Relevant bibliographies by topics / Advanced Propulsion

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Advanced Propulsion'

Author: Grafiati
Published: 4 June 2021
Last updated: 14 February 2022

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Journal articles on the topic "Advanced Propulsion"

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George, Daweel. "Advanced space propulsion concepts." Acta Astronautica 16 (January 1987): 113–23. http://dx.doi.org/10.1016/0094-5765(87)90099-3.

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Seitz, A., D. Schmitt, and S. Donnerhack. "Emission comparison of turbofan and open rotor engines under special consideration of aircraft and mission design aspects." Aeronautical Journal 115, no. 1168 (June 2011): 351–60. http://dx.doi.org/10.1017/s000192400000587x.

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Abstract An integrated parametric model involving the design of propulsion system, airframe and flight mission is presented. Based hereon, the carbon dioxide (CO2) emission characteristics of advanced direct-drive turbofan and open rotor powered aircraft are analysed against pertinent aircraft and propulsion system design parameters. In addition, initial concept-specific trend statements on nitrogen oxides (NOx) as well as propulsor noise emission characteristics are derived. The obtained results contribute to a better understanding of more appropriate aircraft design attributes for advanced system architectures.
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Cruse, T. A., J. F. Unruh, Y. T. Wu, and S. V. Harren. "Probabilistic Structural Analysis for Advanced Space Propulsion Systems." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 251–60. http://dx.doi.org/10.1115/1.2906171.

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This paper reports on recent extensions to ongoing research into probabilistic structural analysis modeling of advanced space propulsion system hardware. The advances concern probabilistic dynamic loading, and probabilistic nonlinear material behavior. In both cases, the reported work represents a significant advance in the state-of-the-art for these topics. Random, or probabilistic loading is normally concerned with the loading described in power spectral density (PSD) terms. The current work describes a method for incorporating random PSD’s along with random material properties, damping, and structural geometry. The probabilistic material response is concerned with the prediction of nonlinear stress-strain behavior for physical processes that can be linked to the original microstructure of the material. Such variables as grain size and orientation, grain boundary strength, etc., are treated as random, initial variables in generating stochastic stress-strain curves. The methodology is demonstrated for a creep simulation.
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Reisz, Aloysius I. "To Go Beyond." Mechanical Engineering 130, no. 11 (November 1, 2008): 42–45. http://dx.doi.org/10.1115/1.2008-nov-2.

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This article discusses experiments with an advanced electromagnetic engine that aims for high-speed, long-distance transportation to reach farther into space. Experimental work at Marshall Space Flight Center in Alabama is attempting to develop an electromagnetic engine designed to achieve higher velocities than current space-engine options and to last longer, too. Space engines with higher specific impulse will sense new science from deep space exploration quicker. In a way, higher specific impulse quickens our intelligence acquisition. Reisz Engineers and the University of Michigan are investigating the propulsive performances of an experimental advanced electromagnetic engine configuration. This electromagnetic propulsion configuration has a magnetic nozzle and the engine performance can be throttled. Electromagnetic propulsion systems can also be configured for operations in Earth space environment, and for lunar robotic and lunar mapping missions. Electromagnetic and fusion space engines promise fast and reliable propulsion systems, which will be needed if mankind is to pursue its exploration of the outer realms of our solar system and beyond.
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Herdrich, G., U. Bauder, A. Boxberger, R. A. Gabrielli, M. Lau, D. Petkow, M. Pfeiffer, C. Syring, and S. Fasoulas. "Advanced plasma (propulsion) concepts at IRS." Vacuum 88 (February 2013): 36–41. http://dx.doi.org/10.1016/j.vacuum.2012.02.032.

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Bayandor, J., S. Abanteriba, and I. Bates. "An advanced zero-head hydro-propulsion." Renewable Energy 24, no. 3-4 (November 2001): 475–84. http://dx.doi.org/10.1016/s0960-1481(01)00031-3.

