Journal articles: 'Advanced Propulsion'

1

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

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

Full text

Abstract:

Abstract An integrated parametric model involving the design of propulsion system, airframe and flight mission is presented. Based hereon, the carbon dioxide (CO2) emission characteristics of advanced direct-drive turbofan and open rotor powered aircraft are analysed against pertinent aircraft and propulsion system design parameters. In addition, initial concept-specific trend statements on nitrogen oxides (NOx) as well as propulsor noise emission characteristics are derived. The obtained results contribute to a better understanding of more appropriate aircraft design attributes for advanced system architectures.

APA, Harvard, Vancouver, ISO, and other styles

3

Cruse, T. A., J. F. Unruh, Y. T. Wu, and S. V. Harren. "Probabilistic Structural Analysis for Advanced Space Propulsion Systems." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 251–60. http://dx.doi.org/10.1115/1.2906171.

Full text

Abstract:

This paper reports on recent extensions to ongoing research into probabilistic structural analysis modeling of advanced space propulsion system hardware. The advances concern probabilistic dynamic loading, and probabilistic nonlinear material behavior. In both cases, the reported work represents a significant advance in the state-of-the-art for these topics. Random, or probabilistic loading is normally concerned with the loading described in power spectral density (PSD) terms. The current work describes a method for incorporating random PSD’s along with random material properties, damping, and structural geometry. The probabilistic material response is concerned with the prediction of nonlinear stress-strain behavior for physical processes that can be linked to the original microstructure of the material. Such variables as grain size and orientation, grain boundary strength, etc., are treated as random, initial variables in generating stochastic stress-strain curves. The methodology is demonstrated for a creep simulation.

APA, Harvard, Vancouver, ISO, and other styles

4

Reisz, Aloysius I. "To Go Beyond." Mechanical Engineering 130, no. 11 (November 1, 2008): 42–45. http://dx.doi.org/10.1115/1.2008-nov-2.

Full text

Abstract:

This article discusses experiments with an advanced electromagnetic engine that aims for high-speed, long-distance transportation to reach farther into space. Experimental work at Marshall Space Flight Center in Alabama is attempting to develop an electromagnetic engine designed to achieve higher velocities than current space-engine options and to last longer, too. Space engines with higher specific impulse will sense new science from deep space exploration quicker. In a way, higher specific impulse quickens our intelligence acquisition. Reisz Engineers and the University of Michigan are investigating the propulsive performances of an experimental advanced electromagnetic engine configuration. This electromagnetic propulsion configuration has a magnetic nozzle and the engine performance can be throttled. Electromagnetic propulsion systems can also be configured for operations in Earth space environment, and for lunar robotic and lunar mapping missions. Electromagnetic and fusion space engines promise fast and reliable propulsion systems, which will be needed if mankind is to pursue its exploration of the outer realms of our solar system and beyond.

APA, Harvard, Vancouver, ISO, and other styles

5

Herdrich, G., U. Bauder, A. Boxberger, R. A. Gabrielli, M. Lau, D. Petkow, M. Pfeiffer, C. Syring, and S. Fasoulas. "Advanced plasma (propulsion) concepts at IRS." Vacuum 88 (February 2013): 36–41. http://dx.doi.org/10.1016/j.vacuum.2012.02.032.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

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

Full text

Abstract:

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

APA, Harvard, Vancouver, ISO, and other styles

11

Van Dine, Piet. "Manufacture of a Prototype Advanced Permanent Magnet Motor Pod." Journal of Ship Production 19, no. 02 (May 1, 2003): 91–97. http://dx.doi.org/10.5957/jsp.2003.19.2.91.

