Journal articles: 'Propulsion systems design'

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Dimitrova, Zlatina. "Vehicle propulsion systems design methods." MATEC Web of Conferences 133 (2017): 02001. http://dx.doi.org/10.1051/matecconf/201713302001.

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Blount, Donald L., and Robert J. Bartee. "Design of Propulsion Systems for High-Speed Craft." Marine Technology and SNAME News 34, no. 04 (October 1, 1997): 276–92. http://dx.doi.org/10.5957/mt1.1997.34.4.276.

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The demand for increased speed in medium and large craft challenges the designer to select propulsion systems which meet performance requirements economically throughout ever-widening operational profiles. The combined hydrodynamic characteristics of hull and propulsors result in a speed-thrust relationship for the environment in which the vessel operates. This speed-thrust relationship requires unique values of power and RPM input for each type and number of propulsors. Power and RPM are also sensitive to the mode of operation of the vessel whether at constant speed, accelerating to a greater speed or towing an object. Most vessels utilize fixed-pitch submerged propellers. Surface propellers are fitted to vessels designed to perform at very high speeds and waterjetpropulsors are being utilized with increasing frequency on larger vessels with high-speed operational profile. This paper discusses brake horsepower (BHP) and propulsor RPM relationships for vessel speed requirements based on the hydrodynamic characteristics of three types of propulsors: submerged propellers, surface propellers and waterjets. An example of predicted vessel performance regarding speed, power and propulsor RPM is presented which includes engine characteristics and BHP versus RPM. This latter format depicts the differences in power demand for three types of propulsors on a monohull vessel with regard to engine characteristics.

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POYRAZ, Özgür, and Melih Cemal KUŞHAN. "DESIGN FOR ADDITIVE MANUFACTURING WITH CASE STUDIES ON AIRCRAFTS AND PROPULSION SYSTEMS." SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE 21, no. 1 (October 8, 2019): 166–75. http://dx.doi.org/10.19062/2247-3173.2019.21.23.

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Gagarinov, I. "Structures of high-power electric propulsion systems." Transactions of the Krylov State Research Centre 1, no. 395 (March 9, 2021): 119–31. http://dx.doi.org/10.24937/2542-2324-2021-1-395-119-131.

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Object and purpose of research. This paper discusses structures of high-power electric propulsion systems for ships. The purpose was to give a summary of design solutions made in development of these systems. Materials and methods. This paper relies on academic and technical data, as well on the long-term author’s experience in marine electric propulsion R&Ds. The solution suggested by the author is based on the comparative analysis of design solutions adopted in the development of structures for high-power marine electric power and propulsion systems. Main results. Summary on design solutions for high-power electric propulsion systems of such ships as icebreakers, oil tankers, LNGCs and cruise liners. Conclusion. Results obtained by author were used in the design of the electric propulsion system of the «Lider» nuclear icebreaker and further could be used in design of Arctic vessels.

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Kaul, Stefan, Paul Mertes, and Lutz Müller. "Application-optimised propulsion systems for energy-efficient operation." Ciencia y tecnología de buques 5, no. 9 (July 23, 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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Leśniewski, Wojciech, Daniel Piątek, Konrad Marszałkowski, and Wojciech Litwin. "Small Vessel with Inboard Engine Retrofitting Concepts; Real Boat Tests, Laboratory Hybrid Drive Tests and Theoretical Studies." Energies 13, no. 10 (May 20, 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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Dahms, Julius, and Andreas Bardenhagen. "Propulsion model for (hybrid) unmanned aircraft systems (UAS)." Aircraft Engineering and Aerospace Technology 91, no. 2 (February 4, 2019): 373–80. http://dx.doi.org/10.1108/aeat-01-2018-0033.

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Purpose This paper deals with the estimation of the necessary masses of propulsion components for multirotor UAS. Originally, within the design process of multirotors, this is an iterative problem, as the propulsion masses contribute to the total takeoff mass. Hence, they influence themselves and cannot be directly calculated. The paper aims to estimate the needed propulsion masses with respect to the requested thrust because of payload, airframe weight and drag forces and with respect to the requested flight time. Design/methodology/approach Analogue to the well-established design synthesis of airplanes, statistical data of existing electrical motors, propellers and rechargeable batteries are evaluated and analyzed. Applying Rankine and Froude’s momentum theory and a generic model for electro motor efficiency factors on the statistical performance data provides correlations between requested performance and, therefore, needed propulsion masses. These correlations are evaluated and analyzed in the scope of buoyant-vertical-thrusted hybrid UAS. Findings This paper provides a generic mathematical propulsion model. For given payloads, airframe structure weights and a requested flight time, appropriate motor, propeller and battery masses can be modelled that will provide appropriate thrust to lift payload, airframe and the propulsion unit itself over a requested flight time. Research limitations/implications The model takes into account a number of motors of four and is valid for the category of nano and small UAS. Practical implications The presented propulsion model enables a full numerical design process for vertical thrusted UAS. Hence, it is the precondition for design optimization and more efficient UAS. Originality/value The propulsion model is unique and it is valid for pure multirotor as well as for hybrid UAS too.

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Jahshan, S. N., and T. Kammash. "Multimegawatt Nuclear Reactor Design for Plasma Propulsion Systems." Journal of Propulsion and Power 21, no. 3 (May 2005): 385–91. http://dx.doi.org/10.2514/1.5456.

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MISHIO, Ryoichi, and Tadashi KASHIMA. "Design of Optimal Feedback Control for Propulsion Systems." Proceedings of Conference of Kansai Branch 2003.78 (2003): _12–15_—_12–16_. http://dx.doi.org/10.1299/jsmekansai.2003.78._12-15_.