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Padture, Nitin P. "Advanced structural ceramics in aerospace propulsion." Nature Materials 15, no. 8 (July 22, 2016): 804–9. http://dx.doi.org/10.1038/nmat4687.

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Garrison, P. W. "Advanced propulsion activities in the USA." Acta Astronautica 16 (January 1987): 357–66. http://dx.doi.org/10.1016/0094-5765(87)90124-x.

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Paton, Neil E. "Materials for advanced space propulsion systems." Materials Science and Engineering: A 143, no. 1-2 (September 1991): 21–29. http://dx.doi.org/10.1016/0921-5093(91)90722-y.

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Jiang, Jing-Wei, and Wei-Xi Huang. "Hydrodynamic design of an advanced submerged propulsion." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 233, no. 18 (June 24, 2019): 6367–82. http://dx.doi.org/10.1177/0954406219860166.

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A new kind of advanced submerged propulsion is automatically modeled and analyzed based on the hydrodynamic and cavitation performance. A mathematical algorithm is proposed to describe the fusion-duct, which is controlled by several design parameters, including section diameters, section lengths, and inlet shape and aspect ratio. The hydrodynamic performances of 13 cases with different parameter combinations are numerically simulated. The simulation is carried out by solving the Reynolds Average Navier-Stokes equations with STAR-CCM+, and the SST k-ω turbulence model is applied. The curves of rotor thrust and torque, stator thrust and duct resistance, along with efficiency and merit coefficient are obtained as functions of the advance coefficient and are compared for different cases. Meanwhile, the pressure distribution on both sides of the rotor and the flow field of intermediate section are systematically analyzed. To guide future designs, an impact factor is further defined and calculated to quantify the effects of different parameters. The results indicate that the section diameters have the most significant influence on hydrodynamic and cavitation performances.
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Dissertations / Theses on the topic "Advanced Propulsion"

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Khayms, Vadim. "Advanced propulsion for microsatellites." Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/8824.

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Thesis (Ph.D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2000.
Includes bibliographical references (leaves 162-166).
Microsatellites have become increasingly popular in recent years as they offer significant cost savings, higher reliability, and are generally more affordable for a large variety of commercial applications. Since many microsatellite missions require considerable propulsion capabilities, miniaturization of the propulsion subsystem is critical in the design of most miniature spacecraft. A broad range of existing propulsion technologies have been considered for the purpose of identifying those devices which maintain high performance at small scale. Scaling laws were developed for each of the selected devices so as to preserve, whenever possible, the basic non-dimensional quantities which ultimately determine the performance of the individual thrusters at small scale. Hall thrusters were initially identified as most promising. In an effort to miniaturize the Hall thruster, a number of complications have been encountered. Some of the most troublesome were higher magnetic field requirements, larger internal heat fluxes and temperatures, and difficulties associated with the manufacturing of the various miniaturized components. In order to validate the proposed scaling laws, a 50 Watt Hall thruster has been designed, manufactured, and tested in a vacuum tank. Results of the experimental testing indicate that, although the maximum thrust levels obtained were on the order of 1.8 mN, about two thirds of the nominal design value, the propellant utilization efficiencies were unexpectedly low at approximately 40%. Close examination of the magnetic assembly has shown that the tip of the iron center pole was overheating during operation due to the insufficient heat conduction. The tip temperatures were estimated to reach 900°C, exceeding the Curie point of iron. As a consequence of the change in the magnetic field profile and the resultant leakage of electrons, the observed ionization fraction and, therefore, the utilization efficiency were lower than expected. Despite the low efficiencies, which were most likely caused by the design imperfections rather than physical limitations, the effort to miniaturize a Hall thruster has provided a number of useful insights for any such attempts in the future. Most importantly, this work has highlighted the generic difficulty, common to all plasma thrusters, associated with the increase of the plasma density as the scale of the device is reduced. The consequences of strict scaling, most notably the higher particle fluxes which cause an increase in the erosion rates and significant loss of operating life at small scale, created a strong incentive to search for propulsion schemes which avoid ionization by electron bombardment. In the quest for a more durable device that could operate at low power, yet provide sufficient operating life to be of practical interest, colloidal thrusters were considered for miniaturization. These are representatives of a technology of electrostatic accelerators which does not rely on ionization in the gas phase and, hence, their operating life is not compromised at small scale. In addition to their intrinsically small dimensions and extremely low operating power levels, eliminating the need for further "miniaturization", colloidal thrusters possess a number of desirable characteristics which make them ideal for many microsatellite missions. Although the physics of electrospray emitters has been studied for decades, many of the mechanisms responsible for the formation of charged jets are still poorly understood. In order to gain further insight, a semi-analytical fluid model was developed to predict the effects of fluid's viscosity on the flow pattern. Results of the analysis indicate that over a broad range of operating conditions viscous shear flow is insignificant in the vicinity of the jet irrespective of the fluid's viscosity. In an attempt to further understand the physics of colloidal thrusters, specifically the effects of internal pressure, electrode geometry, and the internal electrostatic fields on the processes involved in the formation of charged jets, a detailed electrohydrodynamic model was formulated. A numerical scheme was developed to solve for the shape of the fluid meniscus given a prescribed set of operating conditions, fluid properties, and electrode configurations. Intermediate solutions for the conical region have already been obtained, however, convergence in the vicinity of the jet requires further studies. A fully developed model promises to provide valuable information and guidance in the design of colloidal thrusters.
by Vadim Khayms.
Ph.D.
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Doulgeris, Georgios C. "Modelling & integration of advanced propulsion systems." Thesis, Cranfield University, 2008. http://hdl.handle.net/1826/2812.

