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Week 13 Presentation Thursday, April 9 th , 2009

Lunar Descent – Hybrid Propulsion System Propulsion System Inert Mass Finals -100 g Case - 10 kg Case - Arbitrary Case Lunar Descent – Thermodynamic Analysis on the Prop System Lunar Transfer – Chemical Alternative. Week 13 Presentation Thursday, April 9 th , 2009. 1.

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Week 13 Presentation Thursday, April 9 th , 2009

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  1. Lunar Descent – Hybrid Propulsion System Propulsion System Inert Mass Finals-100 g Case- 10 kg Case- Arbitrary Case Lunar Descent – Thermodynamic Analysis on the Prop System Lunar Transfer – Chemical Alternative Week 13 Presentation Thursday, April 9th, 2009 Saad Tanvir Propulsion Group 1

  2. Propulsion System Mass Finals 10 kg Payload case (Hopper) Propellant mass = 121.2 kg Propulsion System Inert mass = 45.4 kg Total Prop System Mass = 166.6 kg 100 g Payload case (Ball) Propellant mass = 78.2 kg Propulsion System Inert mass = 29.9 kg Total Prop System Mass = 108.1 kg Arbitrary Payload case (Falcon 9) Propellant mass = 1783.62 kg Propulsion System Inert mass = 227 kg Total Prop System Mass = 2010.62 kg Saad Tanvir Propulsion Group 2

  3. 100 g – Hybrid Propulsion System Mass Breakdown Saad Tanvir Propulsion Group 3

  4. 10 kg – Hybrid Propulsion System Mass Breakdown Saad Tanvir Propulsion Group 4

  5. Large payload – Hybrid Propulsion System Mass Breakdown Saad Tanvir Propulsion Group 5

  6. Propellant Tank Specifications Saad Tanvir Propulsion Group 6

  7. Pressurant Tank Specifications Saad Tanvir Propulsion Group 7

  8. Hydrogen Peroxide Tanks - Thermodynamic Analysis Assumptions: Tank operating Temperature = 283 K (50 F) Surrounding Temperature = 2.73 K Power Required ~ 35 W ΔT = 280.3 K Q: Rate of Heat transfer [W] A: Area of Cross section of the tank [m2] k: Thermal Conductivity [0.044 W/mK] ΔT: Temperature Difference [K] t: Thickness of the blanket [200 mm] Saad Tanvir Propulsion Group 8

  9. Lunar Descent – Thermodynamic Analysis on Prop System Temperature Drop < 5 K No power required to heat the propulsion system during Lunar Descent Saad Tanvir Propulsion Group 9

  10. Propellant Tank – Operating Pressure Pchamber = 2.07 MPa ∆Pdynamic = ½𝜌v2 ~ 0.072 MPa ∆Pfeed (Upper bound) ~ 0.05 MPa ∆Pcool ~ 0.15pc = 0.31 MPa ∆Pinjector ~ 0.3pc = 0.62 Mpa Ptank~ 3.07 MPa Saad Tanvir Propulsion Group 10

  11. Lunar Transfer: Chemical Alternative Significant mass savings using the Electric Propulsion system Saad Tanvir Propulsion Group 11

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