Relevant bibliographies by topics / Modular propulsion system

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Academic literature on the topic 'Modular propulsion system'

Author: Grafiati
Published: 4 June 2021
Last updated: 9 February 2022

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Journal articles on the topic "Modular propulsion system"

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Yan, Zheng, Xiao Hui Peng, Yu Qiang Cheng, and Jian Jun Wu. "Modeling and Simulation of System Dynamics for Spacecraft Propulsion System." Applied Mechanics and Materials 229-231 (November 2012): 2112–16. http://dx.doi.org/10.4028/www.scientific.net/amm.229-231.2112.

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The spacecraft propulsion system is used for geosynchronous orbit transfer, three-axis stabilization and station-keeping. In order to investigate the system dynamics of spacecraft propulsion system with complex pressurization pipelines and propellant supply pipelines, a modular and extensible simulator UPSSim was developed. The pressurant pipelines were separated into several nodes, each node used lumped parameter model; while the propellant feed pipelines used distributed parameter model. Heat transfer between components and environment was also taken into account. The model accurately predicts the transient behavior of the spacecraft propulsion system during start-up and shutdown process, as well as the effect of pipe initial pressure on the priming waterhammer amplitude. The simulation result demonstrates the adequacy of the modular modeling methodology for spacecraft propulsion system dynamic simulation.
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Igenbergs, E., and M. Kirschner. "A modular propulsion system for the interorbital vehicle." Acta Astronautica 15, no. 8 (1987): 545–50. http://dx.doi.org/10.1016/0094-5765(87)90154-8.

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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 (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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Yan, Zheng, Xiao Hui Peng, Yu Qiang Cheng, and Jian Jun Wu. "System Dynamic Characteristic Simulation of Spacecraft Propulsion System Based on AMESim." Advanced Materials Research 605-607 (December 2012): 679–83. http://dx.doi.org/10.4028/www.scientific.net/amr.605-607.679.

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In order to investigate the dynamic characteristic of the spacecraft propulsion system, numerical simulation was carried out based on the modular and extensible simulation model UPSSim. The model accurately predicts the global behavior of the spacecraft propulsion system in the priming and shutdown process, and also correctly describes the transient behavior of the subsystems. Due to the distributaries of the attitude control thruster supply pipelines, the propellant flow fluctuation attenuates rapidly in the priming process and the waterhammer peak pressure of main engine supply pipelines decreases significantly. The waterhammer waves of the main supply pipelines propagate to the attitude control thruster supply pipelines and dissipate gradually. The farther from the main engine, the later the pressure fluctuates.
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Campora, U., and M. Figari. "Numerical simulation of ship propulsion transients and full-scale validation." Proceedings of the Institution of Mechanical Engineers, Part M: Journal of Engineering for the Maritime Environment 217, no. 1 (2003): 41–52. http://dx.doi.org/10.1243/147509003321623130.

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The paper describes a mathematical model for the dynamics simulation of ship propulsion systems. The model, developed in a MATLAB-SIMULINK software environment, is structured in modular form; the various elements of the system are described as individuals blocks (hull, prime mover, gear, waterjet, etc.) and linked together to take their interactions into account. In this way it is possible to characterize the dynamic behaviour of both the single component and the whole propulsion plant. The model may be used to analyse the system response at off-design and transient conditions. In particular, the developed computer simulation code may be considered as a useful tool to facilitate the correct matching of the prime mover (diesel or gas turbine) to the propulsor (waterjet or propeller) in a wide range of operating conditions. The paper shows the application of the methodology to a cruise ferry used to validate the model results through a full-scale test campaign conducted by the authors during normal operation of the ship.
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Nosseir, Ahmed E. S., Angelo Cervone, and Angelo Pasini. "Modular Impulsive Green Monopropellant Propulsion System (MIMPS-G): For CubeSats in LEO and to the Moon." Aerospace 8, no. 6 (2021): 169. http://dx.doi.org/10.3390/aerospace8060169.

