicle Selection Spring Cannon Launch Vehicle Alternatives March 26, 2009 Launch Vehicle Selection Spring Cannon Launch Vehicle Alternatives Zarinah Blockton Mission Ops~Group Earth to LEO~Phase [Blockton] [OPS]

Mission Configuration – 100 gram Launch Vehicle Dnepr-1 Rocket Converted intercontinental ballistic missile Operated by the International Space Company Kosmotras Selected because of its low cost and high mission reliability [Blockton] [OPS]

Dnepr-1 Characteristics Variable Value Units Height 34.3 m Diameter 3 Number of Stages Orbit Inclination 50.5° Purchase Cost X-Prize Cost Reliability $ 21,000,000 $ 4,600,000 11 of 12 Low Earth Orbit Performance 300 kg 900 km [Blockton] [OPS]

Launch Site Baikonur Cosmodrome, Kazakhstan Although launch site is substantial distance north of the equator, launch performance and cost retain attractiveness Insert Map/Picture/Diagram of Launch Facilities [Blockton] [OPS]

Mission Configuration – 10 kilogram Launch Vehicle Dnepr-1 Rocket Baikonur Cosmodrome, Kazakhstan [Blockton] [OPS]

Mission Configuration – Arbitrary Launch Vehicle Falcon 9 Designed by Space ExplorationTechnologies (SpaceX), USA Although vehicle has not flown, mission reliability looks promising Reduced stages Simplified turbopump engines Selected because it achieved lowest cost per kilogram to Low Lunar Orbit (LLO) [Blockton] [OPS]

Falcon 9 Characteristics Variable Value Units Height 55 m Diameter 3.66 Mass 333,400 kg Number of Stages Orbit Inclination Purchase Cost 2 28.5° $ 38,200,000 Low Earth Orbit Performance 9953 kg 400 km [Blockton] [OPS]

Launch Site Cape Canaveral Air Force Station, Florida Insert Map/Picture/Diagram of Launch Facilities [Blockton] [OPS]

Design Alternative - Locomotion Spring Cannon Ground Launch 45° initial angle Eliminated because g-force at launch exceeds Space Ball’s structural capability [Blockton] [OPS]

Spring Length for 30 g Take-off G force at Launch Spring Length for 30 g Take-off 540 km 18 m spring 18 km 118 g’s G force upon Landing 721 km 30 g’s [Blockton] [OPS]

Back-up Slides Alternative Launch Vehicles - 100 gram, 10 kilogram payload cases Insert here [Blockton] [OPS] <11>

Alternative Launch Vehicles – Arbitrary Payload Case Performance LV Altitude (km) Mass (kg) Thrust (mN) Number of Thrusters mdot_opt Mpay (kg) Power Required (W) Mprop (kg) Dnepr 400 3400 632 3 1.00E-05 2,108.10 4,045.90 909.79 Falcon 9 9953 1885 8 9.90E-06 6,779.50 4,897.80 2,401.90 Delta IV H 23757 4760 19 6.50E-06 18,545.00 7,135.20 3,745.30 Atlas V 11300 2155 9 9.60E-06 7,835.80 5,272.50 2,620.20 LM 2C 2800 510 1,517.00 2,773.90 LM 2E 6900 1286 6 4,465.70 4,162.20 1,819.60 PSLV 3500 701 2,206.40 4,290.70 Delta IV M 9400 1778 9.40E-06 6,359.90 4,599.80 2,280.50 Delta IV M(4,2) 12500 2500 10 8.90E-06 8,897.70 5,419.50 2,699.00 Delta IV M (5,2) 11050 2222 9.20E-06 7,705.30 5,089.90 2,511.00 Delta IV M (5,4) 13750 2690 11 8.70E-06 9,874.30 5,678.30 2,902.20 Falcon 9 H 27980 5718 23 5.80E-06 22,234.00 7,491.20 4,045.50 Ares V 120000 22200 44 1.10E-03 80,600 8,100 32,300 [Blockton] [OPS] <12>

Alternative Launch Vehicles – Arbitrary Payload Case Cost LV 2009 Launch Cost Total $ LLO ($/kg) LL0 ($/kg) LEO Dnepr 21,257,667.55 2.64E+07 12,520.90 6,252.26 Falcon 9 38,201,663.20 4.60E+07 6,782.47 3,838.21 Delta IV H 308,289,232.41 3.20E+08 17,250.95 12,976.77 Atlas V 122,699,257.07 1.31E+08 16,732.94 10,858.34 LM 2C 31,886,501.32 3.58E+07 23,567.67 11,388.04 LM 2E 70,858,891.82 7.72E+07 17,288.36 10,269.40 PSLV 44,194,735.02 4.96E+07 22,469.72 12,627.07 Delta IV M 161,427,039.02 1.69E+08 26,535.55 17,173.09 Delta IV M(4,2) 167,495,724.70 1.76E+08 19,797.70 13,399.66 Delta IV M (5,2) 182,060,570.32 1.90E+08 24,679.59 16,476.07 Delta IV M (5,4) 194,197,941.68 2.03E+08 20,594.76 14,123.49 Falcon 9 H 98,232,848.23 1.11E+08 4,973.40 3,510.82 Ares V 500,000,000.00 5.47E+08 6,787.80 4,166.67 [Blockton] [OPS]

Spring Calculation PE = ½*k*x2 KE = PE KE = ½*m*v2 Vyf = Vy0 – gmoon*t ∆x = VX0*t Insert additional spring figures [Blockton] [OPS]