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Islam, Mohammed F., Brian Veitch, Neil Bose, and Pengfei Liu. "Numerical Study of Hub Taper Angle on Podded Propeller Performance." Marine Technology and SNAME News 43, no. 01 (January 1, 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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Karthigan, Ganesan, Sujoy Mukherjee, and Ranjan Ganguli. "Electromechanical dynamics and optimization of pectoral fin–based ionic polymer–metal composite underwater propulsor." Journal of Intelligent Material Systems and Structures 23, no. 10 (May 6, 2012): 1069–82. http://dx.doi.org/10.1177/1045389x12442010.

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Ionic polymer–metal composites are soft artificial muscle-like bending actuators, which can work efficiently in wet environments such as water. Therefore, there is significant motivation for research on the development and design analysis of ionic polymer–metal composite based biomimetic underwater propulsion systems. Among aquatic animals, fishes are efficient swimmers with advantages such as high maneuverability, high cruising speed, noiseless propulsion, and efficient stabilization. Fish swimming mechanisms provide biomimetic inspiration for underwater propulsor design. Fish locomotion can be broadly classified into body and/or caudal fin propulsion and median and/or paired pectoral fin propulsion. In this article, the paired pectoral fin–based oscillatory propulsion using ionic polymer–metal composite for aquatic propulsor applications is studied. Beam theory and the concept of hydrodynamic function are used to describe the interaction between the beam and water. Furthermore, a quasi-steady blade element model that accounts for unsteady phenomena such as added mass effects, dynamic stall, and the cumulative Wagner effect is used to obtain hydrodynamic performance of the ionic polymer–metal composite propulsor. Dynamic characteristics of ionic polymer–metal composite fin are analyzed using numerical simulations. It is shown that the use of optimization methods can lead to significant improvement in performance of the ionic polymer–metal composite fin.

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Stuhlinger, Ernst. "Future Deep Space Propulsion Systems." International Astronomical Union Colloquium 123 (1990): 355–62. http://dx.doi.org/10.1017/s0252921100077289.

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AbstractAmong several potential future deep space propulsion systems, the two which are closest to realization are selected for closer consideration: solar-electric, and nuclear-electric propulsion. In particular, the paper describes a manned Mars mission using a particle bed reactor and Brayton cycle converter as power source. Technical details of the design and the mission profile of a 4-astronaut expedition to Mars, and a proposed course of action for project implementation are presented.

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Banning, R., M. A. Johnson, and M. J. Grimble. "Advanced Control Design for Marine Diesel Engine Propulsion Systems." Journal of Dynamic Systems, Measurement, and Control 119, no. 2 (June 1, 1997): 167–74. http://dx.doi.org/10.1115/1.2801229.

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A new marine diesel engine propulsion control design procedure is proposed which is applicable to a wide range of marine vessels. This procedure combines linear optimal H∞ control methods with non-linear control techniques to address the propulsion system’s nonlinearity. Simulation results show that a tracking control system aimed at saving fuel and optimizing efficiency may be obtained which is applicable across all maneuvring regimes. This compares favorably with the situation in some operating scenarios where the use of the linear controller alone can result in poor performance or even instability.

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Kim, Ye-Rin, Jae-Myeong Kim, Jae-Jung Jung, So-Yeon Kim, Jae-Hak Choi, and Hyun-Goo Lee. "Comprehensive Design of DC Shipboard Power Systems for Pure Electric Propulsion Ship Based on Battery Energy Storage System." Energies 14, no. 17 (August 25, 2021): 5264. http://dx.doi.org/10.3390/en14175264.

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With the strengthening of international environmental regulations, many studies on the integrated electric propulsion systems applicable to eco-friendly ship are being conducted. However, few studies have been performed to establish a guide line for the overall pure electric propulsion ship design. Therefore, this paper introduces the comprehensive design of DC shipboard power system for pure electric propulsion ship based on battery energy storage system (BESS). To design and configure the pure electric propulsion ship, 2 MW propulsion car ferry was assumed and adopted to be the target vessel in this paper. In order to design the overall system, a series of design processes, such as the decision of the ship operation profile, BESS capacity selection, configuration of the power conversion systems for propulsion, battery charging/discharging procedures, classification of system operation modes, and analysis of the efficiency, were considered. The proposed efficient design and analysis of the pure electric propulsion ship was qualitatively and quantitatively validated by MATLAB Simulink tool. The methodology presented in this paper can help design real ships before the system commissioning.

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Samoilescu, Gheorghe, Dumitru Iorgulescu, Robert Mitrea, and Laura D. Cizer. "Propulsion Systems in Marine Navigation." International conference KNOWLEDGE-BASED ORGANIZATION 24, no. 3 (June 1, 2018): 78–82. http://dx.doi.org/10.1515/kbo-2018-0140.

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Abstract This paper presents variants of propulsion systems as the main factor in the analysis and design of the power system of a sea-going or river vessel; this topic is also under research study within two doctoral theses. The analysis of the ship - main propulsion- thruster assembly is made according to the requirements imposed by the market economy. The parameters to be considered when choosing a propulsion system are: the cost of the investment, the specific cost of transport that depends both on the specific fuel consumption and on the number and level of pay of the crew members operating the propulsion system, the propulsion efficiency, the high safety in handling, and the control accessibility during operation. The Pod and Azipod propulsion systems are analyzed in terms of advantages and disadvantages compared to conventional propulsion systems. The azimuth thrusters can ensure maximum push in any direction regardless the speed of the ship, and thus can change the course of the ship according to its handling needs. The azimuth thrusters do not only operate in horizontal but also in oblique angles, providing the ship with great maneuverability, even at low speeds, where classical rudder systems have poor performance

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Skira, C. A., and M. Agnello. "Control Systems for the Next Century’s Fighter Engines." Journal of Engineering for Gas Turbines and Power 114, no. 4 (October 1, 1992): 749–54. http://dx.doi.org/10.1115/1.2906652.