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Green propellants are currently considered as enabling technology that is revolutionizing the development of high-performance space propulsion, especially for small-sized spacecraft. Modern space missions, either in LEO or interplanetary, require relatively high-thrust and impulsive capabilities to provide better control on the spacecraft, and to overcome the growing challenges, particularly related to overcrowded LEOs, and to modern space application orbital maneuver requirements. Green monopropellants are gaining momentum in the design and development of small and modular liquid propulsion systems, especially for CubeSats, due to their favorable thermophysical properties and relatively high performance when compared to gaseous propellants, and perhaps simpler management when compared to bipropellants. Accordingly, a novel high-thrust modular impulsive green monopropellant propulsion system with a micro electric pump feed cycle is proposed. MIMPS-G500mN is designed to be capable of delivering 0.5 N thrust and offers theoretical total impulse Itot from 850 to 1350 N s per 1U and >3000 N s per 2U depending on the burnt monopropellant, which makes it a candidate for various LEO satellites as well as future Moon missions. Green monopropellant ASCENT (formerly AF-M315E), as well as HAN and ADN-based alternatives (i.e., HNP225 and LMP-103S) were proposed in the preliminary design and system analysis. The article will present state-of-the-art green monopropellants in the (EIL) Energetic Ionic Liquid class and a trade-off study for proposed propellants. System analysis and design of MIMPS-G500mN will be discussed in detail, and the article will conclude with a market survey on small satellites green monopropellant propulsion systems and commercial off-the-shelf thrusters.
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Xiao, Nengqi, Ruiping Zhou, and Xiang Xu. "Vibration of diesel-electric hybrid propulsion system with nonlinear component." Journal of Vibration and Control 24, no. 22 (2018): 5353–65. http://dx.doi.org/10.1177/1077546317753010.

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The lumped parameter method is used to model the components of a marine diesel-electric hybrid propulsion system. Modular modeling and five basic models of torsional vibration are used to establish the torsion of the diesel-electric hybrid propulsion system with a nonlinear components vibration mathematical model. In order to include the nonlinear parts of the marine diesel-hybrid propulsion shafting torsional vibration system characteristics, by combining the perturbation method with the advantages and disadvantages of the harmonic method, a perturbation-harmonic method is presented to solve the diesel-electric hybrid propulsion shafting free vibration characteristics. At the same time, the nonlinear vibration characteristics of the hybrid propulsion shaft system are calculated and analyzed using the incremental harmonic balance method. In order to verify the correctness of the theoretical method of hybrid propulsion system, the correctness of the vibration model and method is verified by carrying out actual tests on a 10,000-ton marine surveillance ship. In order to verify the mathematical model of the ship diesel-hybrid propulsion system and the correctness of the theoretical calculation method, the torsional vibration test is carried out by a strain gauge method for a 10,000-ton marine propulsion shaft. The correctness of the torsional vibration mathematical model and the calculation method is verified by comparing the torsional vibration test data and the theoretical calculation data of the ship propulsion shaft system, which provides the theoretical significance for the calculation and analysis of the torsional vibration of the ship propulsion shaft system.
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Cui, Ze, Zeng Jun Han, Hong Wei Pan, Yao Hua Wang, and Xiao Qing Hua. "The Optimization Design of a Propulsion Module for a Mini-ROV." Advanced Materials Research 403-408 (November 2011): 2795–99. http://dx.doi.org/10.4028/www.scientific.net/amr.403-408.2795.

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For a mini remotely operated vehicle (mini-ROV), the performance of the propulsion system has a direct impact on its underwater running and operation. A proper designed propulsion module will improve the maneuverability and controllablity of the mini ROV. In this paper, we propose a kind of propulsion modular series taking lower drag, higher efficiency and lighter weight as design objectives. Simulation and experiment results are also presented to illustrate performance of a specific designed thruster.
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Matlock, Jay, Stephen Warwick, Philipp Sharikov, Jenner Richards, and Afzal Suleman. "Evaluation of energy efficient propulsion technologies for unmanned aerial vehicles." Transactions of the Canadian Society for Mechanical Engineering 43, no. 4 (2019): 481–89. http://dx.doi.org/10.1139/tcsme-2018-0231.

