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.
Geared toward advanced undergraduates and graduate students, this text develops the concepts of electrical acceleration of gases for propulsion, from primary physical principles to realistic space thruster designs. 1968 edition.
Progress in Astronautics and Aeronautics, Volume 9: Electric Propulsion Development covers the proceedings of the Second Electric Propulsion Conference of the American Rocker Society, held in Berkeley, California on March 14-16, 1962. The conference focuses on the existing problems in electric propulsion and their possible solutions. This book is organized into four sections encompassing 35 chapters. The first section deals with the thermodynamics of arcs; the problems of heat and momentum transfer; the chemical processes within arcs; the arc system materials; and the arc jet design problems. The second section considers the problems of ion systems, the various ion sources, and the neutralization of ion beams. This section also looks into the basic ionization processes, the production and charging of heavy particles, the corrosive properties of cesium, and the ion-optical designs. The third section describes various plasma systems, including helical transmission lines, pulsed pinch accelerators, coaxial systems, and j x B accelerators. The theoretical analyses of these systems are briefly examined. The fourth section includes papers on flight testing of electric propulsion models, on vertical rocket probes, and on satellites, This section also discusses some advanced concepts in electric propulsion, such as air scooping during ascent through the atmosphere, systems design and optimization, and planetary and interplanetary missions. This book is of great value to physicists, space engineers and designers, as well as researchers in the fields of astronautics and aeronautics.
|Author||: Charles L. Zola|
|Release Date||: 1969|
|Pages||: 39 pages|
|Author||: R. J. Litchford|
|Release Date||: 2001|
|Pages||: 51 pages|
|Author||: Wojciech Damian Jaron|
|Release Date||: 2012|
|Pages||: 329 pages|
The aim of this thesis was the design of a retractable, electric propulsion system for sailplanes, which could eliminate the main drawbacks of internal combustion engines. The design process was based on a number of modern sailplanes, within the 12 - 15 meter class, with sustainer operation in mind. One of the goals was to create a universal propulsion system that could be fitted to various aircrafts. The first part of the project concerned the selection of the key components of an electric propulsion system. First, the required power and thrust were calculated, and based on the obtained results a suitable electric motor was chosen. For this motor, an electronic controller was selected. Later, the estimation of propeller parameters was performed. Finally, battery basics were discussed and a battery was selected. The second part of the project concerned CAD modeling of the retractable electric propulsion system. The used materials were discussed in the beginning. The design process focused on two main assemblies: the propeller folding mechanism and the retractable structure. The complete result, the individual sub-assemblies and the most important solutions were presented. The use of composite materials was an important point of this thesis. Performance analysis was done after the system had been designed. The retractable electric propulsion system was designed with optimum results. A fullscale CAD model was created. The designed propulsion system can be considered as universal due to its relatively low weight, adequate power and compact size in the retracted position. Custom-made accessories facilitate mounting. A visit to the glider manufacturer Allstar PZL was the source of information about possible mounting solutions and battery placement options. The designed propulsion system can be used as a sustainer for all designated sailplanes. Self-launching proved possible in case of the lightest sailplanes. With similar power and flight duration, the electric propulsion system should be able to compete with petrol powered sustainer systems within the same class.
|Author||: United States. Congress. Joint Committee on Atomic Energy. Subcommittee on Research, Development, and Radiation|
|Release Date||: 1961|
|Pages||: 315 pages|
Focuses on cooperative AEC-NASA-DOD RPD programs to apply nuclear power to rocket propulsion and spacecraft power systems.
|Author||: National Academies of Sciences, Engineering, and Medicine,Division on Engineering and Physical Sciences,Aeronautics and Space Engineering Board,Committee on Propulsion and Energy Systems to Reduce Commercial Aviation Carbon Emissions|
|Publisher||: National Academies Press|
|Release Date||: 2016-08-09|
|ISBN 10||: 0309440998|
|Pages||: 122 pages|
The primary human activities that release carbon dioxide (CO2) into the atmosphere are the combustion of fossil fuels (coal, natural gas, and oil) to generate electricity, the provision of energy for transportation, and as a consequence of some industrial processes. Although aviation CO2 emissions only make up approximately 2.0 to 2.5 percent of total global annual CO2 emissions, research to reduce CO2 emissions is urgent because (1) such reductions may be legislated even as commercial air travel grows, (2) because it takes new technology a long time to propagate into and through the aviation fleet, and (3) because of the ongoing impact of global CO2 emissions. Commercial Aircraft Propulsion and Energy Systems Research develops a national research agenda for reducing CO2 emissions from commercial aviation. This report focuses on propulsion and energy technologies for reducing carbon emissions from large, commercial aircraftâ€" single-aisle and twin-aisle aircraft that carry 100 or more passengersâ€"because such aircraft account for more than 90 percent of global emissions from commercial aircraft. Moreover, while smaller aircraft also emit CO2, they make only a minor contribution to global emissions, and many technologies that reduce CO2 emissions for large aircraft also apply to smaller aircraft. As commercial aviation continues to grow in terms of revenue-passenger miles and cargo ton miles, CO2 emissions are expected to increase. To reduce the contribution of aviation to climate change, it is essential to improve the effectiveness of ongoing efforts to reduce emissions and initiate research into new approaches.
During the last decade, rapid growth of knowledge in the field of jet, rocket, nuclear, ion and electric propulsion has resulted in many advances useful to the student, engineer and scientist. The purpose for offering this course is to make available to them these recent advances in theory and design. Accordingly, this course is organized into seven parts: Part 1 Introduction; Part 2 Jet Propulsion; Part 3 Rocket Propulsion; Part 4 Nuclear Propulsion; Part 5 Electric and Ion Propulsion; Part 6 Theory on Combustion, Detonation and Fluid Injection; Part 7 Advanced Concepts and Mission Applications. It is written in such a way that it may easily be adopted by other universities as a textbook for a one semester senior or graduate course on the subject. In addition to the undersigned who served as the course instructor and wrote Chapter I, 2 and 3, guest lecturers included: DR. G. L. DUGGER who wrote Chapter 4 "Ram-jets and Air-Aug mented Rockets," DR. GEORGE P. SUTTON who wrote Chapter 5 "Rockets and Cooling Methods," DR . . MARTIN SUMMERFIELD who wrote Chapter 6 "Solid Propellant Rockets," DR. HOWARD S. SEIFERT who wrote Chapter 7 "Hybrid Rockets," DR. CHANDLER C. Ross who wrote Chapter 8 "Advanced Nuclear Rocket Design," MR. GEORGE H. McLAFFERTY who wrote Chapter 9 "Gaseous Nuclear Rockets," DR. S. G. FORBES who wrote Chapter 10 "Electric and Ion Propul sion," DR. R. H. BODEN who wrote Chapter 11 "Ion Propulsion," DR.
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
|Release Date||: 2000|
|Pages||: 16 pages|