AAE450 Spring 2009

Launch Vehicle SelectionSpring Cannon Launch Vehicle Alternatives

Zarinah Blockton

Mission Ops~Group

Earth to LEO~Phase

March 26, 2009

[Blockton] [OPS]

AAE450 Spring 2009

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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AAE450 Spring 2009<3>

100 200 300 400 500 600 700 800 900 10000

500

1000

1500

2000

2500

3000

3500

4000

4500

5000

Circular Altitude (km)

Pay

load

Mas

s (k

g)

4400 kg200 km

3400 kg400 km

300 kg900 km

Dnepr-1 CharacteristicsVariable Value UnitsHeight 34.3 mDiameter 3 mNumber of StagesOrbit Inclination

350.5°

Purchase CostX-Prize Cost Reliability

$ 21,000,000$ 4,600,00011 of 12

Low Earth Orbit Performance

[Blockton] [OPS]

AAE450 Spring 2009

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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AAE450 Spring 2009

Mission Configuration – 10 kilogram Launch Vehicle

– Dnepr-1 Rocket– Baikonur Cosmodrome, Kazakhstan

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AAE450 Spring 2009

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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AAE450 Spring 2009<7>

Falcon 9 Characteristics

Variable Value UnitsHeight 55 mDiameter 3.66 mMass 333,400 kgNumber of StagesOrbit InclinationPurchase Cost

228.5°$ 38,200,000

0 500 1000 1500 2000 25000

2000

4000

6000

8000

10000

12000

Circular Altitude (km)

Pay

load

Mas

s (k

g)

7085 kg

2000 km

9953 kg400 km

Low Earth Orbit Performance

[Blockton] [OPS]

AAE450 Spring 2009

Launch Site– Cape Canaveral Air Force Station, Florida

» Insert Map/Picture/Diagram of Launch Facilities

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AAE450 Spring 2009

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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AAE450 Spring 2009<10>

0 100 200 300 400 500 600 700 800 900 10000

10

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30

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1 second impact time

0.5 second impact time

Range (km)

Lan

din

g G

fo

rce 180

km30 g’s

0 100 200 300 400 500 600 700 800 900 10000

1000

2000

3000

4000

5000

6000

7000

Range (km)

Lau

nch

G f

orc

e

721 km30 g’s

18 km118 g’s

0 100 200 300 400 500 600 700 800 900 10000

5

10

15

20

25

30

35

Range (km)

Sp

rin

g E

xten

sio

n L

eng

th (

m)

540 km18 m spring

Spring Length for 30 g Take-offG force at Launch

G force upon Landing

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AAE450 Spring 2009<11>

Alternative Launch Vehicles - 100 gram, 10 kilogram payload cases

Insert here

Back-up Slides

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AAE450 Spring 2009<12>

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 9 400 9953 1885 8 9.90E-06 6,779.50 4,897.80 2,401.90

Delta IV H 400 23757 4760 19 6.50E-06 18,545.00 7,135.20 3,745.30

Atlas V 400 11300 2155 9 9.60E-06 7,835.80 5,272.50 2,620.20

LM 2C 400 2800 510 3 1.00E-05 1,517.00 2,773.90 909.79

LM 2E 400 6900 1286 6 1.00E-05 4,465.70 4,162.20 1,819.60

PSLV 400 3500 701 3 1.00E-05 2,206.40 4,290.70 909.79

Delta IV M 400 9400 1778 8 9.40E-06 6,359.90 4,599.80 2,280.50Delta IV M(4,2) 400 12500 2500 10 8.90E-06 8,897.70 5,419.50 2,699.00Delta IV M (5,2) 400 11050 2222 9 9.20E-06 7,705.30 5,089.90 2,511.00Delta IV M (5,4) 400 13750 2690 11 8.70E-06 9,874.30 5,678.30 2,902.20

Falcon 9 H 400 27980 5718 23 5.80E-06 22,234.00 7,491.20 4,045.50

Ares V 400 120000 22200 44 1.10E-03 80,600 8,100 32,300

Alternative Launch Vehicles – Arbitrary Payload CasePerformance

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AAE450 Spring 2009

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

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Alternative Launch Vehicles – Arbitrary Payload CaseCost

AAE450 Spring 2009

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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