1. 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
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2. 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
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3. 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
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4. 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
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5. Mission Configuration – 10 kilogram
Launch Vehicle
Dnepr-1 Rocket
Baikonur Cosmodrome, Kazakhstan
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6. 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)
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7. 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
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8. Launch Site Cape Canaveral Air Force Station, Florida
Insert Map/Picture/Diagram of Launch Facilities
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9. Design Alternative - Locomotion
Spring Cannon
Ground Launch
45° initial angle
Eliminated because g-force at launch exceeds Space Ball’s structural capability
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10. 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
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11. Back-up Slides
Alternative Launch Vehicles gram, 10 kilogram payload cases
Insert here
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12. Alternative Launch Vehicles – Arbitrary Payload Case PerformanceLV
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
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13. Alternative Launch Vehicles – Arbitrary Payload Case CostLV
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
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14. Spring Calculation PE = ½*k*x2 KE = PE KE = ½*m*v2 Vyf = Vy0 – gmoon*t
∆x = VX0*t
Insert additional spring figures
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