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.
Download or read book Investigation of a Pulsed Plasma Thruster for Atmospheric Applications written by Manuel Azuara Rosales and published by . This book was released on 2020 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt: To date, the controlled access to terrestrial atmospheric altitudes of more than 20 km is limited with current technology. This is because at such altitudes, the background gas density is too low for conventional blade-based propellers to operate, and too high for most in-space electric propulsion systems. This research aims to investigate the Pulsed Plasma Thruster technology for atmospheric applications, at a background gas pressure of less than 50 Torr, corresponding to terrestrial atmospheric altitudes of more than 20 km. Because the system operates in a highly collisional regime, three acceleration mechanisms are identified, 1) due to ion-neutral collisions, 2) due to the J x B force, and 3) electrostatic acceleration. A theoretical model to obtain the thrust-to-power ratio of a Pulsed Plasma Thruster for atmospheric applications is presented and validated experimentally using a pendulum-based thrust stand, a quadruple Langmuir probe, and a B-dot probe. A proposed Air-Breathing Pulsed Plasma Thruster was investigated, and based on the experimental results, an analytical approach to determine whether the system can sustain an aircraft at the aforementioned altitudes is presented, and experimentally demonstrated through three in-field tests, consisting on launching in-house designed and built aircraft to the stratosphere using high-altitude burst balloons.
Download or read book Introduction to Plasmas and Plasma Dynamics written by Hai-Bin Tang and published by Elsevier. This book was released on 2024-05-09 with total page 421 pages. Available in PDF, EPUB and Kindle. Book excerpt: Introduction to Plasmas and Plasma Dynamics: With Plasma Physics Applications to Space Propulsion, Magnetic Fusion and Space Physics, Second Edition provides an accessible introduction to the understanding of high temperature, ionized gases necessary to conduct research and develop applications related to plasmas. Thoroughly updated and expanded, this sec Describes plasma applications with close reference to elementary processes, promoting a deeper understanding of plasmas in new fields Provides structured problems in every chapter that help readers grasp the book’s practical lessons Includes a new chapter on numerical methods in plasmas that adds crucial context for experimental approaches
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.
Download or read book Recent Advancements in Green Propulsion written by Rachid Amrousse and published by Springer Nature. This book was released on with total page 433 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Dissertation Abstracts International written by and published by . This book was released on 2004 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Breakthrough to Optimized Pulsed Plasma Thrusters written by and published by . This book was released on 2004 with total page 0 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.
Download or read book Propulsion Mechanisms in a Helicon Plasma Thruster written by Nareg Sinenian and published by . This book was released on 2008 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: Electric thrusters offer an attractive option for various in-space propulsion tasks due to their high thrust efficiencies. The performance characteristics of a compact electric thruster utilizing a helicon plasma source is investigated with the goal of identifying potential thrust mechanisms. Performance characteristics such as thrust, specific impulse, ion cost and thrust efficiency are discussed and related to plasma parameters. The design and fabrication of a prototype compact helicon thruster is presented, including design of a radio-frequency power delivery system, electromagnets and a propellant flow system. The design of plasma diagnostics and associated measurement techniques are discussed including a retarding potential analyzer, mach probes and langmuir probes. These diagnostics are used to measure plasma properties such as electron temperature, plasma density, and ion flow velocities. Thruster performance characteristics are then derived from these measurement results. Significant ion acceleration is demonstrated in both Argon and Nitrogen plasmas and potential mechanisms for this are discussed.
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:
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:
Download or read book Multi Axis Thrust Measurements of the EO 1 Pulsed Plasma Thruster written by Lynn A. Arrington and published by . This book was released on 1999 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Evaluation of Pulsed Plasma Thruster Micropulsing written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-21 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper evaluates the concept of pulsed plasma thruster (PPT) micropulsing. Micropulsing was a premise behind a power processing unit (PPU) and an energy storage unit (ESU) design that for certain mission profiles, it was advantageous to operate a PPT at lower energy but higher frequency rather than at a higher energy but lower frequency. This premise allows for reductions in the ESU volume and mass without paying a penalty in thrust. To complete the evaluation, an independent spark plug initiation unit, a high voltage power supply and a variety of mica foil capacitors at 2.6, 5, 10, and 20 capacitance were used to conduct a series of tests on a single PPT to map performance levels of thrust, impulse bit, efficiency and specific impulse over a comparable power range. Testing at NASA Glenn Research Center was conducted with breadboard PPT hardware. The test results showed that operating in the lower energy ESU micropulsing mode produced similar thrust levels to a higher energy ESU operating at high power level. Further testing however showed a reduction in specific impulse and efficiency when the smaller capacitances were used at the highest power levels. This would require more fuel mass for a mission that was predominately high power, potentially negating the ESU mass savings. Therefore, micropulsing is advantageous where most of a mission profile occurs at low power, but retains the ability to conduct high thrust maneuvers when necessary. Arrington, Lynn Glenn Research Center NASA/CR-2004-213209, AIAA Paper 2004-3458, E-14717
Download or read book 39th AIAA ASME SAE ASEE Joint Propulsion Conference Exhibit July 20 23 2003 Huntsville Alabama 03 5000 03 5049 written by and published by . This book was released on 2003 with total page 468 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Performance Comparison of Pulsed Plasma Thruster Electrode Configurations written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-09 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pulsed plasma thrusters are currently planned on two small satellite missions and proposed for a third. In these missions, the pulsed plasma thruster's unique characteristics will be used variously to provide propulsive attitude control, orbit raising, translation, and precision positioning. Pulsed plasma thrusters are attractive for small satellite applications because they are essentially stand alone devices which eliminate the need for toxic and/or distributed propellant systems. Pulsed plasma thrusters also operate at low power and over a wide power range without loss of performance. As part of the technical development required for the noted missions, an experimental program to optimize performance with respect to electrode configuration was undertaken. One of the planned missions will use pulsed plasma thrusters for orbit raising requiring relatively high thrust and previously tested configurations did not provide this. Also, higher capacitor energies were tested than previously tried for this mission. Multiple configurations were tested and a final configuration was selected for flight hardware development. This paper describes the results of the electrode optimization in detail. Arrington, Lynn A. and Haag, Tom W. and Pencil, Eric J. and Meckel, Nicole J. Glenn Research Center NASA/TM-97-206305, E-11002, NAS 1.15:206305, IEPC-97-127 NAS3-27186; RTOP 632-1B-1B...
Download or read book A Performance Comparison of Pulsed Plasma Thruster Electrode Configurations written by and published by . This book was released on 1997 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pulsed Plasma Thruster Using Water Propellant 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:
Download or read book Experimental and Theoretical Investigation of Pulsed Plasma Thrusters written by Hani Kamhawi and published by . This book was released on 2002 with total page 380 pages. Available in PDF, EPUB and Kindle. Book excerpt:
