Download or read book Experimental and Computational Investigation of the Performance of a Micro ion Thruster written by Richard Wirz and published by . This book was released on 2002 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental and Computational Investigation of a RF Plasma Micro Thruster Preprint written by and published by . This book was released on 2008 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt: A prototype RF plasma micro-thruster has been investigated numerically and experimentally. The experimental results were obtained on a thrust stand capable of micro-Newton resolution. Thrust and mass flow (hence specific impulse) were measured for an argon propellant at mass flows ranging from 0.4 to 5.5 mg/sec. An increase to the cold gas thrust of up to 20% was observed for a discharge frequency of 100 MHz and an input power of 70 W. Propulsive efficiency was seen to increase both experimentally and numerically for increasing mass flow and decreasing discharge frequency.

Download or read book Fundamentals of Electric Propulsion written by Dan M. Goebel and published by John Wiley & Sons. This book was released on 2023-10-25 with total page 564 pages. Available in PDF, EPUB and Kindle. Book excerpt: Fundamentals of Electric Propulsion Understand the fundamental basis of spaceflight with this cutting-edge guide As spacecraft engineering continues to advance, so too do the propulsion methods by which human beings can seek out the stars. Ion thrusters and Hall thrusters have been the subject of considerable innovation in recent years, and spacecraft propulsion has never been more efficient. For professionals within and adjacent to spacecraft engineering, this is critical knowledge that can alter the future of space flight. Fundamentals of Electric Propulsion offers a thorough grounding in electric propulsion for spacecraft, particularly the features and mechanisms underlying Ion and Hall thrusters. Updated in the light of rapidly expanding knowledge, the second edition of this essential guide detailed coverage of thruster principles, plasma physics, and more. It reflects the historic output of the legendary Jet Propulsion Laboratory and promises to continue as a must-own volume for spacecraft engineering professionals. Readers of the second edition of Fundamentals of Electric Propulsion readers will also find: Extensive updates to chapters covering hollow cathodes and Hall thrusters, based on vigorous recent research New sections covering magnetic shielding, cathode plume instabilities, and more Figures and homework problems in each chapter to facilitate learning and retention Fundamentals of Electric Propulsion is an essential work for spacecraft engineers and researchers working in spacecraft propulsion and related fields, as well as graduate students in electric propulsion, aerospace science, and space science courses.

Download or read book 38th AIAA ASME SAE ASEE Joint Propulsion Conference Exhibit 02 3800 02 3849 written by and published by . This book was released on 2002 with total page 394 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental and Computational Studies of Electric Thruster Plasma Radiation Emission written by Murat Alp Çelik and published by . This book was released on 2007 with total page 239 pages. Available in PDF, EPUB and Kindle. Book excerpt: Electric thrusters are being developed for in-space propulsion needs of spacecraft as their higher specific impulse enables a significant reduction in the required propellant mass and allows longer duration missions. Over the last few decades many different electric propulsion concepts have been proposed and studied. In studying the electric thrusters, in order to improve the thruster performance as well as to understand the underlying physics of thruster's operation, various diagnostics methods were employed. As one unique method, emission spectroscopy provides a non-invasive, fast and economical diagnostic allowing also the ability to access hard to reach locations. In this study, emission spectroscopy is employed as a means to determine the trends in thruster operations as well as diagnosing the plasma parameters. This study presents the spectral measurement results of three different electric thrusters and plasma sources. First, the BHT-200 Hall thruster emission spectra measurements are presented for varying discharge voltage and for various regions of observation.

