Download or read book Modelling and Design of Inductively Coupled Radio Frequency Gridded Ion Thrusters with an Application to Ion Beam Shepherd Type Space Missions written by Mantas Dobkevicius and published by . This book was released on 2017 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Numerical Modelling and Optimisation of Radio frequency Ion Thrusters written by Martin Felix Closs and published by Herbert Utz Verlag. This book was released on 2002 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Numerical Modelling of a Radio frequency Micro Ion Thruster written by Michael Meng-Tsuan Tsay and published by . This book was released on 2006 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt: A simple performance model is developed for an inductively-coupled radio-frequency micro ion thruster. Methods of particle and energy balance are utilized for modeling the chamber plasma discharge. A transformer model is incorporated in the equations of energy balance for investigating the effect of plasma on the primary circuit and for calculating the absorbed power by the plasma. A simple and one-dimensional ion extraction model is developed based on experimental observation and the result is validated with experimental data. Performance of the RF micro ion thruster is satisfactory with thrust and specific impulse of approximately 2 mN and 2000 seconds, respectively. Comparison is made with a miniature bombardment-type ion thruster, and the RF ion thruster is found to be more efficient when the coupling efficiency is above 80%. Optimization in driving frequency increases power absorption and ionization fraction tremendously. It has a positive but limited effect on propulsive performance as the ion beam current is space-charge limited.
Download or read book Development of a Miniature Radio Frequency Ion Thruster with Inductively Coupled Plasma ICP Source for CubeSat Propulsion written by and published by . This book was released on 2021 with total page 125 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Fundamentals of Electric Propulsion written by Dan M. Goebel and published by John Wiley & Sons. This book was released on 2008-12-22 with total page 528 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Analysis of a Miniature Radio Frequency Ion Thruster with an Inductively Coupled Plasma Source written by Peter Paul Bumbarger and published by . This book was released on 2013 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development of an Ion Thruster and Power Processor for New Millennium s Deep Space 1 Mission written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-02 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Solar Electric Propulsion Technology Applications Readiness Program (NSTAR) will provide a single-string primary propulsion system to NASA's New Millennium Deep Space 1 Mission which will perform comet and asteroid flybys in the years 1999 and 2000. The propulsion system includes a 30-cm diameter ion thruster, a xenon feed system, a power processing unit, and a digital control and interface unit. A total of four engineering model ion thrusters, three breadboard power processors, and a controller have been built, integrated, and tested. An extensive set of development tests has been completed along with thruster design verification tests of 2000 h and 1000 h. An 8000 h Life Demonstration Test is ongoing and has successfully demonstrated more than 6000 h of operation. In situ measurements of accelerator grid wear are consistent with grid lifetimes well in excess of the 12,000 h qualification test requirement. Flight hardware is now being assembled in preparation for integration, functional, and acceptance tests. Sovey, James S. and Hamley, John A. and Haag, Thomas W. and Patterson, Michael J. and Pencil, Eric J. and Peterson, Todd T. and Pinero, Luis R. and Power, John L. and Rawlin, Vincent K. and Sarmiento, Charles J. and Anderson, John R. and Bond, Thomas A. and Cardwell, G. I. and Christensen, Jon A. Glenn Research Center; Jet Propulsion Laboratory RTOP 242-70-01...
Download or read book Microwave Ecr Ion Thruster Development Activities at NASA Glenn Research Center written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-20 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Outer solar system missions will have propulsion system lifetime requirements well in excess of that which can be satisfied by ion thrusters utilizing conventional hollow cathode technology. To satisfy such mission requirements, other technologies must be investigated. One possible approach is to utilize electrodeless plasma production schemes. Such an approach has seen low power application less than 1 kW on earth-space spacecraft such as ARTEMIS which uses the rf thruster the RIT 10 and deep space missions such as MUSES-C which will use a microwave ion thruster. Microwave and rf thruster technologies are compared. A microwave-based ion thruster is investigated for potential high power ion thruster systems requiring very long lifetimes. Foster, John E. and Patterson, Michael J. Glenn Research Center NASA/TM-2002-211877, NAS 1.15:211877, E-13559, AIAA Paper 2002-3837
