Bibliografías temáticas / Propulsion systems

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Literatura académica sobre el tema "Propulsion systems"

Autor: Grafiati

Publicado: 4 de junio de 2021

Última modificación: 27 de julio de 2024

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Artículos de revistas sobre el tema "Propulsion systems"

Fish, Frank E. "Advantages of Natural Propulsive Systems". Marine Technology Society Journal 47, n.º 5 (1 de septiembre de 2013): 37–44. http://dx.doi.org/10.4031/mtsj.47.5.2.

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AbstractThe screw propeller has been the mainstay of marine propulsion, but new developments in biomimetic propulsion can provide advantages in terms of speed, maneuverability, efficiency, and stealth. The diversity of aquatic animals provides designs for drag-based paddling and lift-based oscillatory hydrofoils that can be incorporated into engineered propulsive systems for enhanced performance. While the screw propeller will remain the prominent propulsive device, the choice of alternative biomimetic propulsive systems will be dependent on particular applications, where the specifications dictate improved performance criteria.

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Kaul, Stefan, Paul Mertes y Lutz Müller. "Application-optimised propulsion systems for energy-efficient operation". Ciencia y tecnología de buques 5, n.º 9 (23 de julio de 2011): 87. http://dx.doi.org/10.25043/19098642.53.

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Today, optimal propellers are designed by using advanced numerical methods. Major revolutionary improvements cannot be expected. More essential are the design conditions and the optimal adaptation of the propulsion system according to the operational requirements. The selection and optimisation of the propulsion system based on a systematic analysis of the ship’s requirements and the operation profile are the prerequisites for reliable and energy-efficient propulsion. Solutions are presented, which accommodate these issues with a focus on steerable rudderpropellers. Considerations include the efficiency potential of the propulsor itself, optimisation of the engine propeller interaction, and optimisation of a demandresponsive energy supply. The propeller-thruster interaction is complex, but offers some potential for optimisation. Results of examinations show this. The power distribution between multiple propellers at high loads of limited propeller diameters increases the efficiency. This can be done by double-propeller systems like the SCHOTTEL TwinPropeller or by distributing the power on several thrusters. This distributed propulsion offers economic operation and an increased lifetime by means of the demandresponsive use of energy. An efficiency-optimized electric motor instead of the upper gear box reduces the mechanical losses in the case of diesel-electric propulsion. An example: the SCHOTTEL CombiDrive.

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Pulatov, Valentine. "Magnetic propulsion systems". Progress in Aerospace Sciences 37, n.º 3 (abril de 2001): 245–61. http://dx.doi.org/10.1016/s0376-0421(01)00006-9.

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Achkasov, A. N., G. I. Grechko y V. A. Shishkin. "Nuclear propulsion systems". Atomic Energy 103, n.º 1 (julio de 2007): 532–36. http://dx.doi.org/10.1007/s10512-007-0084-1.

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Leśniewski, Wojciech, Daniel Piątek, Konrad Marszałkowski y Wojciech Litwin. "Small Vessel with Inboard Engine Retrofitting Concepts; Real Boat Tests, Laboratory Hybrid Drive Tests and Theoretical Studies". Energies 13, n.º 10 (20 de mayo de 2020): 2586. http://dx.doi.org/10.3390/en13102586.

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The development of modern technologies and their increasing availability, as well as the falling costs of highly efficient propulsion systems and power sources, have resulted in electric or hybrid propulsions systems’ growing popularity for use on watercraft. Presented in the paper are design and lab tests of a prototype parallel hybrid propulsion system. It describes a concept of retrofitting a conventionally powered nine meter-long vessel with the system, and includes results of power and efficiency measurements, as well as calculations of the vessel’s operating range under the propulsion of its electric motor. The concept of adding of a solar panels array was studied.

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Ibrahim, K., S. Sampath y D. Nalianda. "Voltage synchronisation for hybrid-electric aircraft propulsion systems". Aeronautical Journal 125, n.º 1291 (22 de julio de 2021): 1611–30. http://dx.doi.org/10.1017/aer.2021.56.

