1. Project Bellerophon0 Backup Slides

2. Project Bellerophon1 Trajectory - Steering Law Function of time Defines the orientation of the launch vehicle bb brbr  2e  3e  1e

3. Project Bellerophon2 Model Analysis 5,616 possible combinations for each payload …… Launch Vehicle Stage 1Stage 2Stage 3Launch Method MaterialPropellant Ground Aircraft Balloon Cryogenic Storable Hybrid Solid Aluminum Steel Titanium

4. Project Bellerophon3 Historical Catastrophic Risk Pegasus Our Vehicles

5. Project Bellerophon4 Aircraft Steering Law – Parameter Optimization tb2 25% tb2 Ψ mid1 =5 deg Ψ mid2 =0 deg Ψ e2 To be optimized t climb 1st Stage: tangent law 2nd Stage: 3 linear sections

6. Project Bellerophon5 Definition of Eccentricity e = c/a a: Semi-Major Axis b: Semi-Minor Axis c: center to focus

7. Project Bellerophon6 Risk Assessment - Non-Catastrophic Failure Monte Carlo Histograms - 200g Payload 200g Periapsis Altitude Histogram; std = 21.803 km, mean = 437.44 km 200g Eccentricity Histogram; std = 0.0467, mean = 0.438

8. Project Bellerophon7 Risk Assessment - Non-Catastrophic Failure Monte Carlo Histograms - 1kg Payload 1kg Periapsis Altitude Histogram; std = 15.774 km, mean = 367.727 km 1kg Eccentricity Histogram; std = 0.041094, mean = 0.173289

9. Project Bellerophon8 Risk Assessment - Non-Catastrophic Failure Monte Carlo Histograms - 5kg Payload 5kg Periapsis Altitude Histogram; std = 20.215 km, mean = 516.546 km 5kg Eccentricity Histogram; std = 0.050, mean = 0.445

10. Project Bellerophon9 Performance Characteristics - 200 g Payload

11. Project Bellerophon10 Performance Characteristics - 1 kg Payload

12. Project Bellerophon11 Performance Characteristics - 5 kg Payload

13. Project Bellerophon12 200 g Failure

14. Project Bellerophon13 1 kg Failure

15. Project Bellerophon14 John Tsohas’ Table 200 g Payload Stage m prop /(m i +m prop )  V/stage m stage /GLOMIsp 180.7%3,808 m/s (32%)70.11%352.2s 278.69%4,358 m/s (37%)27.87%309.3s 371.57%3,740 m/s (31%)2.02%309.3s 1 kg Payload 177.11%3,818 m/s (39%)70.48%352.2s 274.3%3,211 m/s (32%)25.97%309.3s 372.7%2,864 m/s (29%)3.55%309.3s 5 kg Payload 183%3,211 m/s (32%)78.95%352.2s 279.44% 3,963 m/s (39%)20.2%309.3s 371.76%2,978 m/s (29%)0.85%309.3s Saturn V Stagem prop /(m i +m prop )  V/stage m stage /GLOMIsp 194.09%75.83%265-310s 292.04%16.28%421s 344.81%7.89%421s Ariane 5 ECA 186.28%71.81%250-275s 293.17%24.00%434s 3 44.31%4.19%446s

16. Project Bellerophon15 John Tsohas’ Table II Payload Prop mass fraction – 3 rd stagePayload mass fractionPayload mass fraction (3rd Stage) 200 g0.00380.0077%0.38% 1 kg0.0160.05733%1.64% 5 kg0.09350.07949%9.35% VehicleProp mass fraction – 3 rd stagePayload mass fractionPayload mass fraction (3rd Stage) Saturn V0.03543.91%49.6% Ariane 40.01862.06%1.64%