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This research study focuses on the design of advanced propulsion cycles, having as primary design goal the improvement on noise emissions and fuel consumption. In this context, a preliminary cycle design method has been developed and applied on four novel propulsion systems; ultra high bypass ratio, recuperated, intercooled-recuperated, constant volume combustion turbofans. The analysis has shown significant improvement in jet noise, and fuel consumption, as a result of high bypass ratio. Additionally, a comparison to future fuel-optimised cycle has revealed the trade-off between noise emissions and fuel consumption, where a reduction of ~30dBs in jet noise may be achieved in the expense of ~10% increase of mission fuel. A second aspect of this study is the integration of the propulsion system for improving fan noise. A novel approach is followed, by half-embedding the turbofan in the upper surface of the wing of a Broad Delta airframe. Such an installation aids in noise reduction, by providing shielding to component (fan) noise. However, it leads to significant inlet distortion levels. In order to assess the effect of installation-born distortion on performance an enhanced fan representation model has been developed, able to predict fan and overall engine performance sensitivity to three-dimensional distorted inlet flow. This model that comprises parallel compressor theory and streamline curvature compressor modelling, has been used for proving a linear relation between the loss in fan stability margins and engine performance. In this way, the design engineer can take into consideration distortion effects on off-design performance, as early as, at the stage of preliminary cycle design.
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Pêgo, João Pedro Gomes Moreira. "Advanced fluid mechanics studies of ship propulsion systems." [S.l.] : [s.n.], 2007. http://deposit.ddb.de/cgi-bin/dokserv?idn=983754853.

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Najafi, Saatlou Esmail. "Techno-economic environmental assessment of advanced intercooled propulsion systems." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/9600.