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The paper describes a conceptual control system design based on advanced technologies currently in the exploratory development phase, and, in some cases, emerging into the advanced development phase. It explores future propulsion control systems that focus on improvements in three areas: (1) significantly reducing control system weight; (2) enhancing engine performance (thrust, sfc, etc.); and (3) improving control system reliability and tolerance to high-threat environments (temperature, vibration, EMI, EMP, etc.). The factors that will influence the design and hardware configuration of future propulsion control systems are described. Design goals for future systems, based on the DOD/NASA IHPTET Initiative, and projections of emerging technology capability (and availability) form the basis for future propulsion control system design requirements and for estimating future hardware configurations.

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Large, James, and Apostolos Pesyridis. "Investigation of Micro Gas Turbine Systems for High Speed Long Loiter Tactical Unmanned Air Systems." Aerospace 6, no. 5 (May 14, 2019): 55. http://dx.doi.org/10.3390/aerospace6050055.

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In this study, the on-going research into the improvement of micro-gas turbine propulsion system performance and the suitability for its application as propulsion systems for small tactical UAVs (<600 kg) is investigated. The study is focused around the concept of converting existing micro turbojet engines into turbofans with the use of a continuously variable gearbox, thus maintaining a single spool configuration and relative design simplicity. This is an effort to reduce the initial engine development cost, whilst improving the propulsive performance. The BMT 120 KS micro turbojet engine is selected for the performance evaluation of the conversion process using the gas turbine performance software GasTurb13. The preliminary design of a matched low-pressure compressor (LPC) for the proposed engine is then performed using meanline calculation methods. According to the analysis that is carried out, an improvement in the converted micro gas turbine engine performance, in terms of thrust and specific fuel consumption is achieved. Furthermore, with the introduction of a CVT gearbox, the fan speed operation may be adjusted independently of the core, allowing an increased thrust generation or better fuel consumption. This therefore enables a wider gamut of operating conditions and enhances the performance and scope of the tactical UAV.

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Lilley, J. S. "Design and optimization of propulsion systems employing scarfed nozzles." Journal of Spacecraft and Rockets 23, no. 6 (November 1986): 597–604. http://dx.doi.org/10.2514/3.25853.

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Behkam, Bahareh, and Metin Sitti. "Design Methodology for Biomimetic Propulsion of Miniature Swimming Robots." Journal of Dynamic Systems, Measurement, and Control 128, no. 1 (September 23, 2005): 36–43. http://dx.doi.org/10.1115/1.2171439.

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Miniature and energy-efficient propulsion systems hold the key to maturing the technology of swimming microrobots. In this paper, two new methods of propulsion inspired by the motility mechanism of prokaryotic and eukaryotic microorganisms are proposed. Hydrodynamic models for each of the two methods are developed, and the optimized design parameters for each of the two propulsion modes are demonstrated. To validate the theoretical result for the prokaryotic flagellar motion, a scaled-up prototype of the robot is fabricated and tested in silicone oil, using the Buckingham PI theorem for scaling. The proposed propulsion methods are appropriate for the swimming robots that are intended to swim in low-velocity fluids.

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Zong, Jianan, Bingjie Zhu, Zhongxi Hou, Xixiang Yang, and Jiaqi Zhai. "Evaluation and Comparison of Hybrid Wing VTOL UAV with Four Different Electric Propulsion Systems." Aerospace 8, no. 9 (September 9, 2021): 256. http://dx.doi.org/10.3390/aerospace8090256.

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Electric propulsion technology has attracted much attention in the aviation industry at present. It has the advantages of environmental protection, safety, low noise, and high design freedom. An important research branch of electric propulsion aircraft is electric vertical takeoff and landing (VTOL) aircraft, which is expected to play an important role in urban traffic in the future. Limited by battery energy density, all electric unmanned aerial vehicles (UAVs) are unable to meet the longer voyage. Series/parallel hybrid-electric propulsion and turboelectric propulsion are considered to be applied to VTOL UAVs to improve performances. In this paper, the potential of these four configurations of electric propulsion systems for small VTOL UAVs are evaluated and compared. The main purpose is to analyze the maximum takeoff mass and fuel consumption of VTOL UAVs with different propulsion systems that meet the same performance requirements and designed mission profiles. The differences and advantages of the four types propulsion VTOL UAV in the maximum takeoff mass and fuel consumption are obtained, which provides a basis for the design and configuration selection of VTOL UAV propulsion system.

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Hirz, M., M. Hofstetter, and D. Lechleitner. "Electric Propulsion Systems Design Supported by Multi-Objective Optimization Strategies." Science & Technique 18, no. 6 (December 5, 2019): 461–70. http://dx.doi.org/10.21122/2227-1031-2019-18-6-461-470.

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Electric drive systems consisting of battery, inverter, electric motor and gearbox are applied in hybridor purely electric vehicles. The layout process of such propulsion systems is performed on system level under consideration of various component properties and their interfering characteristics. In addition, different boundary conditions are taken under account, e. g. performance, efficiency, packaging, costs. In this way, the development process of the power train involves a broad range of influencing parameters and periphery conditions and thus represents a multi-dimensional optimization problem. Stateof-the-art development processes of mechatronic systems are usually executed according to the V-model, which represents a fundamental basis for handling the complex interactions of the different disciplines involved. In addition, stage-gate processes and spiral models are applied to deal with the high level of complexity during conception, design and testing. Involving a large number of technical and economic factors, these sequential, recursive processes may lead to suboptimal solutions since the system design processes do not sufficiently consider the complex relations between the different, partially conflicting domains. In this context, the present publication introduces an integrated multi-objective optimization strategy for the effective conception of electric propulsion systems, which involves a holistic consideration of all components and requirements in a multi-objective manner. The system design synthesis is based on component-specific Pareto-optimal designs to handle performance, efficiency, package and costs for given system requirements. The results are displayed as Pareto-fronts of electric power train system designs variants, from which decision makers are able to choose the best suitable solution. In this way, the presented system design approach for the development of electrically driven axles enables a multi-objective optimization considering efficiency, performance, costs and package. It is capable to reduce development time and to improve overall system quality at the same time.