Full text

Abstract:

Podded propulsion is prevalent in the marine industry. Podded propulsion systems provide many advantages to the ship owner, including increased propulsion efficiency and reduced construction cost. To evaluate the potential of a new pod configuration, a prototype machine was constructed and tested. This prototype machine was mainly constructed of composite parts. The propeller, housings, structural blading, motor canning, and fairings were constructed of composite materials. Composite materials were chosen as a cost saving, schedule reduction, performance enhancement, and as a technology demonstration. This paper will review the unit construction, and test results, focusing on the lessons learned for the composite part manufacture.

APA, Harvard, Vancouver, ISO, and other styles

12

Frisbee, Robert H. "Advanced Space Propulsion for the 21st Century." Journal of Propulsion and Power 19, no. 6 (November 2003): 1129–54. http://dx.doi.org/10.2514/2.6948.

Full text

APA, Harvard, Vancouver, ISO, and other styles

13

Peacock, N. J., and J. H. R. Sadler. "Advanced propulsion systems for large subsonic transports." Journal of Propulsion and Power 8, no. 3 (May 1992): 703–8. http://dx.doi.org/10.2514/3.23535.

Full text

APA, Harvard, Vancouver, ISO, and other styles

14

Guzzella, L. "Modeling and Control of Advanced Propulsion Systems." Oil & Gas Science and Technology - Revue de l'IFP 62, no. 4 (July 2007): 585–94. http://dx.doi.org/10.2516/ogst:2007040.

Full text

APA, Harvard, Vancouver, ISO, and other styles

15

Bundesmann, C., C. Eichhorn, F. Scholze, D. Spemann, H. Neumann, F. Scortecci, H. J. Leiter, et al. "Advanced Electric Propulsion Diagnostic Tools at IOM." Procedia Engineering 185 (2017): 1–8. http://dx.doi.org/10.1016/j.proeng.2017.03.283.

Full text

APA, Harvard, Vancouver, ISO, and other styles

16

Sobel, D. R., and L. J. Spadaccini. "Hydrocarbon Fuel Cooling Technologies for Advanced Propulsion." Journal of Engineering for Gas Turbines and Power 119, no. 2 (April 1, 1997): 344–51. http://dx.doi.org/10.1115/1.2815581.

Full text

Abstract:

Storable hydrocarbon fuels that undergo endothermic reaction provide an attractive heat sink for future high-speed aircraft. An investigation was conducted to explore the endothermic potential of practical fuels, with inexpensive and readily available catalysts, under operating conditions simulative of high-speed flight applications. High heat sink capacities and desirable reaction products have been demonstrated for n-heptane and Norpar 12 fuels using zeolite catalysts in coated-tube reactor configurations. The effects of fuel composition and operating condition on extent of fuel conversion, product composition, and the corresponding endotherm have been examined. The results obtained in this study provide a basis for catalytic-reactor/heat-exchanger design and analysis.

APA, Harvard, Vancouver, ISO, and other styles

17

SFORZA, P. M., and J. L. REMO. "NEO Mission Dynamics and Advanced Space Propulsion." Annals of the New York Academy of Sciences 822, no. 1 Near-Earth Ob (May 1997): 432–46. http://dx.doi.org/10.1111/j.1749-6632.1997.tb48359.x.

Full text

APA, Harvard, Vancouver, ISO, and other styles

18

Moreau, Stéphane, and Michel Roger. "Advanced noise modeling for future propulsion systems." International Journal of Aeroacoustics 17, no. 6-8 (July 28, 2018): 576–99. http://dx.doi.org/10.1177/1475472x18789005.

Full text

Abstract:

In order to meet noise specifications for future foreseen aircraft propulsion systems, such as for ultrahigh bypass ratio turbofans and contra-rotating open rotors, the dominant turbomachinery noise mechanisms need to be modeled accurately at an early design stage. Two novel methods are presented here, which could significantly improve the existing analytical noise models. For the high-solidity ultrahigh bypass ratio, a mode-matching technique based on a modal expansion of acoustic and vortical variables in each subdomain of a blade row is shown to accurately reproduce sound generation and propagation in two-dimensional bifurcated channels and in three-dimensional annular unstaggered flat-plate cascades. For the low solidity contra-rotating open rotors, several extensions to Amiet’s compressible isolated airfoil theory are coupled with Curle’s and Ffowcs Williams and Hawkings’ acoustic analogy in the frequency domain within a strip theory framework, to yield both far-field tonal and broadband noise. Including sweep in both tonal and broadband noise models is shown to significantly improve the comparison with experiments on a stationary swept airfoil in a uniform turbulent stream and on a realistic contra-rotating open rotor geometry at approach conditions.