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The transition to cleaner, more efficient and longer-endurance aircraft is at the forefront of research and development in air vehicles. The focus of this research is to experimentally evaluate hybrid propulsion and energy harvesting systems in unmanned aerial vehicles (UAVs). Hybrid systems offer benefits over conventional gasoline and electric systems including lower environmental impacts, reduced fuel consumption, redundancy, and distributed propulsion. Additional energy efficiency can be achieved by harvesting some of the thermal energy of the exhaust gases. The development and experimental evaluation of a hybrid propulsion UAV was carried out at the University of Victoria Center for Aerospace Research (UVIC-CfAR) in the framework of the Green Aviation Research & Development Network (GARDN) grant. The work involved the development of a framework to evaluate UAV hybrid propulsion efficiency, and to predict the amount of power harvestable from thermoelectric generators (TEGs). The objective was to combine all of the components into a modular test bench that will allow the performance of the parallel hybrid system to be characterized and compared with theoretical results. Several experiments were performed to collect performance data of various components including a triple-TEG system connected to an engine, and system variables were modified to simulate flight profiles.
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Machado, Leonardo, Jay Matlock, and Afzal Suleman. "Experimental evaluation of a hybrid electric propulsion system for small UAVs." Aircraft Engineering and Aerospace Technology 92, no. 5 (2019): 727–36. http://dx.doi.org/10.1108/aeat-06-2019-0120.

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Purpose This paper aims to experimentally evaluate the performance of a parallel hybrid propulsion system for use in small unmanned aerial vehicles (UAVs). Design/methodology/approach The objective is to combine all the individual components of the hybrid electric propulsion system (HEPS) into a modular test bench to characterize the performance of a parallel hybrid propulsion system, and to evaluate a rule-based controller based on the ideal operating line concept for the control of the power plant. Electric motor (EM) designed to supplement the power of the internal combustion engine (ICE) to reduce the overall fuel consumption, with the supervisory controller optimizing ICE torque. Findings The EM was able to supplement the power of the ICE to reduce fuel consumption, and proved the capability of acting as a generator to recharge the batteries drawing from ICE power. Furthermore, the controller showed that it is possible to reduce the fuel consumption with a HEPS when compared to its gasoline counterpart by running simulated representative UAV missions. The findings also highlighted the challenges to build and integrate the HEPS in small UAVs. Originality/value The modularity of the test bench allows each component to be changed to assess its impact on the performance of the system. This allows for further exploration and improvements of the HEPS in a controlled environment.
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Dissertations / Theses on the topic "Modular propulsion system"

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Skendraoui, Nadir. "FAUTEUIL ROULANT MANUEL OPTIMISE ET MODULABLE." Thesis, Reims, 2020. http://www.theses.fr/2020REIMS018.

