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Author : John K. Ziemer
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Dimensionless Performance Model for Gas-fed Pulsed Plasma Thrusters written by John K. Ziemer and published by . This book was released on 1998 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John K. Ziemer
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Performance Characterization of a High Efficiency Gas-fed Pulsed Plasma Thruster written by John K. Ziemer and published by . This book was released on 1997 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John K. Ziemer
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Performance of Gas-fed Pulsed Plasma Thrusters Using Water Vapor Propellant written by John K. Ziemer and published by . This book was released on 2002 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John Kenneth Ziemer
Publisher :
ISBN 13 :
Total Pages : 572 pages
Book Rating : 4.:/5 (493 download)
Download or read book Performance Scaling of Gas-fed Pulsed Plasma Thrusters written by John Kenneth Ziemer and published by . This book was released on 2001 with total page 572 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 170 pages
Book Rating : 4.:/5 (946 download)
Download or read book Gas-Fed Pulsed Plasma Thrusters: Fundamentals, Characteristics and Scaling Laws written by and published by . This book was released on 2000 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: This final report presents the results of a three-year theoretical and experimental investigation into the fundamentals of gas-fed pulsed plasma thrusters (GF-PPTs). The primary goals were to deepen the basic understanding of how the performance of these devices can be optimized and scaled down to low pulse energies for application as efficient high-specific electric thrusters on small spacecraft. This final report gives a detailed overview of previous research, discusses the electromagnetic nature of the acceleration process, the effect of capacitance, electrode geometry, inductance-per-unit length, and discharge initiation on performance, and presents theoretically derived and experimentally verified performance scaling laws.
Author :
Publisher :
ISBN 13 :
Total Pages : 612 pages
Book Rating : 4.0/5 ( download)
Download or read book 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit: 2000-3400 - 2000-3449 written by and published by . This book was released on 2000 with total page 612 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 564 pages
Book Rating : 4.0/5 ( download)
Download or read book 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit July 11-14, 2004, Fort Lauderdale, FL.: no. 3699 written by and published by . This book was released on 2004 with total page 564 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (946 download)
Download or read book High Efficiency Pulsed Plasma Thruster for Satellite Attitude Control and Maneuver written by and published by . This book was released on 2003 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The primary objective of this project was to develop Gas-Fed Pulsed Plasma Thrusters (GF-PPT) that can be used with water vapor or hydrazine as fuel, with vapor pressures of less than 1 Torr necessary to operate the thruster. This propulsion technology can be used to perform orbit phase changes or plane (inclination) changes for near and intermediate-earth orbit satellites. GF-PPT technology is particularly suited for large DELTA-V, in-plane, orbit phase changes. This technology can therefore complement resistojet technology and allow rapid constellation redeployment to insure prompt satellite coverage of conflicts at any location on the surface of the earth with a constellation of satellites optimized for minimum size and cost. This report discusses GF-PPT thruster performance scaling, as well as hardware and power electronics that were developed in this project.
Author :
Publisher :
ISBN 13 :
Total Pages : 980 pages
Book Rating : 4.F/5 ( download)
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1998 with total page 980 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Yiangos George Mikellides
Publisher :
ISBN 13 : 9780599429246
Total Pages : 106 pages
Book Rating : 4.4/5 (292 download)
Download or read book Theoretical Modeling and Optimization of Ablation-fed Pulsed Plasma Thrusters written by Yiangos George Mikellides and published by . This book was released on 1999 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Theoretical modeling of ablation-fed, pulsed plasma thrusters (PPTs) with the MACH2 code has shown that after repeated pulsed operation, the total expelled mass is due to ablation during the discharge and solid decomposition that persists long after the pulse. The latter mass does not considerably contribute to the impulse-bit thus degrading thruster performance. For the rectangular PPT geometry, optimizing current waveforms in combination with channel widths are presented, that utilize all decomposed mass, electromagnetically. These waveforms are characterized by short rise times (1 [mu]sec) and prolonged decays (25 [mu]sec). Simplified modeling based on steady-state, one-dimensional flow reveals that the mass flow rate varies linearly with the square of the magnetic field and that the downstream flow speed is driven towards the Alfven wave speed when the magnetic pressure is much greater than the gasdynamic pressure. The model has been confirmed by MACH2. The mass flow requirement for such magnetosonic flow in turn, determines the surface temperature of the solid.