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Alulema, Victor, Esteban Valencia, Edgar Cando, Victor Hidalgo, and Dario Rodriguez. "Propulsion Sizing Correlations for Electrical and Fuel Powered Unmanned Aerial Vehicles." Aerospace 8, no. 7 (June 24, 2021): 171. http://dx.doi.org/10.3390/aerospace8070171.

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Despite the increasing demand of Unmanned Aerial Vehicles (UAVs) for a wide range of civil applications, there are few methodologies for their initial sizing. Nowadays, classical methods, mainly developed for transport aircraft, have been adapted to UAVs. However, these tools are not always suitable because they do not fully adapt to the plethora of geometrical and propulsive configurations that the UAV sector represents. Therefore, this work provides series of correlations based on off-the-shelf components for the preliminary sizing of propulsion systems for UAVs. This study encompassed electric and fuel-powered propulsion systems, considering that they are the most used in the UAV industry and are the basis of novel architectures such as hybrid propulsion. For these systems, weight correlations were derived, and, depending on data availability, correlations regarding their geometry and energy consumption are also provided. Furthermore, a flowchart for the implementation of the correlations in the UAV design procedure and two practical examples are provided to highlight their usability. To summarize, the main contribution of this work is to provide parametric tools to size rapidly the propulsion system components, which can be embedded in a UAV design and optimization framework. This research complements other correlation studies for UAVs, where the initial sizing of the vehicle is discussed. The present correlations suit multiple UAV categories ranging from micro to Medium-Altitude-Long-Endurance (MALE) UAVs.

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Zaccone, Raphael, Ugo Campora, and Michele Martelli. "Optimisation of a Diesel-Electric Ship Propulsion and Power Generation System Using a Genetic Algorithm." Journal of Marine Science and Engineering 9, no. 6 (May 28, 2021): 587. http://dx.doi.org/10.3390/jmse9060587.

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In recent decades, the design of ship propulsion systems has been focusing on energy efficiency and low pollutant emissions. In this framework, diesel–electric propulsion has become a standard for many ship types and has proven its worth for flexible propulsion design and management. This paper presents an approach to the optimal design of diesel–electric propulsion systems, minimising the fuel consumption while meeting the power and speed requirements. A genetic algorithm performs the optimisation, used to determine the number and type of engines installed on-board and the engines’ design speed and power, selecting within a dataset of four-stroke diesel engines. The same algorithm is then adapted and applied to determine the optimal load sharing strategy in off-design conditions, taking advantage of the high flexibility of the diesel–electric propulsion plants. In order to apply the algorithm, the propulsion layout design is formulated as an optimisation problem, translating the system requirements into a cost function and a set of linear and non-linear constraints. Eventually, the method is applied to a case study vessel: first, the optimal diesel–electric propulsion plants are determined, then the optimal off-design load sharing and working conditions are computed. AC and DC network solutions are compared and critically discussed in both design and off-design conditions.

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Basharina, T. A., M. G. Goncharov, S. N. Lymich, V. S. Levin, and D. P. Shmatov. "Low-thrust liquid-propellant rocket engines as part of advanced ultralight rocket vehicle systems." Spacecrafts & Technologies 5, no. 1 (March 25, 2021): 5–13. http://dx.doi.org/10.26732/j.st.2021.1.01.

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This work examines the most promising design solutions for the creation of propulsion systems for ultra-light launch vehicles by small private enterprises in the rocket and space industry. Comparison of the metal consumption of the combustion chambers with the energy characteristics at different operating pressures showed that the most optimal operating pressure is 12,16 MPa. Comparison of the relative and absolute values of the masses of various configurations describes the nature of the relationship between the number of combustion chambers and the total mass of the propulsion system. It was found that nine-chamber propulsion systems with cameras made with extensive use of additive technologies best meet the key requirements. The analysis carried out includes an assessment of the design parameters of both various components and assemblies and the propulsion system as a whole. Various layouts of propulsion systems are considered in detail, the required degree of technological complexity of structures of various units and assemblies, their production cost are estimated. The ratio of the obtained mass-energy characteristics was achieved through the implementation of design solutions that became available due to the use of additive technologies. The obtained results of preliminary calculations demonstrate the applicability and efficiency of design solutions considered for use in the propelled propulsion system for a promising launch vehicle.

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Lobão de Almeida, Thiago, and Victor Coracini Tonacio. "Passenger submarine concept design for oil production offshore systems." Ciencia y tecnología de buques 4, no. 8 (January 24, 2011): 9. http://dx.doi.org/10.25043/19098642.42.

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The paper proposes an innovative solution to transport workers of offshore oil production platforms from the coast to their units, which operate at the Pre-Salt exploration, 300 km from the coast. A passenger submarine concept design was developed, justified by the range of practical obstacles observed in the current modes of transportation, helicopters and supply boats. Requirements like operational depth (100 m), passenger capacity (250 people), and cruising speed (minimum 13.4 knots) are defined, based on estimates. Firstly, it seeks the adoption of air-independent propulsion (AIP) systems, by fuel cells (PEMFC). However, the work progress leads to an entire electric propulsion system. The internal arrangement is elaborated, regarding passenger comfort, structural constraints, allocation of batteries and ballast tanks. Then, after a hydrodynamic hull optimization, by Computational Fluid Dynamics analysis, we provide a final configuration with 100-m length and 9.7-m diameter, operational speed of 16 kt, and autonomy of 26 hours.

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Altosole, M., and Massimo Figari. "Effective simple methods for numerical modelling of marine engines in ship propulsion control systems design." Journal of Naval Architecture and Marine Engineering 8, no. 2 (December 30, 2011): 129–47. http://dx.doi.org/10.3329/jname.v8i2.7366.

