Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 368
Book Description
The cylindrical thruster differs significantly in its underlying physical mechanisms from the conventional annular Hall thruster. It features high ionization efficiency, quiet operation, ion acceleration in a large volume-to-surface ratio channel, and performance comparable with the state-of-the-art conventional Hall thrusters. Very significant plume narrowing, accompanied by the increase of the energetic ion fraction and improvement of ion focusing, led to 50%-60% increase of the thruster anode efficiency. These improvements were achieved by overrunning the discharge current in the magnetized thruster plasma.
Enhanced Performance of Cylindrical Hall Thrusters
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 368
Book Description
The cylindrical thruster differs significantly in its underlying physical mechanisms from the conventional annular Hall thruster. It features high ionization efficiency, quiet operation, ion acceleration in a large volume-to-surface ratio channel, and performance comparable with the state-of-the-art conventional Hall thrusters. Very significant plume narrowing, accompanied by the increase of the energetic ion fraction and improvement of ion focusing, led to 50%-60% increase of the thruster anode efficiency. These improvements were achieved by overrunning the discharge current in the magnetized thruster plasma.
Publisher:
ISBN:
Category :
Languages : en
Pages : 368
Book Description
The cylindrical thruster differs significantly in its underlying physical mechanisms from the conventional annular Hall thruster. It features high ionization efficiency, quiet operation, ion acceleration in a large volume-to-surface ratio channel, and performance comparable with the state-of-the-art conventional Hall thrusters. Very significant plume narrowing, accompanied by the increase of the energetic ion fraction and improvement of ion focusing, led to 50%-60% increase of the thruster anode efficiency. These improvements were achieved by overrunning the discharge current in the magnetized thruster plasma.
Optimization of Cylindrical Hall Thrusters
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
The cylindrical Hall thruster features high ionization efficiency, quiet operation, and ion acceleration in a large volume-to-surface ratio channel with performance comparable with the state-of-the-art annular Hall thrusters. These characteristics were demonstrated in low and medium power ranges. Optimization of miniaturized cylindrical thrusters led to performance improvements in the 50-200W input power range, including plume narrowing, increased thruster efficiency, reliable discharge initiation, and stable operation. __________________________________________________
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
The cylindrical Hall thruster features high ionization efficiency, quiet operation, and ion acceleration in a large volume-to-surface ratio channel with performance comparable with the state-of-the-art annular Hall thrusters. These characteristics were demonstrated in low and medium power ranges. Optimization of miniaturized cylindrical thrusters led to performance improvements in the 50-200W input power range, including plume narrowing, increased thruster efficiency, reliable discharge initiation, and stable operation. __________________________________________________
Fundamentals of Electric Propulsion
Author: Dan M. Goebel
Publisher: 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.
Publisher: 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.
Enhanced Ionization in the Cylindrical Hall Thruster
Author: A. I. Smirnov
Publisher:
ISBN:
Category : Electric propulsion
Languages : en
Pages : 33
Book Description
Publisher:
ISBN:
Category : Electric propulsion
Languages : en
Pages : 33
Book Description
Electric Field
Author: Mohsen Sheikholeslami Kandelousi
Publisher: BoD – Books on Demand
ISBN: 1789231868
Category : Technology & Engineering
Languages : en
Pages : 324
Book Description
In the present book, various applications of electric field are introduced in health and biology like treating cancer and cell sorting and in engineering and technological applications like enhancing the heat transfer, colloidal hydrodynamics and stability, and lithography. Electric field is defined as a force field arising from the electric charges. Depending on the nature of the material (the ability to polarize) and the inherent or attained surface charges, the response of the electric field varies.
Publisher: BoD – Books on Demand
ISBN: 1789231868
Category : Technology & Engineering
Languages : en
Pages : 324
Book Description
In the present book, various applications of electric field are introduced in health and biology like treating cancer and cell sorting and in engineering and technological applications like enhancing the heat transfer, colloidal hydrodynamics and stability, and lithography. Electric field is defined as a force field arising from the electric charges. Depending on the nature of the material (the ability to polarize) and the inherent or attained surface charges, the response of the electric field varies.
Performance Studies of Miniaturized Cylindrical and Annular Hall Thrusters
A Study of Cylindrical Hall Thruster for Low Power Space Applications
Cathode Effects in Cylindrical Hall Thrusters
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 584
Book Description
Stable operation of a cylindrical Hall thruster (CHT) has been achieved using a hot wire cathode, which functions as a controllable electron emission source. It is shown that as the electron emission from the cathode increases with wire heating, the discharge current increases, the plasma plume angle reduces, and the ion energy distribution function shifts toward higher energies. The observed effect of cathode electron emission on thruster parameters extends and clarifies performance improvements previously obtained for the overrun discharge current regime of the same type of thruster, but using a hollow cathode-neutralizer. Once thruster discharge current saturates with wire heating, further filament heating does not affect other discharge parameters. The saturated values of thruster discharge parameters can be further enhanced by optimal placement of the cathode wire with respect to the magnetic field.
Publisher:
ISBN:
Category :
Languages : en
Pages : 584
Book Description
Stable operation of a cylindrical Hall thruster (CHT) has been achieved using a hot wire cathode, which functions as a controllable electron emission source. It is shown that as the electron emission from the cathode increases with wire heating, the discharge current increases, the plasma plume angle reduces, and the ion energy distribution function shifts toward higher energies. The observed effect of cathode electron emission on thruster parameters extends and clarifies performance improvements previously obtained for the overrun discharge current regime of the same type of thruster, but using a hollow cathode-neutralizer. Once thruster discharge current saturates with wire heating, further filament heating does not affect other discharge parameters. The saturated values of thruster discharge parameters can be further enhanced by optimal placement of the cathode wire with respect to the magnetic field.
Development of a Miniature Low Power Cylindrical Hall Thruster for Microsatellites
Author: Carl Pigeon
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
To enable more advanced commercial microsatellite missions, a low power electric propulsion system was designed by the University of Toronto Space Flight Laboratory. A prototype cylindrical Hall thruster was first developed using electromagnets. The thruster's performance was evaluated over a range of 20-300 W. At the nominal 200 W operation, 6.2 mN of thrust with a specific impulse of 1139 s was measured with xenon propellant. Significant erosion of the thruster's discharge chamber wall was observed which limited its lifetime to 100 hours. Subsequently, a flight representative version of the thruster was developed. Permanent magnets were used to reduce the size, mass, and power consumption. Changes to the design were implemented to improve lifetime. Performance characterization and literature suggest that a reduction in performance is expected with the use of permanent magnets. Lastly, thermal vacuum and vibration tests were performed to bring the thruster to Technology Readiness Level 6.
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
To enable more advanced commercial microsatellite missions, a low power electric propulsion system was designed by the University of Toronto Space Flight Laboratory. A prototype cylindrical Hall thruster was first developed using electromagnets. The thruster's performance was evaluated over a range of 20-300 W. At the nominal 200 W operation, 6.2 mN of thrust with a specific impulse of 1139 s was measured with xenon propellant. Significant erosion of the thruster's discharge chamber wall was observed which limited its lifetime to 100 hours. Subsequently, a flight representative version of the thruster was developed. Permanent magnets were used to reduce the size, mass, and power consumption. Changes to the design were implemented to improve lifetime. Performance characterization and literature suggest that a reduction in performance is expected with the use of permanent magnets. Lastly, thermal vacuum and vibration tests were performed to bring the thruster to Technology Readiness Level 6.
Improvements to a Fully Kinetic Hall Thruster Simulation Code and Characterization of the Cylindrical Cusped Field Thruster
Author: Louis Boulanger (S.M.)
Publisher:
ISBN:
Category :
Languages : en
Pages : 99
Book Description
This thesis presents an effort towards a better understanding of the operation of miniaturized cylindrical Hall thrusters. This class of space propulsion devices has come under attention since the 1990s as a possible candidate for the propulsion of 100-1000 kg satellites. In first part, a fully kinetic simulation code developed at the MIT Space Propulsion Laboratory (SPL) is described and applied to two devices of interest: the Princeton Cylindrical Hall Thruster (CHT) and the MIT DCFT (Diverging Cusped-Field Thruster). During this simulation effort, limitations of PTpic were identified which prompted a major redesign, whose central idea is a better parallelization of the workload. At the same time, possible candidates to replace the leapfrog algorithm in the particle pusher have been studied. This work is described in Chapter 3. Finally, chapter 4 presents the results of the testing of the recently built Cylindrical Cusped-Field Thruster (CCFT) performed at the SPL.
Publisher:
ISBN:
Category :
Languages : en
Pages : 99
Book Description
This thesis presents an effort towards a better understanding of the operation of miniaturized cylindrical Hall thrusters. This class of space propulsion devices has come under attention since the 1990s as a possible candidate for the propulsion of 100-1000 kg satellites. In first part, a fully kinetic simulation code developed at the MIT Space Propulsion Laboratory (SPL) is described and applied to two devices of interest: the Princeton Cylindrical Hall Thruster (CHT) and the MIT DCFT (Diverging Cusped-Field Thruster). During this simulation effort, limitations of PTpic were identified which prompted a major redesign, whose central idea is a better parallelization of the workload. At the same time, possible candidates to replace the leapfrog algorithm in the particle pusher have been studied. This work is described in Chapter 3. Finally, chapter 4 presents the results of the testing of the recently built Cylindrical Cusped-Field Thruster (CCFT) performed at the SPL.