Download or read book 40th AIAA ASME SAE ASEE Joint Propulsion Conference Exhibit July 11 14 2004 Fort Lauderdale FL 04 4100 04 4149 written by and published by . This book was released on 2004 with total page 574 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 Experimental and Analytical Investigation of a Ring Cusp Ion Thruster written by Anita Sengupta and published by . This book was released on 2005 with total page 438 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Miniature Ion Thruster Characterization Via Discharge Plasma Plume and Mission Analyses written by Stephen Anthony Samples and published by . This book was released on 2021 with total page 169 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Miniature Xenon Ion (MiXI) thruster is a 3 cm DC ion thruster developed as low-power, high effciency micro-propulsion. This work focuses on the further development of the MiXI thruster into a viable propulsion technology and investigates the capabilities of MiXI as primary propulsion on CubeSat missions. First, we set the stage for this work by investigating the viability of high dV small spacecraft missions with high effciency, high impulse propulsion, and explore the sensitivities of mission capabilities to thruster properties and performance. One important conclusion is that in the CubeSat form-factor, high impulse micropropulsion enables high dV missions of several km/s with payloads of multiple U volume and multiple kg mass, however these parameters are very sensitive to thruster parameters such as Isp, total effciency, and neutralizer cathode performance. An ion thruster model is then developed to investigate key aspects of miniature DC ion thruster discharge and thruster performance using simplifed descriptions of the plasma behavior to explore a wide range of the thruster design space. Results from this model provide clear boundaries to miniature ion thruster performance while also providing clear pathways for effectively improving thruster design for increased mission capabilities. The results from the model guide an experimental effort to experimentally investigate the 3-ring and Axial Ring-Cusp Hybrid (ARCH) discharge designs for the MiXI thruster. A small plume diagnostics suite consisting of Faraday, emissive, and ExB probes was developed and used to probe the MiXI(ARCH) plume. While no doubly charged ions were detected in the beam at the operating point measured, measurements agree with prior computational work and show a beam flatness of0.6, divergence of 5 degrees, and plume potential of 4.5 V. Later, MiXI(ARCH) was operated with a miniature discharge hollow cathode. Finally, using lessons learned from cathode integration, computational, and analytical modeling, a refned miniature hollow cathode design was developed to further improve discharge and thruster effciency. Through experimental and analytical investigation, mission studies, and further development of critical aspects of the thruster, this work shows that the MiXI thruster is an attractive propulsion option for high effciency, high specifc impulse micropropulsion.

Download or read book Computational Investigations of Characteristic Performance Improvements for Subkilogram Laser Micropropulsion written by Richard Joel Thompson and published by . This book was released on 2009 with total page 89 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental investigations have evaluated the feasibility of using laser-driven plasma microthrusters for small-thrust, high-specific-impulse space maneuvers, particularly for micro- and nanosatellite missions. Recent work made use of the Mach2 hydromagnetics code for the construction of an adequate computational model of the micro-thruster operation. This thesis expounds on this previous work by extending the computational modeling capabilities, allowing for the determination of plasma plume properties and characteristic performance assessment of the microthruster; this allows for further computational investigation of the performance improvements achieved by new design considerations. Two particular design changes are implemented and measured: (i) the simulation of microthruster performance intentionally achieving laser-supported detonation of energetic polymer fuels for higher-thrust capabilities, and (ii) the implementation of an axisymmetric nozzle to improve passive solid-fuel performance. The Mach2 hydromagnetics code with the new performance assessment capabilities was used to examine the performance improvement of these new modes of operation; results of the simulations are presented and then evaluated for their use in the overall design of the plasma microthruster. Laser-supported detonation shows a tremendous potential increase in the laser momentum coupling coefficient C[subscript m], and demonstrates a much higher thrust; the axisymmetric nozzle varies with nozzle half-angle and length, but still demonstrates expected nozzle trends and improves the laser momentum coupling coefficient, C[subscript m], by up to 230% for some designs considered.

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 A Collection of Technical Papers written by and published by . This book was released on 2002 with total page 370 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 500 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Memorandum written by and published by . This book was released on 1994 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of a Throttlable 15 Cm Hollow Cathode Ion Thruster written by Paul J. Wilbur and published by . This book was released on 1972 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of the Performance of a Radio Frequency Thruster written by R. A. Bond and published by . This book was released on 1990 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Creation Analysis and Verification of a Comprehensive Model of a Micro Ion Thruster written by Maxwell Bodnar and published by . This book was released on 2016 with total page 225 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational model of the micro-ion thruster MiXI has been developed, analyzed, and partially verified. This model includes submodels that govern the physical, magnetic, electrostatic, plasma physics, and power deposition of the thruster. Over the past few years, theses have been conducted with the goal of running tests and analyzing the results; this model is used to understand how the thruster components interact so as to make predictions about, and allow for optimization of, the thruster operation. Testing is then performed on the thruster and the results are compared to the output of the code. The magnetic structure of the thruster was analyzed and numerous different configurations generated which were also evaluated by the optimizer and tested. Using the different configurations, models, and optimization tools, the total efficiency of the thruster is theoretically able to reach 69.4%. Operational testing of the thruster at many different throttle settings demonstrated a maximum total efficiency of 45.9 ±24.6%, discharge loss values as low as 109 ±25 eV/ion, and total power required as low as 50.5 ±0.1W to maintain thruster operation with beam extraction. Measurements of the plasma were taken using a Langmuir probe and the interpretation of the tests are used to verify the plasma physics submodel. Power draw measurements and analysis of the throttle inputs during testing are compared to the performance model outputs but were not accurate or consistent enough to fully verify the power deposition and plasma physics models. Analysis of the models and operational testing in this study have led to an increased understanding of the performance and operation of the MiXI-CP-V3 thruster, furthering the effort to create an efficient, flight capable micro-ion thruster.