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 The Micro Pulsed Plasma Thruster written by and published by . This book was released on 1999 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: There is an increased requirement for microsatellites to support such future missions as formation-flying space-based radar, space control, and on-orbit satellite servicing. Devices that can provide precise impulse bit in the 10 micro Newton range may be enabling for a new fleet of 25-kg class spacecraft supporting these missions. In response to this need the Air Force Research Laboratory is developing a miniaturized propulsion unit: the Micro Pulsed Plasma Thruster (Micro-PPT). Like a standard PPT, The Micro-PPT uses a surface discharge across the face of a solid Teflon(TM) propellant to create and accelerate a combination of plasma and neutral vapor. However the Micro-PPT substantially differs from the standard design by using a self-igniting discharge and eliminating the separate igniter and trigger circuit from the thruster. This simplification enables the order-of- magnitude reductions in the thruster size and operational power level required to meet the microsatellite propulsion requirement.

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 High order Modeling of Micro pulsed Plasma Thrusters written by Guang Lin 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 Ionization Non equilibrium and Ablation Phenomena in a Micro Pulsed Plasma Thruster written by Michael Keidar 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 Using a Gatling gun Configured Micro Pulsed Plasma Thruster as a Means to Control Micro Satellites with Extreme Precision written by Lee I. Watson and published by . This book was released on 2011 with total page 206 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 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:

Download or read book Contamination Study of a Micro Pulsed Plasma Thruster written by Ceylan Kesenek and published by . This book was released on 2008 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Development of Micro scale Pulsed Plasma Thruster for Cube Satellite written by 孫宜平 and published by . This book was released on 2018 with total page 75 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 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 Characterizing the Exhaust Plume of the Micro Pulsed Plasma Thrusters by High Speed Imagery written by Sakir Tirsi and published by . This book was released on 2008 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Optimization of Pulsed Plasma Thrusters for Micro satellite Propulsion written by P. J. Turchi 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 Applications for Pulsed Plasma Thrusters and the Development of Small PPTs for Micro spacecraft written by W. Andrew Hoskins 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 High Resolution Laser Diagnostics in Millimeter Scale Micro Pulsed Plasma Thrusters written by and published by . This book was released on 2002 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: A class of Micro-Pulsed Plasma Thruster (MicroPPT) is being developed to provide precise attitude control and stationkeeping ability to 25-kg class satellites. Operating by means of a surface discharge across a Teflon propellant fuel bar only a few millimeters in diameter, the MicroPPT delivers a thrust-to-power ratio of 5 - 10 Micro-N-s/J. Due to the low pulse energy and size, the MicroPPT produces a spatially confined and diffuse plasma plume that is difficult to analyze with material probes for validation of plume modeling. To this end, a Herriott Cell interferometer is introduced to measure the plume electron and neutral densities. By focusing a large number of laser beams into a small measurement volume, the Herriott Cell can increase the instrument resolution by a factor of about 10, compared to a single-pass interferometer, with minimal degradation of spatial resolution. Comparison of these results with a 2 colors, 2-pass interferometer demonstrates experimental validity of the point measurement technique used. Comparison of the measured electron density with modeling predictions by Keidar and Boyd shows close agreement. Attempts to measure the MicroPPT neutral density with a 2 colors configuration of the Herriott Cell interferometer were inconclusive, in spite of previous successes using this technique on larger PPTs.