Author : Carsten A. Scharlemann
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (543 download)
Download or read book Investigation of Thrust Mechanisms in a Water Fed Pulsed Plasma Thruster written by Carsten A. Scharlemann and published by . This book was released on 2003 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Analytic models predict the possibility of extending the range of performance parameters of Pulsed Plasma Thrusters (PPT) by using propellants other than the traditionally used Teflon. A theoretical and experimental effort was initiated at The Ohio State University to investigate the use of alternative propellants for PPT. Analytical and numerical calculations (MACH2) indeed indicate a significant broadening of the obtainable range of specific impulse and thrust-to-power ratios when alternative propellants such as lithium or water are utilized. Consequently, in an effort to investigate changes in physical phenomena and thruster performance experimentally, a hybrid thruster was designed and built, facilitating the use of alternatively water or Teflon. The thruster design includes a unique water propellant feed system, allowing the supply of the water propellant without detrimentally affecting the inherent simplicity of the PPT system. ii The thruster operation and performance was investigated by several different diagnostic methods, including current and voltage measurements, Langmuir probes, and magnetic field probes. Furthermore, impact pressure measurements in the plume of the thruster allowed new insight into the plume structure and the accurate evaluation of impulse bits. Employment of the diagnostic methods for Teflon and water propellant enabled the unambigous identification of propellant related effects such as reduced electron temperature and higher exhaust velocites in the case of water propellant. The electromagnetic nature of the water thruster was clearly identified. For 30 J discharge energy, the water thruster requires only 5% of the mass bit of a Teflon thruster to produce an impulse bit 30% of the magnitude of the Teflon thruster, suggesting greatly increased propellant efficiencies. In agreement with the plasma diagnostic results, a specific impulse for the water thruster of up to 8000 s and efficiencies of up to 16% were evaluated.
Author : Jianjun Wu
Publisher : Springer
ISBN 13 : 9789819779574
Total Pages : 0 pages
Book Rating : 4.7/5 (795 download)
Download or read book Numerical Simulation of Pulsed Plasma Thruster written by Jianjun Wu and published by Springer. This book was released on 2024-11-20 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book are valuable in gaining an understanding of the working mechanism of pulsed plasma thrusters. It facilitates the evaluation of the thruster's working characteristics and propulsive performance, thereby providing a crucial theoretical foundation and reference for the design, development, and engineering application of pulsed plasma thrusters. Additionally, this book significantly contributes to the advancement of space electric propulsion technology. Researchers and engineers in the aerospace propulsion field can greatly benefit from the insights presented within this book. This is an open access book.
Author : D. W. Yannitell
Publisher :
ISBN 13 :
Total Pages : 34 pages
Book Rating : 4.:/5 (227 download)
Download or read book Modeling the Exhaust of the Pulsed Plasma Thruster written by D. W. Yannitell and published by . This book was released on 1985 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: The work presented in this report is an investigation of the plasma flow on a Teflon Pulsed Plasma Thruster (PPT), and the resulting plume. The long range goal is a theoretical model of the flow, both between and beyond the thruster electrodes, that could aid in the improvement of performance, and also predict the contamination potential of the device. The overall model required consists of an internal portion interfaced with an external portion at the exit plane of the electrodes. Most of this report deals with the internal portion of the model. Specifically, the physics of the discharge and plasma acceleration between the electrodes are discussed, and a mathematical model is developed which appears to be consistant with the available experimental data. The investigation shows the necessity of certain additional information without which the model cannot be properly exercised. The validity of certain assumptions of magnetohydrodynamic theory is demonstrated for the nontypical plasma produced by the PPT, and logical consequences of the assumptions are considered vis a vis recently obtained electromagnetic data. A major difficulty in the modeling of the internal flow is the selection of the proper boundary conditions to be applied to the solution domain. These include conditions at the electrodes, the insulator, the ablating Teflon surfaces, and the interface with the vacuum ahead of, and behind, the plasma blobs. Keywords include: Pulsed plasma; Plume modeling; Teflon pulsed plasma.