APA, Harvard, Vancouver, ISO, and other styles

19

Schoerman, Leonard. "High-pressure propulsion - advanced concepts for cooling." Acta Astronautica 14 (January 1986): 423–38. http://dx.doi.org/10.1016/0094-5765(86)90143-8.

Full text

APA, Harvard, Vancouver, ISO, and other styles

20

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

21

Lotfy, A., W. Anis, and Joseph V. M. Halim. "Design PV system for a small GEO satellite and studying the effect of using different types of propulsion." International Journal of Advances in Applied Sciences 8, no. 1 (March 1, 2019): 54. http://dx.doi.org/10.11591/ijaas.v8.i1.pp54-63.

Full text

Abstract:

<p>This paper presents an optimum design of the solar Photo-Voltaic (PV) power system for small Geostationary Earth Orbit (GEO) satellites using triple junction solar cells and advanced Lithium Ion batteries. The paper applies the proposed system on various propulsion technologies; full chemical, full electrical and hybrid propulsions. This research work studies the capability to fulfil efficiently all the satellite power requirements during both the launching and the on-station phases while reducing the high cost challenge. Since the propulsion type is a key factor for the satellite cost, an economic analysis is demonstrated and investigated in two different strategies. The first scenario fixes the satellite weight and offers the revenue due to the increase in the satellite payload. However, the second scenario evaluates the saving profits due to the reduction in the satellite weight using the same number of satellite transponders. The analytical comparison among the different propulsion techniques shows the superior advantages of using the full electrical satellites. </p>

APA, Harvard, Vancouver, ISO, and other styles

22

Kirner, Rudi, Lorenzo Raffaelli, Andrew Rolt, Panagiotis Laskaridis, Georgios Doulgeris, and Riti Singh. "An assessment of distributed propulsion: Advanced propulsion system architectures for conventional aircraft configurations." Aerospace Science and Technology 46 (October 2015): 42–50. http://dx.doi.org/10.1016/j.ast.2015.06.022.

Full text

APA, Harvard, Vancouver, ISO, and other styles

23

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

24

Özden, Yasemin Arıkan, Münir Cansın Özden, Ersin Demir, and Sertaç Kurdoğlu. "Experimental and Numerical Investigation of DARPA Suboff Submarine Propelled with INSEAN E1619 Propeller for Self-Propulsion." Journal of Ship Research 63, no. 4 (December 1, 2019): 235–50. http://dx.doi.org/10.5957/josr.09180084.

Full text

Abstract:

The Defense Advanced Research Projects Agency (DARPA) Suboff Submarine propelled by the Italian Ship Model Basin (INSEAN) E1619 propeller is extensively used in submarine validation studies. Although there are several numerical studies where the DARPA Suboff submarine is used in combination with E1619 propeller there are no experimental data available in open literature for the self-propulsion condition. In this article, the self-propulsion characteristics of the DARPA Suboff submarine model with INSEAN E1619 propeller obtained with experimental and numerical methods are presented and discussed by means of Taylor wake fraction, thrust deduction, hull efficiency, relative rotative efficiency, and propulsive efficiency. To experimentally investigate the submarine form, a self-propulsion experimental setup is designed and manufactured. Resistance and self-propulsion experiments are conducted in Istanbul Technical University Ata Nutku Ship Model Testing Laboratory. Resistance tests are carried out for three different speeds, and the results show good agreement with the published experimental results. Propulsion tests are conducted by using the load-varying self-propulsion test method for constant speed and seven different propeller rotation rates. Rotational speed, thrust, and torque forces at self-propulsion point are investigated. For the numerical computations a commercial Computational Fluid Dynamics (CFD) code is used. Propeller open water characteristics and nondimensional velocities behind the propeller are calculated. Self-propulsion point of the submarine and propeller assembly is also solved numerically and the results are compared with the results obtained from the experiments, and it is seen that especially the propeller rate of revolution and thrust force are predicted with very good approximation.