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AbstractIncreasing demand for commercial air travel is projected to have additional environmental impact through increased emissions from fuel burn. This has necessitated the improvement of aircraft propulsion technologies and proposal of new concepts to mitigate this impact. The hybrid-electric aircraft propulsion system has been identified as a potential method to achieve this improvement. However, there are many challenges to overcome. One such challenges is the combination of electrical power sources and the best strategy to manage the power available in the propulsion system. Earlier methods reviewed did not quantify the mass and efficiency penalties incurred by each method, especially at system level. This work compares three power management approaches on the basis of feasibility, mass and efficiency. The focus is on voltage synchronisation and adaptation to the load rating. The three methods are the regulated rectification, the generator field flux variation and the buck-boost. This comparison was made using the propulsion system of the propulsive fuselage aircraft concept as the reference electrical configuration. Based on the findings, the generator field flux variation approach appeared to be the most promising, based on a balance of feasibility, mass and efficiency, for a 2.6MW system.

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Islam, Mohammed F., Brian Veitch, Neil Bose y Pengfei Liu. "Numerical Study of Hub Taper Angle on Podded Propeller Performance". Marine Technology and SNAME News 43, n.º 01 (1 de enero de 2006): 1–10. http://dx.doi.org/10.5957/mt1.2006.43.1.1.

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Presently, the majority of podded propulsion systems are of the pulling type, because this type provides better hydrodynamic efficiency than the pushing type. There are several possible explanations for the better overall performance of a puller-type podded propulsor. One is related to the difference in hub taper angle. Puller and pusher propellers have opposite hub taper angles, hence different hub and blade root shape. These differences cause changes in the flow condition and possibly influence the overall performance. The current study focuses on the variation in performance of pusher and puller propellers with the same design of blade sections, but different hub taper angles. A hyperboloidal low-order source-doublet steady/unsteady time domain panel method code, PROPELLA, was modified and used to evaluate effects of hub taper angle on the open water propulsive performance of some fixed-pitch screw propellers used in podded propulsion systems. Major findings include good agreement between predictions using the modified code and measurements, significant effects of hub taper angle on propulsive performance of tapered hub propellers, and noticeable effects of hub taper angle on sectional pressure distributions of tapered hub propeller blades.

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Arias, Jonathan, Francisco Martinez, Edgar Cando y Esteban Valencia. "Towards More Efficient Electric Propulsion UAV Systems Using Boundary Layer Ingestion". Drones 7, n.º 12 (21 de noviembre de 2023): 686. http://dx.doi.org/10.3390/drones7120686.

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The implementation of distributed propulsion and boundary layer ingestion for unmanned aerial vehicles represents various challenges for the design of embedded ducts in blended wing body configurations. This work explores the conceptual design and evaluation of DP configurations with BLI. The aerodynamic integration of each configuration is evaluated following a proposed framework, including simulation analysis. Power saving coefficient and propulsive efficiency were compared against a baseline podded case. The results show the optimal propulsion configuration for the BWB UAV obtaining 3.95% of power benefit and propulsive efficiency (ηp>80%). Indeed, the aerodynamic integration effects for the proposed design maintain the BWB’s aerodynamic efficiency, which will contribute to longer endurance and better performance.

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Gallops, G. W., C. F. Weiss y R. A. Carlton. "Integrated Propulsion System Requirements for Control of STOVL Aircraft". Journal of Engineering for Gas Turbines and Power 113, n.º 1 (1 de enero de 1991): 60–67. http://dx.doi.org/10.1115/1.2906531.

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This paper describes an evaluation of propulsion system requirements and capability for a Short Take-Off/Vertical Landing (STOVL) aircraft employing modulation of the propulsive lift distribution for pitch and roll control in hover. The effects of propulsive lift nozzle configuration and propulsion system dynamic response were evaluated using a combined system simulation consisting of a six degree of freedom aircraft model, engine model, and integrated flight/propulsion control. The response and stability of propulsive lift control are compared with control by reaction jets supplied by engine bleed. Aircraft performance is demonstrated in simulated STOVL maneuvers using a dynamic pilot model. The conclusion of this study is that propulsive lift control of aircraft pitch and roll is feasible and can provide as much as a 10 percent increase in engine lift rating over systems that employ reaction control alone. The dynamic response of practical propulsive lift configurations, however, is less than that of reaction control configurations, which must be offset through integration of the propulsion system and its control.