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In the last year, the Department of Naval Architecture and Marine Engineering of Genoa University (now Department of Naval Architecture, Marine Technology and Electrical Engineering) collaborated to the design of the propulsion automation of two different naval vessels; within these projects the authors developed different ship propulsion simulators used to design and test the propulsion control schemes. In these time-domain simulators, each propulsion component is represented by a specific mathematical model, mainly based on algebraic and differential equations. One of the key aspects of the propulsion simulation is the engine dynamics. This problem in principle can be dealt with models based on thermodynamic principles, which are able to represent in detail the behaviour of many variables of interest (engine power and speed, air and gas pressures, temperatures, stresses, etc.). However, thermodynamic models are often characterized by a long computation-time and moreover their development usually requires the knowledge of specific engine information not always available. It is generally preferable to adopt simpler simulation models, for the development of which, very few kinds of information are necessary. In fact, for the rapid prototyping of control schemes, it is generally more important to model the whole plant (in a relatively coarse way) rather than the detailed model of some components. This paper deals with simple mathematical methods, able to represent the engine power or torque only, but they can be suitably applied to many types of marine engines in a straightforward way. The proposed simulation approaches derived from the authors’ experience, gained during their activity in the marine simulation field, and they are particularly suitable for a fast prototyping of the marine propulsion control systems. The validation process of these particular models, regarding a Diesel engine, a marine gas turbine and an electric motor, is illustrated based on the sea trials data and engine manufacturers’ data. Keywords: Dynamic simulation; marine engines performance; gas turbine; propulsion control. doi: http://dx.doi.org/10.3329/jname.v8i2.7366 Journal of Naval Architecture and Marine Engineering 8(2011) 129-147

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Ayancik, Fatma, Qiang Zhong, Daniel B. Quinn, Aaron Brandes, Hilary Bart-Smith, and Keith W. Moored. "Scaling laws for the propulsive performance of three-dimensional pitching propulsors." Journal of Fluid Mechanics 871 (June 3, 2019): 1117–38. http://dx.doi.org/10.1017/jfm.2019.334.

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Scaling laws for the thrust production and energetics of self-propelled or fixed-velocity three-dimensional rigid propulsors undergoing pitching motions are presented. The scaling relations extend the two-dimensional scaling laws presented in Moored & Quinn (AIAA J., 2018, pp. 1–15) by accounting for the added mass of a finite-span propulsor, the downwash/upwash effects from the trailing vortex system of a propulsor and the elliptical topology of shedding trailing-edge vortices. The novel three-dimensional scaling laws are validated with self-propelled inviscid simulations and fixed-velocity experiments over a range of reduced frequencies, Strouhal numbers and aspect ratios relevant to bio-inspired propulsion. The scaling laws elucidate the dominant flow physics behind the thrust production and energetics of pitching bio-propulsors, and they provide guidance for the design of bio-inspired propulsive systems.

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Davies, W. J., R. A. Baumbick, and R. W. Vizzini. "Conceptual Design of an Optic-Based Engine Control System." Journal of Engineering for Gas Turbines and Power 110, no. 1 (January 1, 1988): 28–32. http://dx.doi.org/10.1115/1.3240082.

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Advanced integrated flight and propulsion control systems may require the use of optic technology to provide enhanced electromagnetic immunity and reduced weight. Immunity to electromagnetic interference and pulses is required for integrated systems where flight and propulsion control systems communicate with each other and diverse systems located throughout a composite aircraft. Weight reduction is crucial to the complex engine control systems required for advanced engines incorporating diagnostics, variable geometry and vectoring/reversing exhaust nozzles. A team of Pratt & Whitney, McDonnell Aircraft, Hamilton Standard, and United Technologies Research Center have developed the conceptual design of an optic engine control system, under a contract from NASA Lewis, entitled Fiber Optic Control System Integration (FOCSI). FOCSI is a triservice/NASA joint program designed to provide the optic technology requirements for advanced fighter/attack aircraft.

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Jia, Xinghua, Xiaobo Li, Scott C. Lenaghan, and Mingjun Zhang. "Design of Efficient Propulsion for Nanorobots." IEEE Transactions on Robotics 30, no. 4 (August 2014): 792–801. http://dx.doi.org/10.1109/tro.2014.2303834.

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Adami, Amirhossein, Mahda Mortazavi, and Mehran Nosratollahi. "Multi-modular design optimization and multidisciplinary design optimization." International Journal of Intelligent Unmanned Systems 3, no. 2/3 (May 11, 2015): 156–70. http://dx.doi.org/10.1108/ijius-01-2015-0001.

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Purpose – For complex engineering problems, multidisciplinary design optimization (MDO) techniques use some disciplines that need to be run several times in different modules. In addition, mathematical modeling of a discipline can be improved for each module. The purpose of this paper is to show that multi-modular design optimization (MMO) improves the design performances in comparison with MDO technique for complex systems. Design/methodology/approach – MDO framework and MMO framework are developed to optimum design of a complex system. The nonlinear equality and inequality constrains are considered. The system optimizers included Genetic Algorithm and Sequential Quadratic Programming. Findings – As shown, fewer design variables (optimization variables) are needed at the system level for MMO. Unshared variables are optimized in the related module when shared variables are optimized at the system level. The results of this research show that MMO has lower elapsed times (14 percent) with lower F-count (16 percent). Practical implications – The monopropellant propulsion upper-stage is selected as a case study. In this paper, the efficient model of the monopropellant propulsion system is proposed. According to the results, the proposed model has acceptable accuracy in mass model (error < 2 percent), performance estimation (error < 6 percent) and geometry estimation (error < 10 percent). Originality/value – The monopropellant propulsion system is broken down into the three important modules including propellant tank (tank and propellant), pressurized feeding (tank and gas) and thruster (catalyst, nozzle and catalysts bed) when chemical decomposition, aerothermodynamics, mass and configuration, catalyst and structure have been considered as the disciplines. The both MMO and MDO frameworks are developed for the monopropellant propulsion system.

