project bellerophon0 project bellerophon final design presentation greek hero who rode pegasus hero...

Project Bellerophon 1

PROJECT BELLEROPHON

Final Design PresentationGreek hero who rode Pegasus

HERO BELLEROPHON(buh-lair'-uh-fahn)


QuickTime™ and a decompressor

are needed to see this picture.

r = 50 m

Design Goals

Saturn V118,000 kg $2.7 billion

Ariane 45,000 kg$105 million

Vanguard9 kg$11 million

Pegasus375 kg$16 million

? ? ?Bellerophon200 g, 1kg, 5kg$???

Payload:Cost:

102 m




• Probability of success : 90.00% ( with catastrophic failure)

Design Requirements












are needed to see this picture.Perigee

• Perigee of 300 km

• Probability of success : 99.86% ( without catastrophic failure)







• All possible propellants, material and launch methods should be considered



• $ Minimize Cost $


Things We Ignored

• Physics not Politics• Development costs• 12 launches/year

FAA DecreePre-Application ConsultEnvironmental ReviewPayload Review

Hazard Analysis

Financial ResponsibilitySystem Failure ModesSafety Review

Compliance MonitoringFinal Approval




Preliminary Analysis

Materials

Aluminum

Composite

Steel

Titanium

Launch Methods

Ground

Aircraft

Balloon

Railgun

Conventional Gun

Propellants

Cyrogenic

Storable

Hybrid

Solid

LOX / LH2

H2O2 / RP-1

H2O2 / HTPB

AP / Al / HTPB

20,480 possible combinations for each payload!5,616




are needed to see this picture. QuickTime™ and a decompressor




are needed to see this picture.QuickTime™ and a

decompressorare needed to see this picture.



Model Analysis

MA - SS - DA - HT

Payload / Launch Description Staging Details

• Medium Payload (1 kg)

• Aircraft Launch

Stage 1 Stage 2 Stage 3

• Storable Prop

• Steel

• Solid Prop

• Aluminum

• Hybrid Prop

• Titanium

5,616 possible combinations for each payload!3




r = 50 m

Final Design







Rough Vehicle SubsystemsRequirements PropulsionInert Mass

RefinedVehicle

Trajectory

Final Vehicle

Launch Vehicle

AerothermalAvionicsD & C

PropulsionStructuresTrajectory


Designing a Trajectory

• Can the vehicle make it into orbit?

• What is the best path to take to get there?

Nominal Trajectory - 1 kg Payload






Nominal Trajectory


D&C Controlled Trajectory


AerothermalAvionicsD & C

PropulsionStructuresTrajectory

Final Design

D & C NominalTrajectory

Vehicle ready for Monte Carlo

ControlledTrajectory



r = 50 m

Rough Vehicle SubsystemsRequirements PropulsionInert Mass

RefinedVehicle

Trajectory

Final Vehicle

Launch Vehicle




Accounting for ErrorsMonte Carlo Analysis

IdealVehicle

Manufacturing Uncertainties

Actual Vehicle

+ =

10,000 Xs

D&C Monte Carlo Simulator

Computes perigee

minert

mprop

m

.

.

.

Fre

quen

cy

Perigee (km)

1kg Launch Vehicle: Perigee Altitude HistogramStandard Dev = 16 km Mean = 368 km

RequirementPerigee > 300 km

Perigee (km)


1 kg Failure



Low on gas

Heavy

Poorengineperformance


Monte Carlo Trajectories


Monte Carlo Analysis Results

Payload Monte Carlo Results

0

100

200

300

400

500

600

700

Min Perigee Mean Perigee Max Perigee

Performance

Perigee (km)

200 g1 kg5 kg

99.99%99.99%

99.99%99.99%

100.00%100.00%

SuccessRate


Final Vehicle Specifics






are needed to see this picture.Payload: 200 gLength: 10.18 mDiameter: 1.29 m

Payload: 1 kgLength: 8.65 mDiameter: 1.13 m

Payload: 5 kgLength: 14.25 mDiameter: 1.84 m

Payload Mass [kg]

Vehicle GLOM [kg]

V [m/s]

Controlled Perigee [km]

0.2 2,580 11,900 486

1.0 1,750 9,890 367

5.0 6,290 10,150 513

Q u ic k T ime ™ a n d a d e c o mp re s s o r

a re n e e d e d to s e e th is p ic tu re .








