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Optimizing Translunar Orbit Transfer Vehicle: Hall Thruster Comparisons and Sizing Updates

This presentation outlines recent developments in the sizing and optimization of the Translunar Orbit Transfer Vehicle (OTV). Presented by Brad Appel from the Propulsion Group, it covers various factors affecting mission parameters, including time of flight and thruster performance. Key comparisons of Hall thruster systems are highlighted, showcasing updated OTV specifications and optimal impulse levels. Additionally, the presentation discusses scaling the design based on payload mass and offers insights into supercritical xenon density and associated costs. This collaborative effort with Mission Ops aims to improve mission efficiency and reduce costs.

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Optimizing Translunar Orbit Transfer Vehicle: Hall Thruster Comparisons and Sizing Updates

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  1. Translunar Orbit Transfer Vehicle (OTV): Updates in Sizing and OptimizationMass Comparisons of Available Hall Thrusters Week 6 Presentation Thursday, Feb 19, 2009 Brad Appel Propulsion Group 1

  2. OTV Sizing: Joint Effort with Mission Ops Group Brad Appel Propulsion Group Trading between many parameters: Time of flight, thrust, specific impulse, mass flow rate, power, propellant mass, and cost Currently a TOF of 351 days provides the cheapest mission, but the story drastically changes if the solar panel price varies 2

  3. Comparison of Different Hall Thruster Systems Updated OTV Numbers Based on BHT-1500: Brad Appel Propulsion Group 3

  4. Backup Slides: Optimum Isp for our Mission Note: Curve not steep: Can tolerate 1800-4250 s with only 6% loss Brad Appel Propulsion Group 4

  5. Backup Slides: Various Empirical Curves Brad Appel Propulsion Group 5

  6. Backup Slides: OTV Scaling Up Scaled up the GLXP design according to payload mass fraction and specific power, normalized to the maximum payload capacity of each launch vehicle. Worked with Power Group. Brad Appel Propulsion Group 6

  7. Backup Slides: Other Information Brad Appel Propulsion Group • Density Supercritical Xe: 1673 kg/m3 (P = 150 bar) • Cost Xe: $ 5.00 / liter* OR $1200 / kg** • Assumptions for sizing code: • Payload = 290 kg  Probably larger now (~315) • OTV Structure/Thermal Mass = 120 kg • Launch cost to LEO 400 km: $5000 / kg (roughly extrapolated from $3400 / kg to 200 km) *Source: Defense Energy Support Center – FY 2009 Data **Source: www.chemicool.com 7

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