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PROJECT BELLEROPHON

PROJECT BELLEROPHON. HERO BELLEROPHON. (buh-lair'-uh-fahn). Final Design Presentation. Greek hero who rode Pegasus. Design Goals. r = 50 m. Saturn V 118,000 kg $2.7 billion. 102 m. ? ? ?. Ariane 4 5,000 kg $105 million. Vanguard 9 kg $11 million. Bellerophon

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PROJECT BELLEROPHON

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  1. PROJECT BELLEROPHON HERO BELLEROPHON (buh-lair'-uh-fahn) Final Design Presentation Greek hero who rode Pegasus Project Bellerophon

  2. Design Goals r = 50 m Saturn V 118,000 kg $2.7 billion 102 m ? ? ? Ariane 4 5,000 kg $105 million Vanguard 9 kg $11 million Bellerophon 200 g, 1kg, 5kg $??? Pegasus 375 kg $16 million Payload: Cost: Project Bellerophon

  3. Design Requirements Perigee • Perigee of 300 km • Probability of success : 90.00% ( with catastrophic failure) • Probability of success : 99.86% ( without catastrophic failure) • All possible propellants, material and launch methods should be considered • $ Minimize Cost $ Project Bellerophon

  4. Things We Ignored FAA Decree Pre-Application Consult Environmental Review Payload Review Hazard Analysis Financial Responsibility System Failure Modes Safety Review • Physics not Politics • Development costs • 12 launches/year Compliance Monitoring Final Approval Project Bellerophon

  5. Preliminary Analysis 20,480 possible combinations for each payload! Launch Methods Ground Aircraft Balloon Railgun Conventional Gun Materials Aluminum Composite Steel Titanium Propellants Cyrogenic LOX / LH2 H2O2 / RP-1 Storable H2O2 / HTPB Hybrid Solid AP / Al / HTPB 5,616 Project Bellerophon

  6. Model Analysis Payload / Launch Description Staging Details 5,616 possible combinations for each payload! • Hybrid Prop • Titanium MA - SS - DA - HT Stage 2 Stage 3 Stage 1 • Medium Payload (1 kg) • Aircraft Launch • SolidProp • Aluminum • Storable Prop • Steel 3 Project Bellerophon

  7. Final Design Launch Vehicle Inert Mass Refined Vehicle Requirements Subsystems Propulsion Final Vehicle Aerothermal Avionics D & C Propulsion Structures Trajectory Trajectory r = 50 m Rough Vehicle Project Bellerophon

  8. 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 Project Bellerophon

  9. Nominal Trajectory Project Bellerophon

  10. D&C Controlled Trajectory Project Bellerophon

  11. Final Design Launch Vehicle Inert Mass Refined Vehicle Requirements Subsystems Propulsion Vehicle ready for Monte Carlo Controlled Trajectory Final Vehicle Aerothermal Avionics D & C Propulsion Structures Trajectory Nominal Trajectory D & C Trajectory r = 50 m Rough Vehicle Project Bellerophon

  12. Accounting for ErrorsMonte Carlo Analysis 1kg Launch Vehicle: Perigee Altitude Histogram Standard Dev = 16 km Mean = 368 km Requirement Perigee > 300 km minert mprop D&C Monte Carlo Simulator Computes perigee Frequency m Perigee (km) Perigee (km) . . . Ideal Vehicle Manufacturing Uncertainties + = Actual Vehicle 10,000 Xs Project Bellerophon

  13. 1 kg Failure Low on gas Heavy Poor engine performance Project Bellerophon

  14. Monte Carlo Trajectories Project Bellerophon

  15. Monte Carlo Analysis Results Success Rate 99.99% 99.99% 100.00% Project Bellerophon

  16. Final Vehicle Specifics Payload: 200 g Length: 10.18 m Diameter: 1.29 m Payload: 1 kg Length: 8.65 m Diameter: 1.13 m Payload: 5 kg Length: 14.25 m Diameter: 1.84 m Project Bellerophon

  17. Tour of Vehicle1 kg payload Helium Balloon Gondola Launch Vehicle Project Bellerophon

  18. Tour of Vehicle1 kg payload Stage 3 Stage 2 Stage 1 9 m Project Bellerophon

  19. Tour of Vehicle1 kg payload 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 Project Bellerophon

  20. Tour of Vehicle1 kg payload Stage 2 Inter-stage Skirt 2nd Stage Avionics Liquid Injection Thrust Vector Control (LITVC) Tank (H202) mstage2 is 26% of GLOM Project Bellerophon

  21. Tour of Vehicle1 kg payload Stage 1 Pressurant (N2) Inter-tank Coupler Oxidizer Tank (H202) Fuel Tank (HTPB) mstage1 is 70% of GLOM Project Bellerophon

  22. Tour of Vehicle1 kg payload Project Bellerophon

  23. Mission Timeline1 kg payload 3rd Stage Separation h = 381 km T+ = 515.3 s 2nd Stage Separation h= 257 km T+ = 320.0 s Nose Cone Jettison h = 90.00 km 1st Stage Separation h= 87.4 km T+ = 140.8 s Launch h = 30 km T+ = 0s 1 hr 35 min balloon ascent + 8 min 35 sec launch vehicle ascent = 1.7 hour total mission Project Bellerophon

  24. Catastrophic RiskHistorical Analysis Project Bellerophon

  25. Catastrophic RiskHistorical Analysis Pegasus Project Bellerophon

  26. Cost Model • Can we use existing prices from large launch vehicles to help find ours? Project Bellerophon

  27. Cost Model Payload: 200 g $ 3.6 M Payload: 1 kg $ 3.2 M Payload: 5 kg $ 4.7 M • Build and launch cost includes: - Material - Engine - Handling - Labor - Propellant - Avionics - Tank - Balloon - Gondola Project Bellerophon

  28. Conclusions • High altitude launch is a necessity • 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 • Small launch vehicle price : $ 4M Project Bellerophon

  29. Meet the Team Project Bellerophon

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