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A tool based on a Techno-economic and Environmental Risk Assessment (TERA) framework is useful at the preliminary stage of an aero engine design process, to conceive and assess engines with minimum environmental impact and lowest cost of ownership, in a variety of emission legislation and taxation policy scenarios. This research was performed as part of the EU FP6 New Aero engine Core concepts (NEWAC) programme which was established to assess the potential of innovative gas turbine core technologies to enhance thermal efficiency thereby reducing CO2 emissions and fuel consumption. A representative prediction of engine life and mission fuel burn at the earliest possible design stage is a crucial task that can provide an indication of the approximate overall engine direct operating costs. Two aero engines, a conventional turbofan and a conceptual intercooled turbofan, were assessed and optimised using the TERA approach to identify the designs that provided the maximum time between overhaul (and therefore the minimum maintenance costs). In order to perform these assessments (which included sensitivity and parametric analyses, and optimisation studies) several models were developed and integrated in an optimisation framework. A substantial effort was devoted to the development of a detailed lifing model that calculates the engine life with a reasonable level of accuracy by integrating physics based oxidation, creep and fatigue models. The results obtained from the study demonstrate that an engine optimised for maximum time between overhaul requires a lower overall pressure ratio and specific thrust but this comes at the cost of lower thermal efficiency and therefore higher mission fuel burn. The main contribution to knowledge of this work is a multidisciplinary TERA assessment of a novel intercooled conceptual aero engine. Particular emphasis is placed on the design space exploration and optimisation studies to identify the designs that may offer the largest time between overhaul. The consequent implications therefore this may have on mission fuel burn and direct operating costs. In addition to refining the various TERA models, one of the main recommendations for further work is to optimise the engines for minimum direct operating cost to identify the best economic compromise between engine life and mission fuel burn. This can be done by considering different fuel prices and under a variety of hypothetical emission taxation scenarios, to identify the circumstances in which intercooled engine technology may become economically viable.
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McClure, Erin Kathleen. "An evolving-requirements technology assessment process for advanced propulsion concepts." Diss., Available online, Georgia Institute of Technology, 2006, 2006. http://etd.gatech.edu/theses/available/etd-07062006-101749/.

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Thesis (Ph. D.)--Aerospace Engineering, Georgia Institute of Technology, 2007.
Danielle Soban, Committee Member ; Dimitri Mavris, Committee Chair ; Alan Porter, Committee Member ; Gary Seng, Committee Member ; Daniel Schrage, Committee Member.
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Hartwig, Jason W. "Liquid Acquisition Devices for Advanced In-Space Cryogenic Propulsion Systems." Case Western Reserve University School of Graduate Studies / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=case1396562473.

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Brochard, Paul Eugene. "Analysis of simulation tools for the study of advanced marine power systems." Thesis, Monterey, Calif. : Naval Postgraduate School, 1992. http://handle.dtic.mil/100.2/ADA257338.

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Thesis (M.S. in Electrical Engineering)--Naval Postgraduate School, September 1992.
Thesis Advisor: Williams, Stephen M. "September 1992." Description based on title screen as viewed on March 10, 2009. Includes bibliographical references (p. 103-105). Also available in print.
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Kirner, Rudi. "An investigation into the benefits of distributed propulsion on advanced aircraft configurations." Thesis, Cranfield University, 2013. http://dspace.lib.cranfield.ac.uk/handle/1826/8599.

