1 / 7

Electric Propulsion System Analysis for Orbit Transfer Vehicle: Component Specifications and Performance Assessment

This presentation by Brad Appel's Propulsion Group delves into high-level analysis and specifications of an electric propulsion system for orbit transfer vehicles, aiming to determine performance ranges for mission feasibility. The presentation highlights the selection of the Hall thruster BHT-1500 from Busek and emphasizes the modularity of the electric propulsion system for scalability. Key components discussed include the Xenon tank, pressure regulator, mass flow controller, and power processing unit. Backup slides provide insights on performance comparisons and fundamental equations, such as the ideal rocket equation and specific power of the spacecraft.

vala
Télécharger la présentation

Electric Propulsion System Analysis for Orbit Transfer Vehicle: Component Specifications and Performance Assessment

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  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

More Related