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Kolodziejski, Marcin y Iwona Michalska-Pozoga. "Battery Energy Storage Systems in Ships’ Hybrid/Electric Propulsion Systems". Energies 16, n.º 3 (19 de enero de 2023): 1122. http://dx.doi.org/10.3390/en16031122.

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The shipping industry is going through a period of technology transition that aims to increase the use of carbon-neutral fuels. There is a significant trend of vessels being ordered with alternative fuel propulsion. Shipping’s future fuel market will be more diverse, reliant on multiple energy sources. One of very promising means to meet the decarbonisation requirements is to operate ships with sustainable electrical energy by integrating local renewables, shore connection systems and battery energy storage systems (BESS). With the increasing number of battery/hybrid propulsion vessels in operation and on order, this kind of vessel propulsion is becoming more common, especially in the segment of short range vessels. This paper presents review of recent studies of electrification or hybridisation, different aspects of using the marine BESS and classes of hybrid propulsion vessels. It also reviews several types of energy storage and battery management systems used for ships’ hybrid propulsion. The article describes different marine applications of BESS systems in relation to peak shaving, load levelling, spinning reserve and load response. The study also presents the very latest developments of hybrid/electric propulsion systems offered by leading maritime market manufacturers.

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Tesis sobre el tema "Propulsion systems"

Lemay, Scott A. "Microelectromechanical propulsion systems for spacecraft". Thesis, Monterey, California. Naval Postgraduate School, 2002. http://hdl.handle.net/10945/5883.

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This is a survey of current research on micropropulsion options for very small satellites (less than ten kilogram). The concentration of research and performance evaluations utilize Micro Systems Technology (MST) and Micro Electromechanical Systems technology (MEMS) integrated with existing theories. State of the art methods used for the design and manufacturing of MEMS devices are included to provide a size perspective of microthruster technology. Nine viable microthruster options are presented, including a detailed performance analysis of the Pulsed Plasma Thruster. Exploration of the future role of micropropulsion in space is the influential factor benefiting research efforts on extremely small scale microthrusters. Significant background information on astrodynamics is included to assist the intended reader: a student of Engineering Science with interest in the Aerospace Propulsion Industry.

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Lemay, Scott A. "Microelectromecanical propulsion systems for spacecraft". Monterey, California: Naval Postgraduate School, 2002. http://hdl.handle.net/10945/9767.

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Approved for public release; distribution is unlimited
This is a survey of current research on micropropulsion options for very small satellites (less than ten kilogram). The concentration of research and performance evaluations utilize Micro Systems Technology (MST) and Micro Electromechanical Systems technology (MEMS) integrated with existing theories. State of the art methods used for the design and manufacturing of MEMS devices are included to provide a size perspective of microthruster technology. Nine viable microthruster options are presented, including a detailed performance analysis of the Pulsed Plasma Thruster. Exploration of the future role of micropropulsion in space is the influential factor benefiting research efforts on extremely small scale microthrusters. Significant background information on astrodynamics is included to assist the intended reader: a student of Engineering Science with interest in the Aerospace Propulsion Industry.

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Cazenave, Timothee. "Peak-seeking control of propulsion systems". Thesis, Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/44805.

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Propulsion systems like Turboprop engines are generally designed to operate at a narrow range of optimum steady state performance conditions. However, these conditions are likely to vary in an unpredictable manner according to factors such as components aging, structural damages or even the operating environment. Over time, inefficiencies could add up and can lead to expensive fuel consumption or faster component aging. This thesis presents a self-optimizing control scheme, referred as Peak-seeking control, applied to propulsion systems similar to Turboprop engines. Using an extended Kalman filter, the Peak-seeking method is able drive the system to an optimal condition based only on measurements. No prior knowledge of the engine dynamics is required which make the Peak-seeking technique easy to implement and also allow for modularity in the engine design. This study is performed on both a turboprop and a DC motor driving a variable pitch propeller and considers several performance functions to optimize.

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Mejergren, Henrik. "Comparison of propeller-driven propulsion systems". Thesis, KTH, Skolan för teknikvetenskap (SCI), 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-152804.