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Radical aircraft and propulsion system architecture changes may be required to continue historic performance improvement rates as current civil aircraft and engine technologies mature. Significant fuel-burn savings are predicted to be achieved through the Distributed Propulsion concept, where an array of propulsors is distributed along the span of an aircraft to ingest boundary layer air and increase propulsive efficiency. Studies such as those by NASA predict large performance benefits when integrating Distributed Propulsion with the Blended Wing Body aircraft configuration, as this planform geometry is particularly suited to the ingestion of boundary layer air and the fans can be redesigned to reduce the detrimental distortion effects on performance. Additionally, a conventional aircraft with Distributed Propulsion has not been assessed in public domain literature and may also provide substantial benefits. A conceptual aircraft design code has been developed to enable the modelling of conventional and novel aircraft. A distributed fan tool has been developed to model fan performance, and a mathematical derivation was created and integrated with the fan tool to enable the boundary layer ingestion modelling. A tube & wing Distributed Propulsion aircraft with boundary layer ingestion has been compared with a current technology reference aircraft and an advanced turbofan aircraft of 2035 technology. The advanced tube & wing aircraft achieved a 27.5% fuel-burn reduction relative to the baseline aircraft and the Distributed Propulsion variant showed fuel efficiency gains of 4.1% relative to the advanced turbofan variant due to a reduced specific fuel consumption, produced through a reduction in distributed fan power requirement. The Blended Wing Body with Distributed Propulsion was compared with a turbofan variant reference aircraft and a 5.3% fuel-burn reduction was shown to be achievable through reduced core engine size and weight. The Distributed Propulsion system was shown to be particularly sensitive to inlet duct losses. Further investigation into the parametric sensitivity of the system revealed that duct loss could be mitigated by altering the mass flow and the percentage thrust produced by the distributed fans. Fuel-burn could be further reduced bydecreasing component weight and drag, through decreasing the fan and electrical system size to below that necessary for optimum power or specific fuel consumption.
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Fereirra, César Leal. "Modelling and real-time simulation of an advanced marine full-electrical propulsion system." Thesis, University College London (University of London), 2006. http://discovery.ucl.ac.uk/1445446/.

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After being consolidated as the preferred propulsion system for cruise ships, integrated full electrical propulsion (LFEP) is now being considered as the natural choice for the future warship vessels. The United States and the United Kingdom are developing parallel projects in order to gain broad knowledge of this new propulsion technology. The Royal Navy's Type 45 Destroyer, due to enter into service in 2007, will set the course by development and acquisition of practical experience for the Future Surface Combatant Ship (FSC) and the Future Aircraft Carrier (CVF) programmes, both envisaging the use of integrated full-electrical propulsion. One main step towards this new technology is the computational simulation of each independent component and of the system as a whole, to de-risk and refine the design. The present project aims to develop a computational model of an advanced marine integrated full-electrical propulsion system such as the one being proposed for the Royal Navy's Type 45 Destroyer. The main focus is the development of new advanced electrical equipment models, which are the building blocks of the propulsion system, to be integrated with some existing models from various earlier investigations, to achieve an Integrated Full Electric Propulsion System Model. Two particular aspects of this work are: The construction of an algorithm for the 15-phase induction motor capable of processing the resulting currents at the machine more precisely than the traditional -algorithms, taking into account eventual unbalances and faults in the voltage supply The development of a Direct Torque and Flux Control algorithm for the 15-phase system, capable of maintaining the stability of the induction motor under severe transients, such as the crash-stop manoeuvring situation. The work concludes by assessing the performance of the proposed advanced marine propulsion system predicting its likely behaviour across a number of important scenarios.
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Wilson, Elizabeth (Betsy). "Precious Bits: Frame Synchronization in Jet Propulsion Laboratory's Advanced Multi-Mission Operations System (AMMOS)." International Foundation for Telemetering, 2001. http://hdl.handle.net/10150/607694.

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International Telemetering Conference Proceedings / October 22-25, 2001 / Riviera Hotel and Convention Center, Las Vegas, Nevada
The Jet Propulsion Laboratory’s (JPL) Advanced Multi-Mission Operations System (AMMOS) system processes data received from deep-space spacecraft, where error rates are high, bit rates are low, and every bit is precious. Frame synchronization and data extraction as performed by AMMOS enhance data acquisition and reliability for maximum data return and validity. Unique aspects of data phase determination, sync acquisition and sync loss and other bit-level topics are covered.
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Books on the topic "Advanced Propulsion"

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Timnat, Y. M. Advanced airbreathing propulsion. Malabar, Fla: Krieger Pub. Co., 1996.

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Timnat, Y. M. Advanced chemical rocket propulsion. London: Academic Press, 1987.

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Timnat, Y. M. Advanced chemical rocket propulsion. London: Academic Press, 1987.

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Tajmar, Martin. Advanced Space Propulsion Systems. Vienna: Springer Vienna, 2003. http://dx.doi.org/10.1007/978-3-7091-0547-4.

