by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va .
Written in English
|Statement||David Manzella ... [et al.].|
|Series||NASA technical memorandum -- 107326.|
|Contributions||Manzella, David., United States. National Aeronautics and Space Administration.|
|The Physical Object|
Get this from a library! Evaluation of low power hall thruster propulsion. [David H Manzella; Lewis Research Center,; United States. National Aeronautics and Space Administration,]. Evaluation of low power hall thruster propulsion (OCoLC) Material Type: Government publication, National government publication, Internet resource: Document Type: Book, Internet Resource: All Authors / Contributors: David H Manzella; United States. National Aeronautics and . limiting the maximum power of a single Hall thruster. Arrays of lower power Hall thruster are an alternate strategy for obtaining high power Hall thruster propulsion systems, however neither this approach nor multi-channel Hall thrusters are considered in this analysis. Both of these approaches may offer certain advantages, but theyCited by: The second design iteration in the development of a low-power magnetically shielded Hall thruster was the MaSMi Magnetic field measurements confirmed that a symmetric and fully shielded magnetic field topology was generated by this device across a wide range of possible operating conditions.
An ion thruster or ion drive is a form of electric propulsion used for spacecraft tangoloji.com creates thrust by accelerating ions using electricity.. An ion thruster ionizes a neutral gas by extracting some electrons out of atoms, creating a cloud of positive tangoloji.com ion thrusters rely mainly on electrostatics as ions are accelerated by the Coulomb force along an electric field. Descanso, Deep Space Communications and Navigation Systems Fundamentals of Electric Propulsion - Ion and Hall Thrusters JPL DESCANSO - Deep Space Communications and Navigation Center of . This use of the PPSG, starting on September 28, , was the first use of a Hall thruster outside geosynchronous earth orbit (GEO). Like most Hall thruster propulsion systems used in commercial applications, the Hall thruster on SMART-1 could be throttled over a . Force Transfer in Ion and Hall Thrusters The propellant ionized in ion and Hall thrusters is accelerated by the application of electric fields. However, the mechanism for transferring the thrust from the ion motion to the thruster body, and thereby the spacecraft, is different for ion thrusters and Hall thrusters.
Request PDF | Performance Evaluation of the T Low-Power Hall Current Thruster | The performance of the Aerojet Rocketdyne T low-power Hall current thruster (HCT) is experimentally. The exact power level that qualifies as “high-power” in Hall thrusters is a shifting target. In the s anything over a kilowatt would have been considered high power, yet with the advent of thrusters like the kW NASA M and more recently nested thrusters like the X2, the bar has shifted and now it would be fair to say that “high-power” begins in the kW range, if not higher. Carl Book, Mitchell Walker, “Effect of Anode Temperature on Hall Effect Thruster Performance,” Journal of Propulsion and Power, Volume 26, Number 5, September-October , pp. Journal of Propulsion and Power; Journal of Spacecraft and Rockets; Journal of Thermophysics and Heat Transfer; Browse All Journals; Browse All Virtual Collections; Books. AIAA Education Series; Library of Flight; Progress in Astronautics and Aeronautics; The Aerospace Press; Browse All Books; Meeting Papers; Standards; Other Publications.