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Le fauteuil roulant manuel (FRM) fait partie de la vie quotidienne des personnes atteintes d’handicape moteur. L’objectif de cette thèse est de développer un nouveau FRM basé sur une approche mécanique qui permet de quantifier les efforts résistants dans le but final de concevoir un nouveau système de propulsion manuel modulable qui équipera le FRM. L’approche mécanique fait intervenir plusieurs paramètres cinématiques (vitesse, accélération…) et dynamiques (force de propulsion, résistance au roulement, résistance de l’air…) pour quantifier la charge résistante qui sera par la suite utilisé pour l’étude biomécanique ainsi que pour le dimensionnement de la propulsion. Le FRM sera optimisé pour des personnes handicapé moteurs et sera capable de fournir une propulsion mécanique plus ergonomique et donc moins stressante. L’ergonomie ainsi que la nouvelle architecture du FRM sont basée sur une étude biomécanique numérique et expérimentale qui a été menée en partenariat avec l’université de Technologie de Varsovie. Le fauteuil roulant comportera également un nouveau châssis en aluminium équipée de roue sans moyeu qui permet d’avoir une esthétique nouvelle et meilleure interaction d’effort au niveau de la roue. Cette étude s’articulera donc sur trois parties distinctes ; quantification de la charge résistante durant une propulsion en fauteuil roulant, étude et analyse biomécanique de la propulsion mécanique et enfin conception du nouveau fauteuil roulant manuel avec un nouveau système de propulsion optimisé et modulable<br>Manual wheelchair (MW) still a part of the daily life of people with disabilities. The objective of this thesis is to develop a new MW based on a mechanical approach which quantifies the resistant forces during propulsion with the final aim is designing a new modular manual propulsion system which will equip the FRM. The mechanical approach involves several kinematic parameters like speed, acceleration, and also dynamics parameters like propulsive force, rolling resistance, and air resistance, to quantify the resistant load which will subsequently be used for the biomechanical study as well than for the sizing of the propulsion. The FRM will be optimized for people with motor disabilities and will be able to provide mechanical propulsion that is more ergonomic and therefore less stressful. The ergonomics as well as the new architecture of the FRM are based on a numerical and experimental biomechanical study which was carried out in partnership with the Warsaw’s University of Technology. The wheelchair will also feature a new aluminum frame fitted with a hubless wheels that provides new aesthetics with a better wheel-ground effort's interaction. This study will be therefore structured around three distinct parts; quantification of the resistant load during wheelchair propulsion, biomechanical analysis of the mechanical manual propulsion and finally design of the new manual wheelchair with a new optimized and modular propulsion system
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Sarar, Stephen F. "A galvanically isolated power converter module for DC Zonal Electric Distribution Systems." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2006. http://library.nps.navy.mil/uhtbin/hyperion/06Mar%5FSarar.pdf.

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Thesis (M.S. in Electrical Engineering)--Naval Postgraduate School, March 2006.<br>Thesis Advisor(s): Robert W. Ashton, Andrew A. Parker. "March 2006." Includes bibliographical references (p. 73). Also available online.
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Nelms, Robert Mark. "Simulation of spacecraft power systems using a modular state variable approach." Diss., Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/53653.

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The power requirements for future spacecraft power systems will be on the order of a few hundred kilowatts to a few megawatts. Because of these power levels, a high-voltage, high-power distribution subsystem may be utilized to transmit power from the source to the different loads. Using current state-of-the-art power conditioning electronics, complex series and parallel configurations will be required at the interface between the source and the distribution subsystem and between the distribution subsystem and the loads. The dynamic response of such a spacecraft power system may be obtained using a general purpose program such as SPICE2. However, for large and complex spacecraft power systems, the input file will be large and complex with correspondingly large computation times. As an alternative, the spacecraft power system can be considered as an interconnection of modular components. Each component is treated as a two-port network, and a state model is written with the port voltages as the inputs. The state model of each component is solved using the state transition matrix and assuming that the port voltages are . clamped for each time step. This calculation proceeds as if all two-port networks are decoupled. After the state variables have been updated, the inputs to all components are calculated using network analysis principles. The solution procedure alternates between solving the dynamic model of all components and the network equations for the component inputs. The modular state variable approach and SPICE2 are compared using two example systems. This comparison shows the advantages of the modular state variable approach. First, for the modular state variable approach the system is considered as an interconnection of modular components. In SPICE2, the system is treated as an interconnection of circuit elements. As a result, the system description for large and complex spacecraft power systems is much _ larger and more complex than a modular state variable description. Secondly, the modular state variable approach requires less CPU time than SPICE2. For one of the example systems presented here, the modular state variable approach uses one-twentieth of the CPU time used by SPICE2.<br>Ph. D.
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Flath, Allen III. "Mathematical Programming Approach for the Design of Satellite Power Systems." UKnowledge, 2019. https://uknowledge.uky.edu/ece_etds/136.