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O'Brien, C. J. Advanced earth-to-orbit propulsion concepts. New York: AIAA, 1986.

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Diehl, Larry A. Advanced technology for future space propulsion systems. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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Halford, Gary R. Thermal fatigue durability for advanced propulsion materials. [Washington, DC]: National Aeronautics and Space Administration, 1990.

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Advanced propulsion systems for urban rail vehicles. Englewood Cliffs, N.J: Prentice-Hall, 1985.

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Szuch, John R. Application of advanced computational technology to propulsion CFD. [Washington, DC]: National Aeronautics and Space Administration, 1988.

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American Institute of Aeronautics and Astronautics and European Space Agency, eds. Advanced propulsion systems and technologies, today to 2020. Reston, Va: American Institute of Aeronautics and Astronautics, 2008.

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Book chapters on the topic "Advanced Propulsion"

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Bentley, Matthew A. "Advanced Propulsion." In Spaceplanes, 105–23. New York, NY: Springer New York, 2009. http://dx.doi.org/10.1007/978-0-387-76510-5_8.

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Tajmar, Martin. "Propulsion Fundamentals." In Advanced Space Propulsion Systems, 3–22. Vienna: Springer Vienna, 2003. http://dx.doi.org/10.1007/978-3-7091-0547-4_2.

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Tajmar, Martin. "Propellantless Propulsion." In Advanced Space Propulsion Systems, 107–14. Vienna: Springer Vienna, 2003. http://dx.doi.org/10.1007/978-3-7091-0547-4_8.

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Tajmar, Martin. "Breakthrough Propulsion." In Advanced Space Propulsion Systems, 115–22. Vienna: Springer Vienna, 2003. http://dx.doi.org/10.1007/978-3-7091-0547-4_9.

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Tajmar, Martin. "Nuclear Propulsion Systems." In Advanced Space Propulsion Systems, 57–72. Vienna: Springer Vienna, 2003. http://dx.doi.org/10.1007/978-3-7091-0547-4_5.

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Tajmar, Martin. "Chemical Propulsion Systems." In Advanced Space Propulsion Systems, 23–42. Vienna: Springer Vienna, 2003. http://dx.doi.org/10.1007/978-3-7091-0547-4_3.

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Tajmar, Martin. "Electric Propulsion Systems." In Advanced Space Propulsion Systems, 73–98. Vienna: Springer Vienna, 2003. http://dx.doi.org/10.1007/978-3-7091-0547-4_6.

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Johnson, Les, and Tiffany Lockett. "Advanced Materials for In-Space Propulsion." In Aerospace Materials and Applications, 699–748. Reston ,VA: American Institute of Aeronautics and Astronautics, Inc., 2018. http://dx.doi.org/10.2514/5.9781624104893.0699.0748.

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Tajmar, Martin. "Micropropulsion." In Advanced Space Propulsion Systems, 99–105. Vienna: Springer Vienna, 2003. http://dx.doi.org/10.1007/978-3-7091-0547-4_7.

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Tajmar, Martin. "Launch Assist Technologies." In Advanced Space Propulsion Systems, 43–56. Vienna: Springer Vienna, 2003. http://dx.doi.org/10.1007/978-3-7091-0547-4_4.

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Conference papers on the topic "Advanced Propulsion"

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Woodcock, Gordon, Dave Byers, Leslie Alexander, and Al Krebsbach. "Advanced Chemical Propulsion Study." In 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-3494.

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Gerrish Jr., Harold, George Schmidt, and Stephen Rodgers. "Advanced propulsion research at Marshall's Propulsion Research Center." In 37th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3519.

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FITZGIBBON, CRAIG, BOB FORD, and MITCH WEATHERLY. "Advanced recovery techniques for advanced launch systems." In 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2401.

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ADAMSON, A., and A. STUART. "Propulsion for advanced commercial transports." In Aircraft Design Systems and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-3061.

