The document provides details of a rocket design project to launch a 100 lb satellite into a 165 km sun synchronous orbit from Alaska. It summarizes the mission objectives, requirements, and initial conditions. It then describes the liquid hydrogen/oxygen propulsion system and parameters for the 3 stages. Other considerations like additional mass costs and tank sizing are discussed. The overall performance metrics and efficiencies are presented. It concludes that the design is initially feasible but storage tank sizing exceeds the maximum allowed mass.

1. Final Detail Briefings
Team Rocket:
Airik Phillips, Andrew Bothun, Chengyu Perry Zhang, Daisy
Lazaro, Yijie Wang

2. Overview
• Mission Objectives
• Requirements and Initial Conditions
• Propulsion System
• Stage Parameters
• Considerations
• Overall Performance
• Conclusion

3. Mission Objectives
General:
• Design a rapid response launcher system for simple, light-
weight satellites
Specific:
• Put a single 100 lb. satellite into a sun synchronous 165 km
circular orbit launched from Poker Flat Research Range,
AK.

4. Requirements and Initial
Conditions

5. Req. and Int. Conds.
Mass of Payload: 100 lb.=45.36 kg
Orbit Height: 165 km
Burnout Velocity: 7.805 km/s
Longitude of Launch 65.1167⁰
Earth Rotation Velocity: 195.45 m/s
V Loss Due to Gravity: 1.775 km/s
Circular Orbit: E=0
Inclination: 70⁰
γ=51.697 ⁰ , ϕ=0 ⁰ , β=54.374 ⁰

6. Req. and Int. Conds.
𝚫V of burn out = (-4.838 km/s ŝ + 6.125 km/s Ê + 0 ẑ)
𝚫V Needed = (-4.838 km/s ŝ + 5.930 km/s Ê + 1.775 km/s ẑ)
𝚫V of Design = 8.656 km/s

7. Req. and Int. Conds.
γ=51.697 ⁰ , ϕ=0 ⁰ , β=54.374 ⁰
Launch Window Conditions
Two Launch Windows
• AN Opportunity:
• LWST = 90°+51.6967° = 141.6967° = 0927 hrs.
• DN Opportunity:
• LWST = 90°+180°-51.6967° = 218.3033° = 1433 hrs

8. Req. and Int. Conds.
Dumbkopff Charts
Finert of 0.35 and an
Isp of 460 s give the
lowest total masses

9. Propulsion Systems

10. Propulsion Systems
Liquid Rockets
H2/F2
• Isp = 440 s
• Dangerous to handle
• Hydrofluoric acid is a product of reaction
H2/O2
• Isp = 435 s
• Needs to be very cold for best reaction
• H2 and water are a product of reaction

11. Propulsion Systems
O2/H2 Properties

12. Stage Parameters

13. Stage Parameters
Stage 1
Total initial mass: 4080.04 kg
Payload mass: 811.99 kg
Inert stage mass: 1143.82 kg
H2 mass: 563.11 kg
• Volume: 7.948 m3
O2 mass: 1564.12 kg
• Volume: 1.368 m3
Burn time: 55.772 s
Burn out height: 112.075 km
Isp: 388.603 s
𝚫V = 3.0296 km/s
Avg thrust: 145.197 kN

14. Stage Parameters
Nozzle and Chamber Stage 1
At: 0.025 m2
• Dt: 0.0892 m
Ae:0.407 m2
• De: 0.360 m
Assume 𝜃𝑐𝑛 = 𝜃𝑐𝑐 = 15⁰
𝜂 𝑐: 98.3%
Lnozzle: 50.52 cm
𝐴 𝑐
𝐴 𝑡
: 3.402
Dc: 16.45 cm
L*: 1.02 m
Lc: 29.98 cm
Vc: 6375 cm3
ρ: 8500 kg/m3
σtu: 310 MPa
tc: 0.4964 mm
Factor of Safety: 2
tcactual: 0.993 mm
mc: 1.78 kg
mnozzle: 3.01 kg

15. Stage Parameters
Nozzle Schematics Stage 1
Expansion Ratio: 16.089 F/O Mixture Ratio: 5.6
Tc: 3375 K Pc: 3.45 MPa

16. Stage Parameters
Stage 2
Total initial mass: 811.99 kg
Payload mass: 161.6 kg
Inert stage mass: 227.64 kg
H2 mass: 104.08 kg
• Volume: 1.469 m3
O2 mass: 316.67 kg
• Volume: 0.279 m3
Burn time: 14.635 s
Burn out height: 146.750 km
Isp: 415.502 s
𝚫V = 3.0296 km/s
Avg thrust: 117.743 kN

