1 / 9

More Attitude Control Thruster Options

More Attitude Control Thruster Options. Brittany Waletzko Translunar /OTV Phase Week 7. The Scenario. Need thrusters to despin / desaturate reaction wheels during TLI Must be capable of impulsive Δ V ~50 m/s

ranae
Download Presentation

More Attitude Control Thruster Options

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. More Attitude Control Thruster Options Brittany Waletzko Translunar/OTV Phase Week 7 Brittany Waletzko - ATT

  2. The Scenario BrittanyWaletzko- ATT Need thrusters to despin/desaturate reaction wheels during TLI Must be capable of impulsive ΔV ~50 m/s Already using Electric Propulsion for main engine  utilize power for attitude control? <1>

  3. Bottom-Line Figures (hydrazine monopropellant system uses <1W) Bottom line: Neither of these options is likely to be the best option based on cost, power consumption, and complexity Future Work: Solidifying supporting hardware mass/power/cost figures, OTV integration work BrittanyWaletzko- ATT <2>

  4. Questions? BrittanyWaletzko- ATT <3>

  5. Thruster Locations and Thrust Direction Vectors Thruster placement planned with assistance from Brian Erson Brittany Waletzko - ATT <4>

  6. How They Work Source: TU Delft website Brittany Waletzko - ATT <5>

  7. Further Comments Brittany Waletzko - ATT <6>

  8. Updated System Estimates 8 thrusters may be too redundant; 4 already allows for the loss of one thruster, 8 makes the entire system redundant  reliability analysis needed Brittany Waletzko - ATT <7>

  9. Primary References Monopropellant Hydrazine Thrusters. Astrium Space Propulsion. 21 Jan 2009. <http://cs.astrium.eads.net/sp/SpacecraftPropulsion/MonopropellantThrusters.html> Rocket Research Corporation. "Final Report for Monopropellant Hydrazine Thruster System," 1965. http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19670030394_1967030394.pdf Eric Wernimont, Ph.D. General Kinetics, Inc.: Huntington Beach, CA. Email Correspondence 7 Feb - 10 Feb 2009. <http://www.marotta.com/DataSheets/MV100series.htm> <http://www.circlesealcontrols.com/products/atkomatic_valves/pdf/cscatkoc_2007-10_lo.pdf> “Electrothermal Hydrazine Data” and many other links <http://www.lr.tudelft.nl/live/pagina.jsp?id=6cf1d7c6-dd9a-432b-b40e-02f4f8ed0d0d&lang=en> Sellers, “Investigation Into Cost-Effective Propulsion System Options for Small Satellites.” Journal of Reducing Space Mission Cost, 1998. Pinero and Bowers. “Power Electronics for a Miniaturized Arcjet.” 32nd Joint Propulsion Conference and Exhibit,” 1996. BrittanyWaletzko- ATT <8>

More Related