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Vilja, John, and John Vilja. "Rocketdyne advanced propulsion systems overview." In 33rd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3309.

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Portz, Ronald, David Krismer, Frank Lu, Kim Wilson, Leslie Alexander, Jack Chapman, and Chris England. "Advanced Chemical Propulsion System Study." In 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-5433.

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Popa-Samil, Liviu. "Advanced nuclear space propulsion systems." In 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-6039.

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Cruse, T. A., J. F. Unruh, Y. T. Wu, and S. V. Harren. "Probabilistic Structural Analysis for Advanced Space Propulsion Systems." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-127.

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The paper reports on recent extensions to ongoing research into probabilistic structural analysis modeling of advanced space propulsion system hardware. The advances concern probabilistic dynamic loading, and probabilistic nonlinear material behavior. In both cases, the reported work represents a significant advance in the state-of-the-art for these topics. Random, or probabilistic loading is normally concerned with the loading described in power spectral density (PSD) terms. The current work describes a method for incorporating random PSD’s along with random material properties, damping, and structural geometry. The probabilistic material response is concerned with the prediction of nonlinear stress-strain behavior for physical processes that can be linked to the original microstructure of the material. Such variables as grain size and orientation, grain boundary strength, etc. are treated as random, initial variables in generating stochastic stress-strain curves. The methodology is demonstrated for a creep simulation.
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WETCH, JOSEPH, EDWARD BRITT, JOHN LAWLESS, and ANATOLII KOROTEEV. "Electric propulsion applications." In Conference on Advanced SEI Technologies. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3445.

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OBRIEN, C., and A. KOBAYASHI. "Advanced earth-to-orbit propulsion concepts." In 22nd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1386.

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Reports on the topic "Advanced Propulsion"

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Davis, Eric W. Advanced Propulsion Study. Fort Belvoir, VA: Defense Technical Information Center, February 2004. http://dx.doi.org/10.21236/ada426465.

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Choueiri, Edgar, Mark A. Cappelli, Manuel Martinez-Sanchez, Ashley Hallock, Stephen Gildea, and Taylor Matlock. Advanced Plasma Propulsion. Fort Belvoir, VA: Defense Technical Information Center, November 2011. http://dx.doi.org/10.21236/ada564078.

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Borman, G., M. Corradini, P. Farrell, D. Foster, J. Martin, and C. Rutland. Center for Advanced Propulsion Systems. Fort Belvoir, VA: Defense Technical Information Center, February 1993. http://dx.doi.org/10.21236/ada263588.

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Borman, G. L. Center for Advanced Propulsion (Equipment). Fort Belvoir, VA: Defense Technical Information Center, August 1991. http://dx.doi.org/10.21236/ada244387.

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Epstein, Alan H., and Choon S. Tan. Advanced and Adaptable Military Propulsion. Fort Belvoir, VA: Defense Technical Information Center, January 2008. http://dx.doi.org/10.21236/ada476486.

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Borman, G. L. Center for Advanced Propulsion Systems (Fellowship). Fort Belvoir, VA: Defense Technical Information Center, August 1992. http://dx.doi.org/10.21236/ada260571.

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Oldenborg, R., J. Early, and C. Lester. Advanced ignition and propulsion technology program. Office of Scientific and Technical Information (OSTI), November 1998. http://dx.doi.org/10.2172/676952.

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Stutrud, Jeffrey S. Advanced Propulsion Concepts and Component Technologies. Fort Belvoir, VA: Defense Technical Information Center, July 2007. http://dx.doi.org/10.21236/ada474918.

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Kare, J. T. Ground-to-orbit laser propulsion: Advanced applications. Office of Scientific and Technical Information (OSTI), January 1990. http://dx.doi.org/10.2172/6203669.

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Nusca, Michael J. High-Performance Computing and Simulation for Advanced Armament Propulsion. Fort Belvoir, VA: Defense Technical Information Center, June 2004. http://dx.doi.org/10.21236/ada424252.

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