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Satellite power systems can be understood as islanded dc microgrids supplied by specialized and coordinated solar cell arrays augmented by electrochemical battery systems to handle high-power loads and periods of eclipse. The periodic availability of power, the limited capacity of batteries, and the dependence of all mission service on power consumption create a unique situation in which temporal power and energy scarcity exist. A multi-period model of an orbital satellite power system’s performance over a mission’s duration can be constructed. A modular power system architecture is used to characterize the system’s constraints. Using mathematical programming, an optimization problem can be posed such that the optimal power and energy ratings for the power system are determined for any load schedule imposed by a given mission’s requirements. The optimal energy trajectory of the electrical power system over a mission’s duration is also determined when the mathematical programming problem is solved. A generic set of mission requirements is identified to test this approach, but the objective function of the resulting optimization problem can be modified to return different results. These results can provide a clear illustration of the trade-offs that designers of such power systems consider in the design process.
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Books on the topic "Modular propulsion system"

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L, Felder James, and United States. National Aeronautics and Space Administration., eds. Predicted performance of an integrated modular engine system. National Aeronautics and Space Administration, 1993.

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C, Rapp Douglas, and United States. National Aeronautics and Space Administration., eds. Reliability studies of Integrated modular engine system designs. National Aeronautics and Space Administration, 1993.

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Reliability studies of Integrated modular engine system designs. National Aeronautics and Space Administration, 1993.

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High leverage space transportation system technologies for human exploration missions to the moon and beyond. National Aeronautics and Space Administration, 1996.

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Book chapters on the topic "Modular propulsion system"

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Howe, Steven D. "Advanced Propulsion: Pulsed, Fusion, Antimatter and Breakthrough Physics." In Reference Module in Earth Systems and Environmental Sciences. Elsevier, 2020. http://dx.doi.org/10.1016/b978-0-12-819725-7.00022-2.

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Conference papers on the topic "Modular propulsion system"

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Nelson, Steven D., and Peter Current. "Modular Architecture Propulsion System (MAPS™)." In 2018 Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4704.

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EMERICK, ROGER, and JAMES O'COIN. "A modular propulsion system for missile attitude control." In 25th Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2952.

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MORANO, JOSEPH, and JOHN HENDERSON. "A modular propulsion system required for Space Station assembly." In 25th Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2613.

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Sievers, Robert K., Thomas K. Hunt, Joseph F. Ivanenok, Jan E. Pantolin, and David A. Butkiewicz. "Modular radioisotope AMTEC power system." In Proceedings of the tenth symposium on space nuclear power and propulsion. AIP, 1993. http://dx.doi.org/10.1063/1.43168.

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HARDY, TERRY, and DOUGLAS RAPP. "Reliability studies of Integrated Modular Engine system designs." In 29th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1886.

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FRANKENFIELD, BRUCE, and JERRY CAREK. "Fluid design studies of integrated modular engine system." In 29th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1887.

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BINDER, MICHAEL, and JAMES FELDER. "Predicted performance of an Integrated Modular Engine system." In 29th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1888.

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HOBBS, L. "The design of a general purpose modular propellant feed system." In 26th Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1939.

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Allotta, Benedetto, Riccardo Costanzi, Jonathan Gelli, Luca Pugi, and Alessandro Ridolfi. "Design of a modular propulsion system for MARTA AUV." In OCEANS 2015 - Genova. IEEE, 2015. http://dx.doi.org/10.1109/oceans-genova.2015.7271397.

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Spichartz, M., V. Staudt, and A. Steimel. "Modular Multilevel Converter for propulsion system of electric ships." In 2013 IEEE Electric Ship Technologies Symposium (ESTS 2013). IEEE, 2013. http://dx.doi.org/10.1109/ests.2013.6523740.

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Reports on the topic "Modular propulsion system"

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Kelly, K., J. Brown, G. Kamsickas, and W. Tucker. Modular Simulator System (MSS). System/Segment Specification for the Generic Modular Simulator System - Propulsion Module Propulsion Module. Volume 5. Defense Technical Information Center, 1993. http://dx.doi.org/10.21236/ada276972.

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