17. Stage Parameters
Nozzle and Chamber Stage 2
At: 0.019 m2
• Dt: 0.0778 m
Ae:0.308 m2
• De: 0.313 m
Assume 𝜃𝑐𝑛 = 𝜃𝑐𝑐 = 15⁰
𝜂 𝑐: 98.3%
Lnozzle: 43.92 cm
𝐴 𝑐
𝐴 𝑡
: 3.587
Dc: 14.73 cm
L*: 1.02 m
Lc: 28.44 cm
Vc: 4845cm3
ρ: 8500 kg/m3
σtu: 310 MPa
tc: 0.4327 mm
Factor of Safety: 2
tcactual: 0.8655 mm
mc: 1.305 kg
mnozzle: 1.984 kg

18. Stage Parameters
Nozzle Schematics Stage 2
Expansion Ratio: 16.089 F/O Mixture Ratio: 5.6
Tc: 3375 K Pc: 3.45 MPa

19. Stage Parameters
Stage 3
Total initial mass: 161.6 kg
Payload mass: 45.36 kg
Inert stage mass: 40.684 kg
H2 mass: 18.602 kg
• Volume: 0.263 m3
O2 mass: 56.954 kg
• Volume: 0.0499 m3
Burn time: 17.727 s
Burn out height: 165.496 km
Isp: 415.502 s
𝚫V = 2.5966 km/s
Avg thrust: 17.373 kN

20. Stage Parameters
Nozzle and Chamber Stage 3
At: 0.003 m2
• Dt: 0.0309 m
Ae:0.045 m2
• De: 0.12 m
Assume 𝜃𝑐𝑛 = 𝜃𝑐𝑐 = 15⁰
𝜂 𝑐: 98.3%
Lnozzle: 16.57 cm
𝐴 𝑐
𝐴 𝑡
: 5.315
Dc: 7.12 cm
L*: 1.02 m
Lc: 19.19 cm
Vc: 765cm3
ρ: 8500 kg/m3
σtu: 310 MPa
tc: 0.172 mm
Factor of Safety: 4
tcactual: 0.6878 mm
mc: 0.322 kg
mnozzle: 0.229 kg

21. Stage Parameters
Nozzle Schematics Stage 3
Expansion Ratio: 16.089 F/O Mixture Ratio: 5.6
Tc: 3375 K Pc: 3.45 MPa

22. Other Considerations

23. Other Considerations
Other Mass Costs:
• Exterior shell - sized for each stage
• Stage separators - sized for each stage
• Fuel/Oxidizer tanks - sized for each stage
• Fuel/Oxidizer coolers - consistent through the stages
• Transport conduits - consistent through the stages
To Fulfill these Other Considerations:
• Stage 1 is left with 1139.03 kg of inert mass
• Stage 2 is left with 222.76 kg of inert mass
• Stage 3 is left with 35.89 kg of inert mass

24. Other Considerations
Tanking Sizing
Stage 1
H2 @ 101.325 MPa: 7.948 m3
• Cylindrical R: 0.75 m, L: 4.498 m
• Mass w/ Graphite: 5578.58 kg
O2 @ 101.325 MPa: 1.368 m3
• Sphere R: 0.6887 m
• Mass w/ Graphite: 720.29 kg
Stage 2
H2 @ 101.325 MPa: 1.469 m3
• Cylindrical R: 0.7052 m
• Mass w/ Graphite: 775.21 kg
O2 @ 101.325 MPa: 0.279 m3
• Sphere R: 0.4054 m
• Mass w/ Graphite: 146.91 kg
Stage 3
101.325 MPa: 0.263 m3
• Sphere R: 0.3975 m
• Mass w/ Graphite: 138.52 kg
O2 @ 101.325 MPa: 0.0499 m3
• Sphere R: 0.2284 m
• Mass w/ Graphite: 26.44 kg

25. Other Considerations
Injectors:
• Shower Head
• Self Impinging Doublet
• Cross Impinging
• Centripetal/Swirling
• Pintle Injector

26. Overall Performance

27. Overall Performances
Final Altitude: 165.496 km
Final Velocity: 8.656 km/s
Nozzle Efficiency: 98.3%
Combustion Efficiency: 98.2%
Overall Efficiency: 96.53%

28. Conclusion

29. Conclusion
Problem:
On a first pass the rocket design looks feasible, but upon sizing
of fuel and oxidizer storage the maximum mass allowed was
greatly surpassed on all stages.
Solution:
This could potentially be mitigated by condensing the fuel and
oxidizer for smaller tanks.

30. END