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Development Of A Miniature Radio Frequency Ion Thruster With Inductively Coupled Plasma Icp Source For Cubesat Propulsion
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Book Synopsis Development of a Miniature Radio-Frequency Ion Thruster with Inductively Coupled Plasma (ICP) Source for CubeSat Propulsion by :
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:
Book Synopsis Analysis of a Miniature Radio Frequency Ion Thruster with an Inductively Coupled Plasma Source by : Peter Paul Bumbarger
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:
Book Synopsis Numerical Modelling of a Radio-frequency Micro Ion Thruster by : Michael Meng-Tsuan Tsay
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.
Book Synopsis Development of a Miniature Microwave-frequency Ion Thruster by : Daniel P. Lubey
Download or read book Development of a Miniature Microwave-frequency Ion Thruster written by Daniel P. Lubey and published by . This book was released on 2011 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Magnetized Radio Frequency Plasma Sources for Electric Space Propulsion by : Jan Dennis Gerst
Download or read book Investigation of Magnetized Radio Frequency Plasma Sources for Electric Space Propulsion written by Jan Dennis Gerst and published by . This book was released on 2013 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The PEGASES thruster (Plasma Propulsion with Electronegative Gases) is a novel type of electric thruster for space propulsion. It uses negative and positive ions produced by an inductively coupled radio frequency discharge to create the thrust by electrostatically accelerating the ions through a set of grids. A magnetic filter is used to increase the amount of negative ions in the cavity of the thruster. The PEGASES thruster is not only a source to create a strongly negative ion plasma or even an ion-ion plasma but it can also be used as a classical ion thruster. This means that a plasma is created and only the positive ions are extracted and accelerated making it necessary to neutralize the plasma behind the acceleration stage like in other ion thrusters. The performances of the PEGASES thruster have been investigated mainly in xenon in order to compare the obtained results with RIT-type ion thrusters. The thruster has been investigated with the help of a variety of probes such as a Langmuir probe, a planar probe, a capacitive probe and a RPA (Retarding Potential Analyzer). In addition, an ExB probe has been developed to measure the velocity of the ions leaving the thruster and to differentiate between the ion species present in the plasma.
Book Synopsis Miniature Ion Thruster Characterization Via Discharge Plasma, Plume, and Mission Analyses by : Stephen Anthony Samples
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.
Book Synopsis Empirical Aspects of a Mini-Helicon Plasma Thruster Experiment (mHTX@MIT) by : Joseph Eugene Palaia
Download or read book Empirical Aspects of a Mini-Helicon Plasma Thruster Experiment (mHTX@MIT) written by Joseph Eugene Palaia and published by . This book was released on 2006 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt: A helicon plasma source experiment has been developed and then constructed in the MIT Space Propulsion Laboratory (SPL) vacuum chamber. This experiment allows study of the intrinsic advantages of efficient helicon plasma production for use in space electric propulsion. Historical helicon experiment data have been applied to help size the experiment. The goal was to create a robust and flexible experimental system which would allow optimization of the source and system parameters for efficient thrust generation, and would permit for correlation between helicon theory and experiment. This effort may lead to the development of a new electric propulsion device, the Mini-Helicon Plasma Thruster. A design process was undertaken for the creation of this experimental setup, with the aid of a number of students and researchers at the MIT SPL. This thesis will focus on the author's specific contributions to this larger effort, which included the following elements. A survey of past helicon experiment parameters was completed, made possible largely due to the wealth of data provided by helicon plasma use in academia and for research and development. An analysis of the flow of propellant through the thruster was completed, utilizing low Mach number flow theory. A metallic structure was designed, structurally analyzed and constructed to support the electromagnets used to provide the required magnetic field. In addition, a radio frequency matching network enclosure and suitable interconnections were designed and constructed as part of the RF power delivery system. The result of the design and construction effort is a working, reliable, and flexible helicon plasma source system. This system provides the capability for future experimentation and helicon plasma thruster development.
Book Synopsis Numerical Modelling and Optimisation of Radio-frequency Ion Thrusters by : Martin Felix Closs
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:
Book Synopsis Development of a Plasma Simulation Tool for Radio Frequency Ion Thrusters by : Robert Henrich
Download or read book Development of a Plasma Simulation Tool for Radio Frequency Ion Thrusters written by Robert Henrich and published by . This book was released on 2013 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Microwave ECR Ion Thruster Development Activities at NASA Glenn Research Center by :
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:
Book Synopsis PROTOTYPING AND OPTIMIZATION OF A MINIATURE MICROWAVE-FREQUENCY ION THRUSTER. by : Mohammed Asif
Download or read book PROTOTYPING AND OPTIMIZATION OF A MINIATURE MICROWAVE-FREQUENCY ION THRUSTER. written by Mohammed Asif and published by . This book was released on 2018 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis presents progress on the development of the Miniature Microwave-Frequency Ion Thruster (MMIT), currently being developed at Penn State as a microthruster with high specific impulse that can be used on small satellites for station keeping, attitude adjustments, and modest delta-V maneuvers. The MMIT works by generating a microwave electron cyclotron resonance (ECR) discharge plasma, then accelerating ions through a series of electrostatic grids. Using argon as the propellant, the MMIT can start with as low as 2.6 W of total absorbed power from a 4.98-GHz coaxial input power source. For the current MMIT iteration, our research thrusts have been threefold: demonstrating plasma generation; sustaining and containing the plasma; and extracting the ion beam. We have largely focused on optimizing the geometry of the magnets and antenna used for ECR plasma generation; defining the geometry of the chamber for containment of the plasma; and developing grid geometries for efficient beam extraction. Progress to date toward a functional prototype has leveraged numerical simulations and experimental measurements on the proof-of-concept design, which we are currently further optimizing. A Langmuir probe is used to measure ion density and temperature in the plume as well as beam current, and a Faraday cup is used to measure the current density of the beam. The measurements obtained from these probes are used as the basis for determining a calculated thrust for the MMIT.
Book Synopsis LIFE ASSESSMENT OF A MINIATURE MICROWAVE-FREQUENCY ION THRUSTER. by : Sang Hsieh
Download or read book LIFE ASSESSMENT OF A MINIATURE MICROWAVE-FREQUENCY ION THRUSTER. written by Sang Hsieh and published by . This book was released on 2018 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis presents an assessment of grid life for the Miniature Microwave-Frequency Ion Thruster (MMIT), which is being developed at The Pennsylvania State University. The MMIT is proposed mainly for use in station keeping, modest delta-V maneuvers, and attitude control on small satellites. Previous research on the MMIT developed a working prototype that demonstrated plasma generation, plasma sustainment, and ion beam extraction. The iterative development process has incrementally improved the MMIT. Findings from previous research on the arcing and sputtering of the grids drove us to establish a new design criterion for grid life. The main failure criterion for the grids depends on the mass loss of the grid.Research on the thruster life can be divided into three parts: predicting the life of the grids, determination of the variables in the life equation, and proposing new design criteria based on the life assessment. We focus on studying the effective variables in the life prediction. Experimental data show the deformation of the grid caused by arcing and sputtering. The voltage difference between the grids serves to throttle the thruster and is the driver for sputtering. The influence of hole diameter and voltage on the life equation helps us understand how the arcing and sputtering affect life. Based on other research in the literature, we define a new parameter for the MMIT.The correlation between hole diameter, acceleration voltage, and thrust gives us a new perspective on the grid design. Previous research designed the grid based on the thrust requirement alone. However, the grid life is also one of many aspects to consider. The findings on the hole diameter and grid material with propellant lead to new design criteria. The fully functional flight version of the thruster should combine the previous design standard and new design guidelines.
Book Synopsis Micro Newton Thruster Development by : Franz Georg Hey
Download or read book Micro Newton Thruster Development written by Franz Georg Hey and published by Springer. This book was released on 2018-03-01 with total page 181 pages. Available in PDF, EPUB and Kindle. Book excerpt: Franz Georg Hey summarises the development and testing of a micro-Newton thrust balance, as well as the downscaling of a High Efficiency Multistage Plasma Thruster to micro-Newton thrust levels. The balance is tailored to fully characterise thruster candidates for the space based gravitational wave detector LISA. Thus, thrust noise measurements in sub-micro-Newton regime can be performed in the overall LISA bandwidth. The downscaled thruster can be operated down to serval tens of micro-Newton with a comparably high specific impulse. About the Author Franz Georg Hey works as mechanical, thermal, propulsion architect and technical lead of the micro‐Newton propulsion laboratory of Europe’s leading air and spacecraft manufacturer. The author is participating on major programmes for future satellite and electric propulsion development. The author’s research is performed in close collaboration with the Dresden University of Technology, the University of Bremen and the DLR Bremen.
Book Synopsis Fundamentals of Electric Propulsion by : Dan M. Goebel
Download or read book Fundamentals of Electric Propulsion written by Dan M. Goebel and published by Wiley. This book was released on 2008-12-22 with total page 486 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.
Book Synopsis Development of a Micro ECR Ion Thruster for Space Propulsion by : 沈明學
Download or read book Development of a Micro ECR Ion Thruster for Space Propulsion written by 沈明學 and published by . This book was released on 2017 with total page 191 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721532490 Total Pages :32 pages Book Rating :4.5/5 (324 download)
Book Synopsis Microwave Ecr Ion Thruster Development Activities at NASA Glenn Research Center by : National Aeronautics and Space Administration (NASA)
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
Book Synopsis Modelling and Design of Inductively Coupled Radio Frequency Gridded Ion Thrusters with an Application to Ion Beam Shepherd Type Space Missions by : Mantas Dobkevicius
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 pages. Available in PDF, EPUB and Kindle. Book excerpt:
