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### Lunar Descent: Hybrid Propulsion System Mass Breakdown and Thermodynamic Analysis ###

This presentation by Saad Tanvir reviews the hybrid propulsion system for lunar descent, analyzing mass breakdown for three payload cases (100g, 10kg, and arbitrary). It discusses propellant and inert mass specifics, showing total propulsion system mass for each case. Thermodynamic analysis addresses tank operating conditions and heat transfer requirements during descent. It also explores alternative chemical propulsion systems, highlighting significant mass savings achievable with electric propulsion technology. The presentation provides a comprehensive overview of system parameters and performance. ###

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### Lunar Descent: Hybrid Propulsion System Mass Breakdown and Thermodynamic Analysis ###

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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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