Download or read book Design and Fabrication of a Flight Model 2 3kW Ion Thruster for the Deep Space l Mission written by Jon A. Christensen and published by . This book was released on 1998 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Thermal Environmental Testing of NSTAR Engineering Model Ion Thrusters written by and published by . This book was released on 1999 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development Status of the NASA 30 cm Ion Thruster and Power Processor written by and published by . This book was released on 1994 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Next Ion Thruster Thermal Model written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-13 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: As the NEXT ion thruster progresses towards higher technology readiness, it is necessary to develop the tools that will support its implementation into flight programs. An ion thruster thermal model has been developed for the latest prototype model design to aid in predicting thruster temperatures for various missions. This model is comprised of two parts. The first part predicts the heating from the discharge plasma for various throttling points based on a discharge chamber plasma model. This model shows, as expected, that the internal heating is strongly correlated with the discharge power. Typically, the internal plasma heating increases with beam current and decreases slightly with beam voltage. The second is a model based on a finite difference thermal code used to predict the thruster temperatures. Both parts of the model will be described in this paper. This model has been correlated with a thermal development test on the NEXT Prototype Model 1 thruster with most predicted component temperatures within 5 to 10 C of test temperatures. The model indicates that heating, and hence current collection, is not based purely on the footprint of the magnet rings, but follows a 0.1:1:2:1 ratio for the cathode-to-conical-to-cylindrical-to-front magnet rings. This thermal model has also been used to predict the temperatures during the worst case mission profile that is anticipated for the thruster. The model predicts ample thermal margin for all of its components except the external cable harness under the hottest anticipated mission scenario. The external cable harness will be re-rated or replaced to meet the predicted environment. VanNoord, Jonathan L. Glenn Research Center NASA/TM-2010-216919, AIAA Paper 2007-5218, E-17495
Download or read book Ion Thruster Development at NASA Lewis Research Center written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-12-29 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Recent ion propulsion technology efforts at NASA's Lewis Research Center including development of kW-class xenon ion thrusters, high power xenon and krypton ion thrusters, and power processors are reviewed. Thruster physical characteristics, performance data, life projections, and power processor component technology are summarized. The ion propulsion technology program is structured to address a broad set of mission applications from satellite stationkeeping and repositioning to primary propulsion using solar or nuclear power systems. Sovey, James S. and Hamley, John A. and Patterson, Michael J. and Rawlin, Vincent K. and Sarver-Verhey, Timothy R. Glenn Research Center NASA-TM-105983, E-7507, NAS 1.15:105983 RTOP 506-42-31...
Download or read book Ion Engine and Hall Thruster Development at the NASA Glenn Research Center written by and published by . This book was released on 2002 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Vacuum Arc Ion Thruster for Space Propulsion written by and published by . This book was released on 1998 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Phase I project has demonstrated the feasibility of a 500 W vacuum arc ion thruster (VAIT) that is very different from present Xe ion thrusters that are in production for space missions. The VAIT does not require storage and feed of gases, reducing the parts count considerably. The VAIT produces a highly ionized plasma with minimal neutral build up in the grids, potentially making the grid lifetime longer and potentially allowing smaller grid spacing to be used. The VAIT has been shown (in related research over two decades) to produce plasmas (hence directed ion beams) of dozens of heavy ions such as Ba, La, Ce, Pr, Nd, Sm, Gd, Dy, Ho, Er, Tm, Yb, H(Ta, W, Ir, Pt, Au, Pb, Bi, Th and U. This wide range of possible ions provides great flexibility to the VAIT, allowing us to tailor different ion beams (with different thrust, specific impulse levels) to different missions. Ion streaming velocities of 5 x 104 rn/s were measured using Time-of-Flight (TOF) methods, which imply a thrust level of 0.13 N.
Download or read book Microwave ECR Ion Thruster Development Activities at NASA Glenn Research Center written by and published by . This book was released on 2002 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High Power Ecr Ion Thruster Discharge Characterization written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Electron cyclotron resonance (ECR) based ion thrusters with carbon based ion optics can potentially satisfy lifetime requirements for long duration missions (approximately 10 years) because grid erosion and cathode insert depletion issues are virtually eliminated. Though the ECR plasma discharge has been found to typically operate at slightly higher discharge losses than conventional DC ion thrusters (for high total thruster power applications), the discharge power fraction is small (less than 1 percent at 25 kW). In this regard, the benefits of increased life, low discharge plasma potentials, and reduced complexity are welcome tradeoffs for the associated discharge efficiency decrease. Presented here are results from discharge characterization of a large area ECR plasma source for gridded ion thruster applications. These measurements included load matching efficacy, bulk plasma properties via Langmuir probe, and plasma uniformity as measured using current probes distributed at the exit plane. A high degree of plasma uniformity was observed (flatness greater than 0.9). Additionally, charge state composition was qualitatively evaluated using emission spectroscopy. Plasma induced emission was dominated by xenon ion lines. No doubly charged xenon ions were detected.Foster, John E. and Kamhawi, Hani and Haag, Thomas and Carpenter, Christian and Williams, George W.Glenn Research CenterELECTRON CYCLOTRON RESONANCE; ION ENGINES; PLASMA JETS; CHARACTERIZATION; ION OPTICS; PLASMA POTENTIALS; XENON; CHARGED PARTICLES; MICROWAVES; CURRENT DENSITY; ELECTRON ENERGY; ELECTROSTATIC PROBES