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Global warming caused by combustion of fossil fuels is a hot topic in today’s society and the world is constantly trying to makes steps towards a brighter tomorrow with stricter environmental laws and research of alternative fuels. A great propulsion system is however not great solely of it being environmental friendly, it must also achieve other requirements. A comparison using different propulsion systems and different fuel types has been made and evaluated in four different categories; power; range; cost and environmental impact. The process of scientifically compare systems using given attributes is a big part of the study and is hoped to yield inspiration to the reader to apply to their own application, not necessarily using the same categories. The result has been assembled in a matrix and depending on what category one prefers the most, different results are presented. A clear observation is a lack of range for all of the systems using electricity due to the low energy density compared to fossil fuels. Hydrogen fuel cells and ICE are however constrained by the volume required to store hydrogen but applications can surely be found where the great gravimetric energy-density can be utilized at its full potential. The future of alternative fuels and propulsion systems are looking great checking the improvements of technology on electrical components such as batteries, fuel cells and solar cells the last 10 years. The improvements not only affecting performance such as increased energy-density and power but also cost, making them more desired by the common man.

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Friedrich, Christian. "Hybrid-electric propulsion systems for aircraft". Thesis, University of Cambridge, 2015. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.708913.

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Saunders, Thomas E. "Performance of small thrusters and propulsion systems". Thesis, Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA231482.

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Thesis (M.S. in Mechanical Engineering)--Naval Postgraduate School, March 1990.
Thesis Advisor(s): Healey, A.J. Second Reader: Reid, Glenn N. "March 1990." Description based on signature page as viewed on October 21, 2009. DTIC identifier(s): AUV(Autonomous Underwater Vehicles), thrusters, underwater vehicles, self operation, marine propellers, thrust, shipmotion, thesis. Author(s) subject terms: Autonomous Underwater Vehicle, AUV, Unmanned Untethered Underwater Vehicle, UUV, underwater vehicle systems design, propulsors, small thrusters. Includes bibliographical references (p. 73). Also available online.

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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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Bost, Alexander Connor Larkin. "Materials for small-scale space propulsion systems". Thesis, Massachusetts Institute of Technology, 2017. http://hdl.handle.net/1721.1/112412.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 91-92).
This thesis explores a variety of materials and methods for creating emitter arrays for the ion electrospray propulsion system (iEPS), a compact, efficient, and scalable space propulsion system for use in a wide range of space missions. The increasing utilization of small, cheap, easy-to-launch satellites known as CubeSats has spurred demand for a propulsion system which exists at the nexus of high power efficiency, low mass, surface area, and volume, and high specific impulse. iEPS has demonstrated a unique potential to satisfy all of these stringent design requirements in a way no presently existing propulsion system can. The first part of this work explores utilizing microelectromechanical systems (MEMS) processing to increase the thrust density of iEPS. Silicon molds were designed and manufactured with differing emission site size and spacing. Additionally, a variety of materials were tested with the aim of forming a porous network within the molds prior to selective removal of the mold. A molded array is successfully fired as a result of these research efforts. The second part of this work explores creation of porous substrates for use with an existing laser ablation method of creating emitter arrays. The first iEPS thrusters tested in space used porous borosilicate glass emitter chips, which demonstrated shortcomings in terms of material uniformity, pore size, and ionic liquid fuel containment. This work explores materials and methods for improving all of these and demonstrates the successful firing of an array made by sintering a silicon dioxide nano-bead powder.
by Alexander Connor Larkin Bost.
S.M.

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Schoeffler, Lara Elaine. "Orbital Dynamics of Space Nuclear Propulsion Systems". Case Western Reserve University School of Graduate Studies / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=case1618332162764726.

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Ling, Jack C. L. "Compressors for miniature unmanned aerospace propulsion systems". Phd thesis, School of Aerospace, Mechanical and Mechatronic Engineering, 2009. http://hdl.handle.net/2123/6430.

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Libros sobre el tema "Propulsion systems"

Guzzella, Lino y Antonio Sciarretta. Vehicle Propulsion Systems. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-35913-2.

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Aerospace propulsion systems. Singapore: Wiley, 2010.

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Ten-Huei, Guo, Duyar Ahmet y United States. National Aeronautics and Space Administration., eds. Identification of propulsion systems. [Washington, D.C.]: NASA, 1991.

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D, Brown Charles. Spacecraft propulsion. Washington, DC: American Institute of Aeronautics and Astronautics, 1996.

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D, Brown Charles. Spacecraft propulsion. Washington, DC: American Institute of Aeronautics and Astronautics, 1995.

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Czysz, Paul A. y Claudio Bruno. Future Spacecraft Propulsion Systems. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-88814-7.

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MacIsaac, Bernie y Roy Langton. Gas Turbine Propulsion Systems. Chichester, UK: John Wiley & Sons, Ltd, 2011. http://dx.doi.org/10.1002/9781119975489.

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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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Lewis Research Center. Aeropropulsion Facilities & Experiments Division, ed. The Propulsion Systems Laboratory. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, Aeropropulsion Facilities & Experiments Division, 1991.

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Lewis Research Center. Aeropropulsion Facilities & Experiments Division., ed. The Propulsion Systems Laboratory. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, Aeropropulsion Facilities & Experiments Division, 1991.

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Capítulos de libros sobre el tema "Propulsion systems"

Palocz-Andresen, Michael. "Propulsion Systems". En Decreasing Fuel Consumption and Exhaust Gas Emissions in Transportation, 121–34. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-11976-7_8.

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Moss, J. Barrie y John P. W. Stark. "Propulsion Systems". En Spacecraft Systems Engineering, 177–219. Chichester, UK: John Wiley & Sons, Ltd, 2011. http://dx.doi.org/10.1002/9781119971009.ch6.

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Nixon, John. "Propulsion Systems". En Modern English for Aeronautics and Space Technology, 51–63. München: Carl Hanser Verlag GmbH & Co. KG, 2011. http://dx.doi.org/10.3139/9783446428348.004.

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Neacşu, Dorin O. "Propulsion Systems". En Automotive Power Systems, 273–90. Boca Raton : CRC Press, 2020.: CRC Press, 2020. http://dx.doi.org/10.1201/9781003053231-14.

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Suresh, B. N. y K. Sivan. "Propulsion Systems". En Integrated Design for Space Transportation System, 329–90. New Delhi: Springer India, 2015. http://dx.doi.org/10.1007/978-81-322-2532-4_9.

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Pfaff, Manfred. "Propulsion Systems". En Ship Operation Technology, 77–206. Wiesbaden: Springer Fachmedien Wiesbaden, 2021. http://dx.doi.org/10.1007/978-3-658-32729-3_4.

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Nixon, M. A. y Joseph Michaels. "Propulsion Systems". En Modern English for Aeronautics and Space Technology, 51–65. 2^a ed. München: Carl Hanser Verlag GmbH & Co. KG, 2021. http://dx.doi.org/10.3139/9783446470118.004.

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Seedhouse, Erik. "Propulsion systems". En Martian Outpost, 99–113. New York, NY: Praxis, 2009. http://dx.doi.org/10.1007/978-0-387-98191-8_5.

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Nixon, John D. y Joseph Michaels. "Propulsion Systems". En Modern English for Aeronautics and Space Technology, 51–65. München, Germany: Carl Hanser Verlag GmbH & Co. KG, 2021. http://dx.doi.org/10.1007/978-3-446-47011-8_4.

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Tajmar, Martin. "Propulsion Fundamentals". En 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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Actas de conferencias sobre el tema "Propulsion systems"

Metcalf, Bryson J. y Gabor Karafiath. "Hydrodynamic Assessment of Alternative Propulsion Arrangements". En SNAME 10th Propeller and Shafting Symposium. SNAME, 2003. http://dx.doi.org/10.5957/pss-2003-20.

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Non-traditional hydrodynamic propulsion systems such as pods, water jets, surface drives, and vertical axis propellers either inherently provide a steering capability or are sold with the steering element as an integral part. In addition, the appendage drag of these systems varies greatly. Thus the traditional measure of merit, the propulsive coefficient, which is mostly concerned with propeller efficiency and hull-propeller interaction, is not the best assessment of non-traditional propulsion systems. A new proposed measure of merit called the Hydrodynamic system coefficient is presented It is the ratio of the "bare hull" effective power to the final delivered power. Bare hull in this case refers to the vessel configuration without it's steering and propulsion-related appendages. The Hydrodynamic system coefficient is presented for several cases of the following vessel configurations; twin-pod propulsion, traditional shaft and strut arrangements, and nonintegral type skegs. Additionally, the application is also explained for vertical axis propellers, water-jet propulsion, tunnel hull arrangements, and surface drives. It is shown that the Hydrodynamic system coefficient is an excellent single parameter for comparing/assessing the performance among these various types of propulsion arrangements. The unadjusted model-test results are presented along with an adjusted calculation for cases where the rotating element of the model propulsor had poor performance.

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HALOULAKOS, V. y R. BOURQUE. "Fusion propulsion systems". En 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2629.

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CAMPBELL, JOHN. "Miniature propulsion systems". En 28th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-3252.

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Athanasakos, Georgios, Nikolaos Aretakis, Alexios Alexiou y Konstantinos Mathioudakis. "Turboelectric Distributed Propulsion Modelling Accounting for Fan Boundary Layer Ingestion and Inlet Distortion". En ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14621.

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Abstract A modelling approach of Boundary Layer Ingesting (BLI) propulsion systems is presented. Initially, a distorted compressor model is created utilizing the parallel compressor theory to estimate the impact of inlet distortion on fan performance. Next, a BLI propulsor model is developed considering both distortion effects and reduced inlet momentum drag caused from boundary layer ingestion. Finally, a Turbo-electric Distributed Propulsion (TeDP) model is set up, consisting of the BLI propulsor model, the associated turboshaft engine model and a representation of the relevant electrical system. Each model is validated through comparison with numerical and/or experimental data. A design point calculation is carried out initially to establish propulsor key dimensions for a specified number of propulsors and assuming common inlet conditions. Parametric design point analyses are then carried out to study the influence of propulsors number and location under different inlet conditions, by varying fan design pressure ratio between 1.15 and 1.5. BLI and non BLI configurations are compared at propulsion system level to assess the BLI benefits. The results show that maximum BLI gains of 9.3% in TSFC and 4.7% in propulsive efficiency can be achieved with 16 propulsors and FPR = 1.5, compared to podded propulsors, while further benefits can be achieved by moving the propulsor array backwards in the airframe.

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Lusby, Brian, Kris Romig y Michelle Smith. "Auxiliary Propulsion System Analysis Tool for Sizing On-Orbit Propulsion Systems". En 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-4841.

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Bossard, John A. "Propulsion Efficiency Considerations for Combined Cycle Propulsion Systems". En 51st AIAA/SAE/ASEE Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-3943.

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Ballard, R., K. Dill y S. McIntyre. "Propulsion Systems Test Bed - An optimum process for propulsion systems development". En 32nd Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-89.

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Gallops, G. W., C. F. Weiss y R. A. Carlton. "Integrated Propulsion System Requirements for Control of STOVL Aircraft". En ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-364.

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This paper describes an evaluation of propulsion system requirements and capability for a Short Take Off / Vertical Landing (STOVL) aircraft employing modulation of the propulsive lift distribution for pitch and roll control in hover. The effects of propulsive lift nozzle configuration and propulsion system dynamic response were evaluated using a combined system simulation consisting of a six degree of freedom aircraft model, engine model and integrated flight/propulsion control. The response and stability of propulsive lift control is compared with control by reaction jets supplied by engine bleed. Aircraft performance is demonstrated in simulated STOVL maneuvers using a dynamic pilot model. The conclusion of this study is that propulsive lift control of aircraft pitch and roll is feasible and can provide as much as a 10 percent increase in engine lift rating over systems which employ reaction control alone. The dynamic response of practical propulsive lift configurations, however, is less than that of reaction control configurations which must be offset through integration of the propulsion system and its control.

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NEUMAN, J., D. VAN HAAFTEN y W. MADSEN. "Nuclear propulsion systems engineering". En Conference on Advanced SEI Technologies. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3447.

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ROCK, STEPHEN, ABBAS EMAMI-NAEINI y ROBERT ANEX. "Propulsion control specifications in integrated flight propulsion control systems". En 24th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3236.