APA, Harvard, Vancouver, ISO, and other styles

25

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

26

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

27

DADE, THOMAS B. "Advanced Electric Propulsion, Power Generation, and Power Distribution." Naval Engineers Journal 106, no. 2 (March 1994): 83–92. http://dx.doi.org/10.1111/j.1559-3584.1994.tb02824.x.

Full text

APA, Harvard, Vancouver, ISO, and other styles

28

Petteri, Ämmälä. "CRP Azipod Propulsion Concept-Advanced Cost-Effective Solution." Journal of The Japan Institute of Marine Engineering 39, no. 9 (2004): 544–54. http://dx.doi.org/10.5988/jime.39.544.

Full text

APA, Harvard, Vancouver, ISO, and other styles

29

Roth, M., and B. G. Logan. "Advanced space power and propulsion based on lasers." European Physical Journal Special Topics 224, no. 13 (October 2015): 2657–63. http://dx.doi.org/10.1140/epjst/e2015-02578-4.

Full text

APA, Harvard, Vancouver, ISO, and other styles

30

Turk, M. A., and P. K. Zeiner. "Advanced technology payoffs for future small propulsion systems." Journal of Propulsion and Power 3, no. 4 (July 1987): 313–19. http://dx.doi.org/10.2514/3.22992.

Full text

APA, Harvard, Vancouver, ISO, and other styles

31

KANDA, Takeshi. "Research Activities of Advanced Propulsion Technology in JAXA." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7, ists26 (2009): Ta_1—Ta_5. http://dx.doi.org/10.2322/tstj.7.ta_1.

Full text

APA, Harvard, Vancouver, ISO, and other styles

32

Jackson, T. A., D. R. Eklund, and A. J. Fink. "High speed propulsion: Performance advantage of advanced materials." Journal of Materials Science 39, no. 19 (October 2004): 5905–13. http://dx.doi.org/10.1023/b:jmsc.0000041687.37448.06.

Full text

APA, Harvard, Vancouver, ISO, and other styles

33

Thomas, Ulrich. "Comparison of advanced propulsion systems in cislunar space." Acta Astronautica 12, no. 1 (January 1985): 53–59. http://dx.doi.org/10.1016/0094-5765(85)90009-8.

Full text

APA, Harvard, Vancouver, ISO, and other styles

34

Szuch, John R. "Application of advanced computational technology to propulsion CFD." Computers & Structures 30, no. 1-2 (January 1988): 375–84. http://dx.doi.org/10.1016/0045-7949(88)90243-x.

Full text

APA, Harvard, Vancouver, ISO, and other styles

35

Winterberg, F. "Advanced charged particle beam ignited nuclear pulse propulsion." Acta Astronautica 64, no. 11-12 (June 2009): 1080–84. http://dx.doi.org/10.1016/j.actaastro.2009.01.054.

Full text

APA, Harvard, Vancouver, ISO, and other styles

36

Rosato, Daniel A., Mason Thornton, Jonathan Sosa, Christian Bachman, Gabriel B. Goodwin, and Kareem A. Ahmed. "Stabilized detonation for hypersonic propulsion." Proceedings of the National Academy of Sciences 118, no. 20 (May 10, 2021): e2102244118. http://dx.doi.org/10.1073/pnas.2102244118.