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Gebauer, Jan, Renata Wagnerová, Pavel Smutný, and Petr Podešva. "Controller design for variable pitch propeller propulsion drive." IFAC-PapersOnLine 52, no. 27 (2019): 186–91. http://dx.doi.org/10.1016/j.ifacol.2019.12.754.

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Ngo, V., T. Hofman, M. Steinbuch, and A. Serrarens. "Structural analysis of control design objectives for vehicular propulsion systems." International Journal of Powertrains 4, no. 1 (2015): 16. http://dx.doi.org/10.1504/ijpt.2015.067455.

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Sziroczak, David, Istvan Jankovics, Istvan Gal, and Daniel Rohacs. "Conceptual design of small aircraft with hybrid-electric propulsion systems." Energy 204 (August 2020): 117937. http://dx.doi.org/10.1016/j.energy.2020.117937.

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Hu, Liang Deng, Chi Sun, Zhi Hua Zhao, and Yu Lin Chen. "Design of Control Console for Vessel Integrated Power Propulsion Subsystem." Advanced Materials Research 846-847 (November 2013): 347–54. http://dx.doi.org/10.4028/www.scientific.net/amr.846-847.347.

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This The integrated power system (IPS) to be used in future ships will be a big leap in the building of ship power platforms, representing the prospective direction of in the development of ship power systems. A centralized control console with PLC(Programmable Logic Control) and touch screen has been designed for the propulsion subsystem of the vessel integrated power system. The centralized control console is mainly used to monitor the operations of the propulsion motor and propulsion inverter and to make remote control communications with the propulsion display and control console of energy management. This paper has made a detailed description of its hardware, software and communication, and given full account of the PLC program as well as the process of the start-up, speed regulation and shutdown performed by the propulsion subsystem under local or remote control. The site tests prove that the designed centralized control console can effectively monitor the running conditions of the propulsion subsystem and improve the digitalization, intelligent capability, stability and reliability of the vessel integrated power system, which will be of reference value to the research on ship automatic management and long-distance monitoring.

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Seitz, Arne, Anaïs Luisa Habermann, Fabian Peter, Florian Troeltsch, Alejandro Castillo Pardo, Biagio Della Corte, Martijn van Sluis, et al. "Proof of Concept Study for Fuselage Boundary Layer Ingesting Propulsion." Aerospace 8, no. 1 (January 13, 2021): 16. http://dx.doi.org/10.3390/aerospace8010016.

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Key results from the EU H2020 project CENTRELINE are presented. The research activities undertaken to demonstrate the proof of concept (technology readiness level—TRL 3) for the so-called propulsive fuselage concept (PFC) for fuselage wake-filling propulsion integration are discussed. The technology application case in the wide-body market segment is motivated. The developed performance bookkeeping scheme for fuselage boundary layer ingestion (BLI) propulsion integration is reviewed. The results of the 2D aerodynamic shape optimization for the bare PFC configuration are presented. Key findings from the high-fidelity aero-numerical simulation and aerodynamic validation testing, i.e., the overall aircraft wind tunnel and the BLI fan rig test campaigns, are discussed. The design results for the architectural concept, systems integration and electric machinery pre-design for the fuselage fan turbo-electric power train are summarized. The design and performance implications on the main power plants are analyzed. Conceptual design solutions for the mechanical and aero-structural integration of the BLI propulsive device are introduced. Key heuristics deduced for PFC conceptual aircraft design are presented. Assessments of fuel burn, NOx emissions, and noise are presented for the PFC aircraft and benchmarked against advanced conventional technology for an entry-into-service in 2035. The PFC design mission fuel benefit based on 2D optimized PFC aero-shaping is 4.7%.

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Nabawy, Mostafa R. A., and Ruta Marcinkeviciute. "Scalability of resonant motor-driven flapping wing propulsion systems." Royal Society Open Science 8, no. 9 (September 2021): 210452. http://dx.doi.org/10.1098/rsos.210452.

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This work aims to develop an integrated conceptual design process to assess the scalability and performance of propulsion systems of resonant motor-driven flapping wing vehicles. The developed process allows designers to explore the interaction between electrical, mechanical and aerodynamic domains in a single transparent design environment. Wings are modelled based on a quasi-steady treatment that evaluates aerodynamics from geometry and kinematic information. System mechanics is modelled as a damped second-order dynamic system operating at resonance with nonlinear aerodynamic damping. Motors are modelled using standard equations that relate operational parameters and AC voltage input. Design scaling laws are developed using available data based on current levels of technology. The design method provides insights into the effects of changing core design variables such as the actuator size, actuator mass fraction and pitching kinematics on the overall design solution. It is shown that system efficiency achieves peak values of 30–36% at motor masses of 0.5–1 g when a constant angle of attack kinematics is employed. While sinusoidal angle of attack kinematics demands more aerodynamic and electric powers compared with the constant angle of attack case, sinusoidal angle of attack kinematics can lead to a maximum difference of around 15% in peak system efficiency.

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Lewis, W. J. "Propulsion Systems for Supersonic V/STOL Aircraft." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 206–11. http://dx.doi.org/10.1115/1.2906163.

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A number of different powerplant systems have been and are being considered for supersonic V/STOL aircraft. Some of the main features of these different powerplants are described. As a result of studying the results of operation of successful and unsuccessful V/STOL aircraft in the powered lift condition, a number of real requirements for practical and flexible operation can be identified. These requirements may have a profound impact on the design and configuration of the powered lift powerplant. Some of these are discussed and conclusions reached.

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Kadiyam, Jagadeesh, and Santhakumar Mohan. "Conceptual design of a hybrid propulsion underwater robotic vehicle with different propulsion systems for ocean observations." Ocean Engineering 182 (June 2019): 112–25. http://dx.doi.org/10.1016/j.oceaneng.2019.04.069.

