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.
Download or read book Assessment of the Plume Characteristics of a Miniaturized Pulsed Plasma Thurster written by Richard Henry [Verfasser] Sypniewski Jr. and published by . This book was released on 2016 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Pulsed Plasma Thrusters are one of the most simplistic constructions in the electric propulsion family and are categorized among the electromagnetic class of thrusters. This classification of electromagnetics deals with the underlying physics of the pulsed plasma thruster and is much more complex with less understanding then other electric propulsion systems. However, due to the mechanical simplicity, wide range of specific impulses, non-toxic propellant, and the numerous applications, these thrusters are an ideal candidate for integrating into CubeSats. CubeSats are nanosatellites that are designed in three typical standard sizes (1 Unit, 2 Unit, and 3 Unit), each with standardized footprints. The smallest volumetric dimensions are the 1 Unit CubeSat, which is 10 x 10 x 10 cm. The volume and mass of CubeSats are quite small and therefore the miniaturization of the Pulsed Plasma Thruster is necessary to adhere to these constraints. Current research has shown that when miniaturization of a Pulsed Plasma Thruster there is a tendency for the thruster to work and perform in the electrothermal regime rather than in the electromagnetic one. Understanding which regime the thruster is operating in is critical for understanding how to optimize the design. For example, a thruster operates with higher efficiencies in the electromagnetic regime because there is much less loss from Ohmic heating. Preliminary testing of the Micro-Pulsed Plasma Thruster design was performed by the research company called FOTEC and determined a thruster chamber design. To understand thoroughly the Micro-Pulsed Plasma Thruster, characterization of the thruster and its plume will be conducted experimentally. This characterization will determine parametric features such as current/voltage waveform, electron temperatures, electron densities, and exhaust velocities. Performing the initial characterizations will give insight into the Micro-Pulsed Plasma Thruster and will provide further understanding into the regime that the thruster is operating in. The characteristics that resulted from this thesis concluded that the Micro-Pulsed Plasma Thruster is operating in the electromagnetic regime. This was concluded based on several characteristic traits that only conclude for electromagnetic acceleration mechanisms. These were that the peak currents reached were approximately 5,000 A and the exhaust velocity was in the 50 km/sec range. Further information was measured and the total resistance and inductance was calculated to be 13 m and 24 nH. Details on this information and how it was calculated is discussed in this thesis.*****Pulsed Plasma Thrusters are one of the most simplistic constructions in the electric propulsion family and are categorized among the electromagnetic class of thrusters. This classification of electromagnetics deals with the underlying physics of the pulsed plasma thruster and is much more complex with less understanding then other electric propulsion systems. However, due to the mechanical simplicity, wide range of specific impulses, non-toxic propellant, and the numerous applications, these thrusters are an ideal candidate for integrating into CubeSats. CubeSats are nanosatellites that are designed in three typical standard sizes (1 Unit, 2 Unit, and 3 Unit), each with standardized footprints. The smallest volumetric dimensions are the 1 Unit CubeSat, which is 10 x 10 x 10 cm. The volume and mass of CubeSats are quite small and therefore the miniaturization of the Pulsed Plasma Thruster is necessary to adhere to these constraints. Current research has shown that when miniaturization of a Pulsed Plasma Thruster there is a tendency for the thruster to work and perform in the electrothermal regime rather than in the electromagnetic one. Understanding which regime the thruster is operating in is critical for understanding how to optimize the design. For example, a thruster operates with higher efficiencies in the electromagne
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:
Download or read book Experimental Characterization of a Micro Pulsed Inductive Thruster MicroPIT Prototype written by Matthew Frederick Bartone and published by . This book was released on 2007 with total page 146 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pulsed Plasma Thruster Plume Characterization of Ion Species Using a Gridded Energy Analyzer written by Krystal Marie Parker and published by . This book was released on 2002 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Characterization of Electric Solid Propellant Pulsed Microthrusters written by Matthew Scott Glascock and published by . This book was released on 2016 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: "Electric solid propellants are an attractive option for space propulsion because they are ignited by applied electric power only. In this work, the behavior of pulsed microthruster devices utilizing such a material is investigated. These devices are similar in function and operation to the pulsed plasma thruster, which typically uses Teflon as propellant. A Faraday probe, Langmuir triple probe, residual gas analyzer, pendulum thrust stand and high speed camera are utilized as diagnostic devices. These thrusters are made in batches, of which a few devices were tested experimentally in vacuum environments. Results indicate a plume electron temperature of about 1.7 eV, with an electron density between 1011 and 1014 cm−3. According to thermal equilibrium and adiabatic expansion calculations, these relatively hot electrons are mixed with ~2000 K neutral and ion species, forming a non-equilibrium gas. From time-of-flight analysis, this gas mixture plume has an effective velocity of 1500-1650 m/s on centerline. The ablated mass of this plume is 215 [mu]g on average, of which an estimated 0.3% is ionized species while 45+̲11% is ablated at negligible relative speed. This late-time ablation occurs on a time scale three times that of the 0.5 ms pulse discharge, and does not contribute to the measured 0.21 mN-s impulse per pulse. Similar values have previously been measured in pulsed plasma thrusters. These observations indicate the electric solid propellant material in this configuration behaves similar to Teflon in an electrothermal pulsed plasma thruster"--Abstract, page iv.
Download or read book Plume Characterization of a One Millipound Solid Teflon Pulsed Plasma Thruster written by L. C. Pless and published by . This book was released on 1978 with total page 103 pages. Available in PDF, EPUB and Kindle. Book excerpt: An evaluation was made of the pulsed plasma thruster plume-wall backscatter characteristics of the MOLSINK facility. On the thruster axis, this backscatter drops off to zero as the angle between the axis and wall location reaches 40. This wall backscatter was found to be essentially symmetric about the plume axis. The total integrated backscatter from the MOLSINK wall is approximately equal to 5% of the total mass injected from the pulsed plasma thruster during the discharge pulse.
Download or read book Performance Characterization of a Novel Plasma Thruster to Provide a Revolutionary Operationally Responsive Space Capability with Micro and Nano satellites written by John-David C. De la Harpe and published by . This book was released on 2011 with total page 240 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book End of life Stationary Plasma Thruster Far field Plume Characterization written by Eric J. Pencil and published by . This book was released on 1996 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book written by and published by . This book was released on 1999 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance Characterization of the High Power Helicon Plasma Thruster with Varying Magnetic Nozzle Configurations written by Ilia Slobodov and published by . This book was released on 2011 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Progress in Development of Modeling Capabilities for a Micro pulsed Plasma Thruster written by Michael Keidar 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 An Electric Propulsion Diagnostic Package for the Characterization of the Plasma Thruster spacecraft Interactions on STENTOR Satellite written by M. Capacci and published by . This book was released on 1999 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Characterization of Plasma Actuator Based Microthruster Concepts for High Altitude Aircrafts and Cubesats written by Jignesh Soni and published by . This book was released on 2014 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transition is made from DBD to normal glow discharge plasma based on earlier findings, and several electrostatic and electromagnetic thruster designs are presented and investigated. The data presented in the thesis is intended to define the design space for development of a prototype microthruster.
Download or read book Development of a Micro pulsed Plasma Thruster for the Dawgstar Nanosatellite written by Christopher Rayburn and published by . This book was released on 2000 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Modular Numerical Environment for the Characterization of a Helicon Plasma Thruster written by Yaman Güçlü and published by . This book was released on 2011 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Vacuum Chamber Construction and Contamination Study of a Micro Pulsed Plasma Thruster written by Jacob H. Debevec and published by . This book was released on 2007 with total page 226 pages. Available in PDF, EPUB and Kindle. Book excerpt:
