Author: John E. FosterPublisher:
ISBN:
Category : Electrons
Languages : en
Pages : 13
Book Description
Ion and electron transport in an NSTAR-derivative ion thruster
Author: John E. FosterPublisher:
ISBN:
Category : Electrons
Languages : en
Pages : 13
Book Description
Ion and Electron Transport in an Nstar-derivative Ion Thruster ... Nasa
Author: United States. National Aeronautics and Space AdministrationPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Ion and Electron Transport in an NSTAR-Derivative Ion Thruster
Author: Inter-Cusp Ion and Electron Transport in a Nstar-Derivative Ion Thruster
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781721261611
Category :
Languages : en
Pages : 32
Book Description
Diffusion of electrons and ions to anode surfaces between the magnetic cusps of a NASA Solar Electric Propulsion Technology Application Readiness ion thruster has been characterized. Ion flux measurements were made at the anode and at the screen grid electrode. The measurements indicated that the average ion current density at the anode and at the screen grid were approximately equal. Additionally, it was found that the electron flux to the anode between cusps is best described by the classical cross-field diffusion coefficient. Foster, John E. Glenn Research Center NASA/TM-2001-210669, NAS 1.15:210669, E-12535
INTER-CUSP ION AND ELECTRON TRANSPORT IN A NSTAR-DERIVATIVE ION THRUSTER... NASA/TM-2001-210669... AUG. 16, 2001
Author: Fundamentals of Electric Propulsion
Author: Dan M. GoebelPublisher: John Wiley & Sons
ISBN: 0470436263
Category : Technology & Engineering
Languages : en
Pages : 528
Book Description
Throughout most of the twentieth century, electric propulsion was considered the technology of the future. Now, the future has arrived. This important new book explains the fundamentals of electric propulsion for spacecraft and describes in detail the physics and characteristics of the two major electric thrusters in use today, ion and Hall thrusters. The authors provide an introduction to plasma physics in order to allow readers to understand the models and derivations used in determining electric thruster performance. They then go on to present detailed explanations of: Thruster principles Ion thruster plasma generators and accelerator grids Hollow cathodes Hall thrusters Ion and Hall thruster plumes Flight ion and Hall thrusters Based largely on research and development performed at the Jet Propulsion Laboratory (JPL) and complemented with scores of tables, figures, homework problems, and references, Fundamentals of Electric Propulsion: Ion and Hall Thrusters is an indispensable textbook for advanced undergraduate and graduate students who are preparing to enter the aerospace industry. It also serves as an equally valuable resource for professional engineers already at work in the field.
41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 10-13 July 2005, Tucson, Arizona: 05-4400 - 05-4449
Author: Ion Propulsion
Author: George Raymond BrewerPublisher: Gordon & Breach Publishing Group
ISBN:
Category : Science
Languages : en
Pages : 552
Book Description
Monthly Catalog of United States Government Publications
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 882
Book Description
Plume and Discharge Plasma Measurements of an Nstar-Type Ion Thruster
Author: National Aeronautics and Space Adm NasaPublisher: Independently Published
ISBN: 9781724087355
Category : Science
Languages : en
Pages : 40
Book Description
The success of the NASA Deep Space I spacecraft has demonstrated that ion propulsion is a viable option for deep space science missions. More aggressive missions such as Comet Nuclear Sample Return and Europa lander will require higher power, higher propellant throughput and longer thruster lifetime than the NASA Solar Electric Propulsion Technology Application Readiness (NSTAR) engine. Presented here are thruster plume and discharge plasma measurements of an NSTAR-type thruster operated from 0.5 kW to 5 kW. From Faraday plume sweeps, beam divergence was determined. From Langmuir probe plume measurements on centerline, low energy ion production on axis due to charge-exchange and direct ionization was assessed. Additionally, plume plasma potential measurements made on axis were used to determine the upper energy limits at which ions created on centerline could be radially accelerated. Wall probes flush-mounted to the thruster discharge chamber anode were used to assess plasma conditions. Langmuir probe measurements at the wall indicated significant differences in the electron temperature in the cylindrical and conical sections of the discharge chamber. Foster, John E and Soulas, George C. and Patterson, Michael J. Glenn Research Center NASA/TM-2000-210382, E-12438, AIAA Paper 2000-3812, NAS 1.15:210382