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Cheng, Mengjiao, Lina Zhang, and Feng Shi. "Design of functionally cooperating systems and application towards self-propulsive mini-generators." Materials Chemistry Frontiers 5, no. 1 (2021): 129–50. http://dx.doi.org/10.1039/d0qm00548g.

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Progress of ‘functionally cooperating systems’ is reviewed with emphasis on self-propulsion including design of material systems for applications in mini-generators based on horizontal/vertical motions, self-assembly, and directed transportation.

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Lou, De Cang, Wen Guo, Zhi Guo Wang, and Yong Hong Wang. "Integrated Thermal Management System Design for Advanced Propulsion System." Applied Mechanics and Materials 232 (November 2012): 723–29. http://dx.doi.org/10.4028/www.scientific.net/amm.232.723.

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Thermal management system (TMS) design is considered to be a key technology for advanced aero engines and supersonic or hypersonic propulsion systems. In this paper, the concepts of coupling flow and thermodynamic networks are proposed for TMS design. In this method, the propulsion system is considered to be a zero-dimensional flow system. Components, subsystems and hence the entire engine system can be modelled using some basic flow and thermodynamics networks. The platform for TMS design, ThermalM, is developed based on this model. As an example, modelling for a Turbine Based Combined Cycle (TBCC) thermal management system is described. Performance of the fuel heat exchanger in the network is discussed in detail. With the TMS design technology, performance of the advanced propulsion system can be analysed.

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Nosseir, Ahmed E. S., Angelo Cervone, and Angelo Pasini. "Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers." Aerospace 8, no. 1 (January 15, 2021): 20. http://dx.doi.org/10.3390/aerospace8010020.

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Current research trends have advanced the use of “green propellants” on a wide scale for spacecraft in various space missions; mainly for environmental sustainability and safety concerns. Small satellites, particularly micro and nanosatellites, evolved from passive planetary-orbiting to being able to perform active orbital operations that may require high-thrust impulsive capabilities. Thus, onboard primary and auxiliary propulsion systems capable of performing such orbital operations are required. Novelty in primary propulsion systems design calls for specific attention to miniaturization, which can be achieved, along the above-mentioned orbital transfer capabilities, by utilizing green monopropellants due to their relative high performance together with simplicity, and better storability when compared to gaseous and bi-propellants, especially for miniaturized systems. Owing to the ongoing rapid research activities in the green-propulsion field, it was necessary to extensively study and collect various data of green monopropellants properties and performance that would further assist analysts and designers in the research and development of liquid propulsion systems. This review traces the history and origins of green monopropellants and after intensive study of physicochemical properties of such propellants it was possible to classify green monopropellants to three main classes: Energetic Ionic Liquids (EILs), Liquid NOx Monopropellants, and Hydrogen Peroxide Aqueous Solutions (HPAS). Further, the tabulated data and performance comparisons will provide substantial assistance in using analysis tools—such as: Rocket Propulsion Analysis (RPA) and NASA CEA—for engineers and scientists dealing with chemical propulsion systems analysis and design. Some applications of green monopropellants were discussed through different propulsion systems configurations such as: multi-mode, dual mode, and combined chemical–electric propulsion. Although the in-space demonstrated EILs (i.e., AF-M315E and LMP-103S) are widely proposed and utilized in many space applications, the investigation transpired that NOx fuel blends possess the highest performance, while HPAS yield the lowest performance even compared to hydrazine.

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Koch, P. N., J. K. Allen, F. Mistree, and A. Barlow. "Facilitating Concept Exploration for Configuring Turbine Propulsion Systems." Journal of Mechanical Design 120, no. 4 (December 1, 1998): 702–6. http://dx.doi.org/10.1115/1.2829334.

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In this Technical Brief we illustrate the efficacy of the Robust Concept Exploration Method as applied to the preliminary design of a turbine lift engine for Advanced Short Take-Off and Vertical Landing (ASTOVL) fighter aircraft. This example is defined in collaboration with the Rolls-Royce Atlanta Engineering Group.

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Shafaee, Maziar, Parviz Mohammad Zadeh, Abbas Elkaie, and Hamed Fallah. "Design optimization of a thrust chamber using a mass-based model to improve the geometrical and performance parameters of low-thrust space propulsion systems." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 5 (April 17, 2018): 1820–37. http://dx.doi.org/10.1177/0954410018767288.

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A large portion of the wet and dry mass budget in any space system is assigned to the propulsion system. Each of these depends on the engine system design values. Any effort to decrease the mass of space systems demands an additional effort to reduce the propulsion system mass, which in turn requires a complete review of the engine design. Thus, proposing a computational model derived from the engine design and based on minimum system mass is necessary. The present computational research developed a propulsion system design strategy for liquid propulsion systems to optimize take-off mass and satisfy the thrust required under performance and structural constraints. Improvement of the geometric and performance variables and component mass using a mass-based model for optimization process is investigated. The method uses a hybrid genetic algorithm sequential quadratic programming as an optimizer. The mass-based formulation problem is solved using a hybrid optimization algorithm with a genetic algorithm as the global optimizer and sequential quadratic programming as the local optimizer starting from the solution given by the genetic algorithm. The convergence of the optimization algorithm is improved by introducing an initial solution based on genetic algorithm. Comparison of the proposed design optimization model with a real space propulsion system indicates that the performance of the proposed algorithm significantly improved the final results. While propellant mass, engine consumption rate and engine geometric dimensions decreased, specific impulse increased. All of these decreased the total mass of the space propulsion system.

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LeCren, R. T., R. E. Gildersleeve, and R. A. Swanek. "Combustor and Seal System for a Water Piston Propulsor." Journal of Engineering for Gas Turbines and Power 111, no. 1 (January 1, 1989): 117–22. http://dx.doi.org/10.1115/1.3240206.

