Instrumentation, Control and Torch Ignition Systems Development for LOX/Methane Propulsion Research PDF Download
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Author: Jesus Betancourt-Roque
Publisher:
ISBN:
Category : Automatic data collection systems
Languages : en
Pages :
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Author: Jesus Betancourt-Roque
Publisher:
ISBN:
Category : Automatic data collection systems
Languages : en
Pages :
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Author: Nasa Technical Reports Server (Ntrs)
Publisher: BiblioGov
ISBN: 9781289235215
Category :
Languages : en
Pages : 22
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Book Description
A workhorse liquid oxygen-liquid methane (LOX/LCH4) rocket igniter was recently tested at NASA Glenn Research Center s (GRC) Research Combustion Laboratory (RCL). These tests were conducted in support of the Reaction Control Engine (RCE) development task of the Propulsion and Cryogenics Advanced Development (PCAD) project. The igniter was a GRC in-house design used to evaluate the ignition processes for LOX/LCH4. The test matrix was developed to examine the flammability of LOX/LCH4 over a range of oxidizer-to-fuel mixture ratios, both in the core fuel flow and total flow. In addition, testing also examined the durability of the hardware by accumulating ignition pulses. Over the course of testing, a total of 1402 individual ignition pulses were successfully demonstrated over the range of mixture ratios. Testing was halted after the failure of the ceramic in the igniter spark plug.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781719389631
Category :
Languages : en
Pages : 40
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Book Description
The use of nontoxic propellants in future exploration vehicles would enable safer, more cost-effective mission scenarios. One promising green alternative to existing hypergols is liquid methane (LCH4) with liquid oxygen (LO2). A 100 lbf LO2/LCH4 engine was developed under the NASA Propulsion and Cryogenic Advanced Development project and tested at the NASA Glenn Research Center Altitude Combustion Stand in a low pressure environment. High ignition energy is a perceived drawback of this propellant combination; so this ignition margin test program examined ignition performance versus delivered spark energy. Sensitivity of ignition to spark timing and repetition rate was also explored. Three different exciter units were used with the engine s augmented (torch) igniter. Captured waveforms indicated spark behavior in hot fire conditions was inconsistent compared to the well-behaved dry sparks. This suggests that rising pressure and flow rate increase spark impedance and may at some point compromise an exciter s ability to complete each spark. The reduced spark energies of such quenched deliveries resulted in more erratic ignitions, decreasing ignition probability. The timing of the sparks relative to the pressure/flow conditions also impacted the probability of ignition. Sparks occurring early in the flow could trigger ignition with energies as low as 1 to 6 mJ, though multiple, similarly timed sparks of 55 to 75 mJ were required for reliable ignition. Delayed spark application and reduced spark repetition rate both correlated with late and occasional failed ignitions. An optimum time interval for spark application and ignition therefore coincides with propellant introduction to the igniter. Kleinhenz, Julie and Sarmiento, Charles and Marshall, William Glenn Research Center LIQUEFIED GASES; LIQUID OXYGEN; METHANE; SPARK IGNITION; REACTION CONTROL; SPARK PLUGS; AUGMENTATION; ALTITUDE; LOW PRESSURE; DATA REDUCTION; ENGINE DESIGN; WAVEFORMS; ELECTRICAL MEASUREMENT; ENERGY REQUIREMENTS; IGNITERS; OSCILLOSCOPES
Author: Robert Joseph Ellis
Publisher:
ISBN:
Category : Liquid propellants
Languages : en
Pages :
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Author: Chunyoung Park
Publisher:
ISBN: 9781321723946
Category : Plasma jets
Languages : en
Pages : 62
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Abstract: A DC-thermal plasma jet is proposed as a reliable ignition source for reaction control system (RCS) thrusters employing oxygen with hydrocarbons, like methane. Industrial plasma torch systems are analyzed to understand the behavioral characteristics of DC-thermal plasmas. Nitrogen is used as a working gas for the source of plasma jet to understand the general mechanism of thermal plasma formation. DC-thermal plasmas require high electrical energy to maintain their arc discharge status which presents challenges in space systems. The purpose of this study is, therefore, to find a suitable configuration which minimizes power consumption. Various physical and electrical conditions relate to a thermal plasma formation. In this study, the input voltage (221-332V) and pressure (5-15 psi) are applied as initial conditions. The DC-power module and starter module are designed as plasma drivers and a commercial off-the-shelf torch head is used for this research. The normalized method is developed to estimate the arc temperature. Test results show that the lowest power consumption and arc-starting voltage are 1,321W and 248.8 VDC, respectively. In addition, it is found that the current is a major factor for varying the mass flow rate. Since the lowest power consumption is still high, future improvements and research should focus on integrating a high-power and lightweight energy source, developing a high-frequency and half-duty cycle power system, and incorporating a composite cathode. In addition, a new conceptual torch design is proposed to be considered as an igniter for RCS thrusters. The next step would be to repeat the plasma torch tests with the new configuration at ambient and vacuum conditions. These would be followed by combustion tests to verify the actual functionality of the plasma igniter for RCS thrusters with various oxidizer and fuel mixture ratios. In parallel, research should focus on miniaturization of the electrical system.
Author: John Drury Clark
Publisher: Rutgers University Press
ISBN: 0813599199
Category : Biography & Autobiography
Languages : en
Pages : 217
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Book Description
This newly reissued debut book in the Rutgers University Press Classics Imprint is the story of the search for a rocket propellant which could be trusted to take man into space. This search was a hazardous enterprise carried out by rival labs who worked against the known laws of nature, with no guarantee of success or safety. Acclaimed scientist and sci-fi author John Drury Clark writes with irreverent and eyewitness immediacy about the development of the explosive fuels strong enough to negate the relentless restraints of gravity. The resulting volume is as much a memoir as a work of history, sharing a behind-the-scenes view of an enterprise which eventually took men to the moon, missiles to the planets, and satellites to outer space. A classic work in the history of science, and described as “a good book on rocket stuff…that’s a really fun one” by SpaceX founder Elon Musk, readers will want to get their hands on this influential classic, available for the first time in decades.
Author: Jesús Roberto Flores
Publisher:
ISBN:
Category : Internal combustion engines
Languages : en
Pages :
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Author: DP Mishra
Publisher: CRC Press
ISBN: 1351708414
Category : Technology & Engineering
Languages : en
Pages : 364
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Book Description
The book follows a unified approach to present the basic principles of rocket propulsion in concise and lucid form. This textbook comprises of ten chapters ranging from brief introduction and elements of rocket propulsion, aerothermodynamics to solid, liquid and hybrid propellant rocket engines with chapter on electrical propulsion. Worked out examples are also provided at the end of chapter for understanding uncertainty analysis. This book is designed and developed as an introductory text on the fundamental aspects of rocket propulsion for both undergraduate and graduate students. It is also aimed towards practicing engineers in the field of space engineering. This comprehensive guide also provides adequate problems for audience to understand intricate aspects of rocket propulsion enabling them to design and develop rocket engines for peaceful purposes.
Author:
Publisher:
ISBN:
Category : Airframes
Languages : en
Pages : 220
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Author: Dieter K. Huzel
Publisher: AIAA
ISBN: 9781600864001
Category : Liquid propellant rocket engines
Languages : en
Pages : 452
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