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Week 4 Presentation Thursday, Feb 5, 2009

Orbit Transfer Vehicle Electric Propulsion System: High-Level Analysis and Component Specifications. Week 4 Presentation Thursday, Feb 5, 2009. 1. Electric Propulsion System Analysis. Determine a performance range for mission feasibility Choose a thruster for the X1 design

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Week 4 Presentation Thursday, Feb 5, 2009

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  1. Orbit Transfer Vehicle Electric Propulsion System: High-Level Analysis and Component Specifications Week 4 Presentation Thursday, Feb 5, 2009 Brad Appel Propulsion Group 1

  2. Electric Propulsion System Analysis Brad Appel Propulsion Group Determine a performance range for mission feasibility Choose a thruster for the X1 design Hall thruster BHT-1500 from Busek will satisfy the requirements EP system is in general modular  good for scaling 2

  3. Propulsion System Components Xe Tank FVV Pressure Regulator From Power Distribution Unit FVV Mass Flow Controller Power Processing Unit Hall Thruster Brad Appel Propulsion Group 3

  4. Backup Slides: EP Performance Comparison Brad Appel Propulsion Group 4

  5. Backup Slides: EP Performance Comparison Brad Appel Propulsion Group 5

  6. Backup Slides: Fundamental Equations Brad Appel Propulsion Group Ideal rocket equation for propellant mass: Specific power of overall spacecraft: Mass of spherical tank: 6

  7. Backup Slides: Other Information Brad Appel Propulsion Group • Density Supercritical Xe: 1673 kg/m3 • Cost Xe: $ 5.00 / liter* • Assumptions for sizing code: • Delta V = 8 km/s • S/C specific power = 65 W/kg • Payload = 250 kg *Source: Defense Energy Support Center – FY 2009 Data 7

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