Week 13 Presentation Thursday, April 9 th, 2009 Saad Tanvir Propulsion Group 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

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

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

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

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

Propellant Tank Specifications Saad Tanvir Propulsion Group 6

Pressurant Tank Specifications Saad Tanvir Propulsion Group 7

Saad Tanvir Propulsion Group 8 Hydrogen Peroxide Tanks - Thermodynamic Analysis Assumptions: Tank operating Temperature = 283 K (50 F) Surrounding Temperature = 2.73 K Power Required ~ 35 W ΔT = K Q: Rate of Heat transfer [W] A: Area of Cross section of the tank [ m 2 ] k: Thermal Conductivity [0.044 W/mK] ΔT: Temperature Difference [K] t: Thickness of the blanket [200 mm]

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

Propellant Tank – Operating Pressure P chamber = 2.07 MPa ∆P dynamic = ½ v 2 ~ MPa ∆P feed (Upper bound) ~ 0.05 MPa ∆P cool ~ 0.15pc = 0.31 MPa ∆P injector ~ 0.3pc = 0.62 Mpa P tank ~ 3.07 MPa Saad Tanvir Propulsion Group 10

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