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Informes sobre el tema "Propulsion systems"

Qian, Yuping, Yangjun Zhang y WEILIN ZHUGE. Key Technology Challenges of Electric Ducted Fan Propulsion Systems for eVTOL. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, noviembre de 2023. http://dx.doi.org/10.4271/epr2023027.

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<div class="section abstract"><div class="htmlview paragraph">Electrical vertical takeoff and landing (eVTOL) vehicles for urban air mobility (UAM) are garnering increased attention from both the automotive and aerospace industries, with use cases ranging from individual transportation, public service, cargo delivery, and more. Distributed electric propulsion systems are their main technical feature; they determine vehicle size and propulsion efficiency and provide distributed thrust to achieve attitude control. Considering the intended role of eVTOL vehicles, ducted-fan systems are ideal choice for the propulsor, as the duct provides a physical barrier between the rotating blades and the human, especially during the take-off and landing phases.</div><div class="htmlview paragraph"><b>Key Technology Challenges of Electric Ducted Fan Propulsion Systems for eVTOL</b> introduces the main bottlenecks and key enablers of ducted-fan propulsion systems for eVTOL applications. Based on the introduction and discussion of these important issues, this report will help eVTOL engineers understand the key technical issues and inspire them to develop the ideal solutions that will enable eVTOL vehicle deployment for UAM operations.</div><div class="htmlview paragraph"><a href="https://www.sae.org/publications/edge-research-reports" target="_blank">Click here to access the full SAE EDGE</a><sup>TM</sup><a href="https://www.sae.org/publications/edge-research-reports" target="_blank"> Research Report portfolio.</a></div></div>

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Lawrence, Timothy J. Nuclear Thermal Rocket Propulsion Systems. Fort Belvoir, VA: Defense Technical Information Center, marzo de 2005. http://dx.doi.org/10.21236/ada430931.

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

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

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Melof, Brian Matthew, David L. Keese, Brian V. Ingram, Mark Charles Grubelich, Judith Alison Ruffner y William Rusty Escapule. Hydrogen peroxide-based propulsion and power systems. Office of Scientific and Technical Information (OSTI), abril de 2004. http://dx.doi.org/10.2172/903157.

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Jiang, Yuxiang. Unsettled Technology Areas in Electric Propulsion Systems. SAE International, mayo de 2021. http://dx.doi.org/10.4271/epr2021012.

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Electric vehicle (EV) transmission technology—crucial for battery electric vehicles (BEVs) and hybrid electric vehicles (HEVs)—is developing quickly and customers want good performance at a low cost. Single-speed gearboxes are popular in electric drive systems due to their simple and cost-effective configuration. However, multispeed gearboxes are being taken to market due to their higher low-speed torque, dynamic performance, and energy efficiency. Unsettled Technology Areas in Electric Propulsion Systems reviews the economic drivers, existing techniques, and current challenges of EV transmission technology—including torque interruption during shifting; thermal and sealing issues; and noise, vibration, and harshness (NVH). This report discusses the pros and cons for both single-speed and multispeed gearboxes with numerical analysis.

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Belian, Olivia. ALTERNATIVE POWER AND PROPULSION FOR SPACE SYSTEMS. Office of Scientific and Technical Information (OSTI), julio de 2023. http://dx.doi.org/10.2172/1993026.

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Gaines, L. L., A. Elgowainy y M. Q. Wang. Full Fuel-Cycle Comparison of Forklift Propulsion Systems. Office of Scientific and Technical Information (OSTI), octubre de 2008. http://dx.doi.org/10.2172/1219584.

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Gaines, L. L., A. Elgowainy y M. Q. Wang. Full fuel-cycle comparison of forklift propulsion systems. Office of Scientific and Technical Information (OSTI), noviembre de 2008. http://dx.doi.org/10.2172/946421.

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Chan, S. H., C. C. Tan, Y. G. Zhao y P. J. Janke. Li-SF(6) Combustion in Stored Chemical Energy Propulsion Systems. Fort Belvoir, VA: Defense Technical Information Center, julio de 1990. http://dx.doi.org/10.21236/ada224846.

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