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The Water Piston Propulsor (WPP) is an advanced in-water propulsion system for Marine Corps amphibious vehicles. Significant weight and volume reductions are the primary advantages of the WPP system versus the more conventional propulsion technologies used today. WPP thrust is produced by porting high-pressure combustion gases into the water-filled channels of a rotor. Gas expansion results in the expulsion of water from the downstream end of the rotor channel. Solar Turbines Incorporated, a subsidiary of Caterpillar Inc., is currently under contract to the David Taylor Research Center for the development of the high-temperature, high-pressure combustor and rotor seal systems. Details of combustor and rotor seal design, performance, and development test are discussed.

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García-Pérez, Andrés. "Optimum preliminary design of ion thrusters in concurrent design facility." Concurrent Engineering 28, no. 3 (July 20, 2020): 189–97. http://dx.doi.org/10.1177/1063293x20938422.

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In recent years, the development of new satellites has accelerated, especially for small satellites like university-class Cubesats, due to low design and manufacturing costs. The preliminary design of these spacecraft requires the utilization of new tools that improve the interrelation among the different subsystems and optimize the design. One of the most suitable approaches is the concurrent design facility, which connects specialists of each subsystem in the same room to facilitate the communication among them. This method provides different preliminary designs for the complete system by an iterative process in a reduced time, taking into account the simultaneity with the designs of the subsystems. One of the main subsystems of a spacecraft is the propulsion system, which plays a key role in the success of a mission by allowing the spacecraft to reach the final destination. Electric propulsion has become an interesting option due to the high value of the specific impulse, which provides the necessary velocity increment with a lower propellant mass compared to the traditional chemical rockets. The purpose of this paper is to present the equations implemented in the propulsion module of the concurrent design facility to obtain optimum designs of ion thrusters, which supposes a novelty compared to the traditional design approach of these systems, where there is no interaction with the design of the rest of subsystems. The objective is to help the designer to select the best options in a fast and easy way and improve the efficiency of the iterative work of the concurrent design facility.

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Osigwe, Emmanuel O., Arnold Gad-Briggs, and Theoklis Nikolaidis. "Feasibility of a Helium Closed-Cycle Gas Turbine for UAV Propulsion." Applied Sciences 11, no. 1 (December 22, 2020): 28. http://dx.doi.org/10.3390/app11010028.

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When selecting a design for an unmanned aerial vehicle, the choice of the propulsion system is vital in terms of mission requirements, sustainability, usability, noise, controllability, reliability and technology readiness level (TRL). This study analyses the various propulsion systems used in unmanned aerial vehicles (UAVs), paying particular focus on the closed-cycle propulsion systems. The study also investigates the feasibility of using helium closed-cycle gas turbines for UAV propulsion, highlighting the merits and demerits of helium closed-cycle gas turbines. Some of the advantages mentioned include high payload, low noise and high altitude mission ability; while the major drawbacks include a heat sink, nuclear hazard radiation and the shield weight. A preliminary assessment of the cycle showed that a pressure ratio of 4, turbine entry temperature (TET) of 800 °C and mass flow of 50 kg/s could be used to achieve a lightweight helium closed-cycle gas turbine design for UAV mission considering component design constraints.

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Panzeri, Marco, Andrey Savelyev, Kirill Anisimov, Roberto d’Ippolito, and Artur Mirzoyan. "Uncertainty quantification and robust design optimization applied to aircraft propulsion systems." Transportation Research Procedia 29 (2018): 289–302. http://dx.doi.org/10.1016/j.trpro.2018.02.026.

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Terao, Yutaka, Akihisa Seta, Hiroyuki Ohsaki, Hitoshi Oyori, and Noriko Morioka. "Lightweight Design of Fully Superconducting Motors for Electrical Aircraft Propulsion Systems." IEEE Transactions on Applied Superconductivity 29, no. 5 (August 2019): 1–5. http://dx.doi.org/10.1109/tasc.2019.2902323.

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Fioriti, Marco, Luca Boggero, and Sabrina Corpino. "Preliminary Sub-Systems Design Integrated in a Multidisciplinary Design Optimization Framework." Transactions on Aerospace Research 2017, no. 4 (December 1, 2017): 9–23. http://dx.doi.org/10.2478/tar-2017-0025.

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Abstract The aircraft design is a complex subject since several and completely different design disciplines are involved in the project. Many efforts are made to harmonize and optimize the design trying to combine all disciplines together at the same level of detail. Within the ongoing AGILE (Horizon 2020) research, an aircraft MDO (Multidisciplinary Design Optimization) process is setting up connecting several design tools and competences together. Each tool covers a different design discipline such as aerodynamics, structure, propulsion and systems. This paper focuses on the integration of the sub-system design discipline with the others in order to obtain a complete and optimized aircraft preliminary design. All design parameters used to integrate the sub-system branch with the others are discussed as for their redefinition within the different detail level of the design.

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Iftikhar, Muhammad H., Byung-Gun Park, and Ji-Won Kim. "Design and Analysis of a Five-Phase Permanent-Magnet Synchronous Motor for Fault-Tolerant Drive." Energies 14, no. 2 (January 19, 2021): 514. http://dx.doi.org/10.3390/en14020514.

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Reliability is a fundamental requirement in electric propulsion systems, involving a particular approach in studies on system failure probabilities. An intrinsic improvement to the propulsion system involves introducing robust architectures such as fault-tolerant motor drives to these systems. Considering the potential for hardware failures, a fault-tolerant design approach will achieve reliability objectives without recourse to optimized redundancy or over-sizing the system. Provisions for planned degraded modes of operation are designed to operate the motor in fault-tolerant mode, which makes them different from the pure design redundancy approach. This article presents how a five-phase permanent-magnet synchronous motor operates under one- or two-phase faults, and how the system reconfigures post-fault motor currents to meet the torque and speed requirement of reliable operation that meets the requirements of an electric propulsion system.

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Journal articles on the topic 'Propulsion systems design'

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