Author : Jeremy J. Selstrom
Publisher :
ISBN 13 :
Total Pages : 260 pages
Book Rating : 4.:/5 (66 download)
Download or read book Thrust and Performance Study of Micro Pulsed Plasma Thrusters written by Jeremy J. Selstrom and published by . This book was released on 2010 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Diego Mejia Montano
Publisher :
ISBN 13 :
Total Pages : 64 pages
Book Rating : 4.:/5 (111 download)
Download or read book Characterization of an Exploding Micro-wire Pulsed Plasma Thruster written by Diego Mejia Montano and published by . This book was released on 2019 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pulsed Plasma Thrusters typically live in the low-range efficiency realm compared to other types of electric propulsion thrusters. In an attempt to explore if any added benefits could be gained from experimenting with a new propellant type, additional physics had to be incorporated into the classical RLC model approach. A study into modeling how a micro-wire propellant would react when subjected to energy deposition via current-driven heating was undertaken. Once a first-order estimate, verified with computational estimates, was obtained then the classical RLC series circuit model could be used to compare and validate the results obtained from experimentation. It was found that while the proposed propellant type is feasible, it produced performance differences that could not be explained solely by the classical model and a more exhaustive investigation into various phenomena will have to be pursued.
Author : Jeremiah Daniel Hanna
Publisher :
ISBN 13 :
Total Pages : 103 pages
Book Rating : 4.:/5 (116 download)
Download or read book Liquid Pulsed Plasma Thruster Plasma Plume Investigation and MR-SAT Cold Gas Propulsion System Performance Analysis written by Jeremiah Daniel Hanna and published by . This book was released on 2017 with total page 103 pages. Available in PDF, EPUB and Kindle. Book excerpt: "The plasma plume produced by a liquid pulsed plasma thruster is investigated using a Langmuir triple probe and a nude Faraday probe. The Langmuir triple probe failed to produce results which are suspected caused by the presence of ionic liquid in the plume resulting in shorting of the probe. The nude Faraday probe is able to record the ion current density which revealed a high level of inconsistency in the plasma plume. Ion current density recorded by the nude Faraday probe had a relative standard deviation of upwards of 100% of the mean value. Controlling the amount of propellant used during each pulse was extremely difficult. Investigating the plasma plume with more complex probes was not done due to the inconsistency measured by the nude Faraday probe and the expulsion of ionic liquid from the thruster which is highly corrosive to metals. Examining the historical thrust test data performed by the Missouri Satellite Research Team, a revised model with new assumptions was created and resulted in an improvement in accuracy to within 4.5%. The cold gas propulsion system developed over the years had undergone testing which resulted in measured thrust half of what was predicted. Developing a thrust prediction scheme that incorporates the effects of the solenoid control valve decreases the error to between 1-3% depending on temperature considerations. This thrust prediction scheme can be applied to the current design for the NanoSat 8 competition and results in an accurate prediction of thrust"--Abstract, page iii.
Author :
Publisher :
ISBN 13 :
Total Pages : 69 pages
Book Rating : 4.:/5 (742 download)
Download or read book Breakthrough to Optimized Pulsed Plasma Thrusters written by and published by . This book was released on 2004 with total page 69 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analytic models predict the possibility of extending the range of performance parameters of Pulsed Plasma Thrusters (PPT) by using propellants other than the traditionally used Teflon. A theoretical and experimental effort was initiated at The Ohio State University to investigate the use of alternative propellants for PPT. Analytical and numerical calculations (MACH2) indeed indicate a significant broadening of the obtainable range of specific impulse and thrust-to-power ratios when alternative propellants such as lithium or water are utilized. Consequently, in an effort to investigate changes in physical phenomena and thruster performance experimentally, a hybrid thruster was designed and built, facilitating the use of alternatively water or Teflon. The thruster design includes a unique water propellant feed system, allowing the supply of the water propellant without detrimentally affecting the inherent simplicity of the PPT system. The thruster operation and performance was investigated by several different diagnostic methods, including current and voltage measurements, Langmuir probes, and magnetic field probes. Furthermore, impact pressure measurements in the plume of the thruster allowed new insight into the plume structure and the accurate evaluation of impulse bits. Employment of the diagnostic methods for Teflon and water propellant enabled the unambiguous identification of propellant related effects such as reduced electron temperature and higher exhaust velocities in the case of water propellant.