Tour of Vehicle1 kg payload



Launch Vehicle



Helium Balloon

Gondola




Tour of Vehicle

1 kg payload





Stage 3

Stage 2

Stage 1

9 m





Stage 3

Nose Cone (Al / Ti)

Payload (1.64% of mstage3)

Propellant (AP / Al / HTPB)

Spin Table

3rd Stage Nozzle



mstage3 is 4% of GLOM




Tour of Vehicle

1 kg payload

Stage 2

Inter-stage Skirt

2nd Stage Avionics

Liquid Injection Thrust

Vector Control (LITVC) Tank

(H202)






Stage 1

Pressurant (N2)

Inter-tank Coupler

Oxidizer Tank (H202)

Fuel Tank (HTPB)





Mission Timeline1 kg payload

1 hr 35 min balloon ascent + 8 min 35 sec launch vehicle ascent= 1.7 hour total mission

Launch

h = 30 km

T+ = 0s

1st Stage Separation

h = 87.4 km

T+ = 140.8 s

Nose Cone Jettison

h = 90.00 km

2nd Stage Separation

h = 257 km

T+ = 320.0 s

3rd Stage Separation

h = 381 km

T+ = 515.3 s


Catastrophic RiskHistorical Analysis

Item Failure Rate Success Rate

Stage 1 Propellants 2.08% 97.92%



Stage / Payload Separation 0.23% 99.77%

Nose Cone Jettison 0.28% 99.72%

Electrical 0.43% 99.57%

Avionics 0.43% 99.57%

Total 6.16% 93.84%










Catastrophic RiskHistorical Analysis

Number of Launches

Success Rate for Past 10

10 60.00%

20 80.00%

30 100.00%

Pegasus

Number of Launches

Success Rate

≤ 12 60.00%

≤ 24 80.00%

> 24 93.84%






Cost Model

• Can we use existing prices from large launch vehicles to help find ours?

Payload Mass [kg]

Total Vehicle Cost

0.2 $35,000

1.0 $100,000

5.0 $300,000


Cost Model

• Build and launch cost includes:- Material - Engine - Handling- Labor - Propellant - Avionics- Tank - Balloon - Gondola






are needed to see this picture.Payload: 200 g

$ 3.6 M

Payload: 1 kg

$ 3.2 M

Payload: 5 kg

$ 4.7 M


• Small launch vehicle price : $ 4M

Conclusions

• High altitude launch is a necessity






are needed to see this picture.• Need to optimize trajectory and D&C

• Space grade avionics are too expensive

• Engines and tanks do not scale simply

• Prices are difficult to assess


Meet the TeamAerothermal Brian Budzinski

Jason Darby Chris Strauss Alex Woods Jayme Zott

TrajectoryScott Breitengross

Daniel ChuaKyle DonahueBradley Ferris

Allen GuzikElizabeth Harkness

Jun Kanehara

Avionics Nicole Bryan

Timothy Lorenzana Justin Rhodes Danielle Yaple

Propulsion Jerald Balta

John Beasley Stephen Bluestone

Richard Hinton Dana Lattibeaudiere

William Ling Stephanie Morris Stephan Shurn Nicole Wilcox

Structures David Childers Jessica Doyle

Steven Hiu Steven Izzo Molly Kane

Jessica Schoenbauer Sarah Shoemaker Vincent Teixeira Brandon White

D & C Albert Chaney Alfred Lynam Jeffrey Stuart Adam Waite

Michael Walker

project bellerophon0 project bellerophon final design presentation greek hero who rode pegasus hero...

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