Full text

Abstract:

Future terrestrial and interplanetary travel will require high-speed flight and reentry in planetary atmospheres by way of robust, controllable means. This, in large part, hinges on having reliable propulsion systems for hypersonic and supersonic flight. Given the availability of fuels as propellants, we likely will rely on some form of chemical or nuclear propulsion, which means using various forms of exothermic reactions and therefore combustion waves. Such waves may be deflagrations, which are subsonic reaction waves, or detonations, which are ultrahigh-speed supersonic reaction waves. Detonations are an extremely efficient, highly energetic mode of reaction generally associated with intense blast explosions and supernovas. Detonation-based propulsion systems are now of considerable interest because of their potential use for greater propulsion power compared to deflagration-based systems. An understanding of the ignition, propagation, and stability of detonation waves is critical to harnessing their propulsive potential and depends on our ability to study them in a laboratory setting. Here we present a unique experimental configuration, a hypersonic high-enthalpy reaction facility that produces a detonation that is fixed in space, which is crucial for controlling and harnessing the reaction power. A standing oblique detonation wave, stabilized on a ramp, is created in a hypersonic flow of hydrogen and air. Flow diagnostics, such as high-speed shadowgraph and chemiluminescence imaging, show detonation initiation and stabilization and are corroborated through comparison to simulations. This breakthrough in experimental analysis allows for a possible pathway to develop and integrate ultra-high-speed detonation technology enabling hypersonic propulsion and advanced power systems.

APA, Harvard, Vancouver, ISO, and other styles

37

McGlone, M. E. "Transition of a Technology Base for Advanced Aircraft Gas Turbine Control Systems." Journal of Engineering for Gas Turbines and Power 120, no. 3 (July 1, 1998): 437–41. http://dx.doi.org/10.1115/1.2818163.

Full text

Abstract:

Technology assessments during the 1980s projected the development of advanced military fighter aircraft that would require propulsion systems that could accommodate multimission capability with super maneuverability. These propulsion systems would be required to provide significantly improved thrust to weight, reduced thrust specific fuel consumption, and up and away thrust vectoring capabilities. Digital electronic control systems with significantly expanded capabilities would be required to handle these multifunction control actuation systems, to integrate them with flight control systems, and to provide fail-operational capability. This paper will discuss the challenges that were presented to propulsion system control designers, the innovation of technology to address these challenges, and the transition of that technology to production readiness. Technology advancements will be discussed in the area of digital electronic control capability and packaging, advanced fuel management systems, high pressure fuel hydraulic actuation systems for multifunction nozzles, integrated flight propulsion controls, and higher-order language software development tools. Each of these areas provided unique opportunities where technology development programs and flight prototyping carried concepts to reality.

APA, Harvard, Vancouver, ISO, and other styles

38

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

39

Szelecka, Agnieszka. "Advanced laboratory for testing plasma thrusters and Hall thruster measurement campaign." Nukleonika 61, no. 2 (June 1, 2016): 213–18. http://dx.doi.org/10.1515/nuka-2016-0036.

Full text

Abstract:

Abstract Plasma engines are used for space propulsion as an alternative to chemical thrusters. Due to the high exhaust velocity of the propellant, they are more efficient for long-distance interplanetary space missions than their conventional counterparts. An advanced laboratory of plasma space propulsion (PlaNS) at the Institute of Plasma Physics and Laser Microfusion (IPPLM) specializes in designing and testing various electric propulsion devices. Inside of a special vacuum chamber with three performance pumps, an environment similar to the one that prevails in space is created. An innovative Micro Pulsed Plasma Thruster (LμPPT) with liquid propellant was built at the laboratory. Now it is used to test the second prototype of Hall effect thruster (HET) operating on krypton propellant. Meantime, an improved prototype of krypton Hall thruster is constructed.

APA, Harvard, Vancouver, ISO, and other styles

40

Denning, R. M., and N. A. Mitchell. "Trends in Military Aircraft Propulsion." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 203, no. 1 (January 1989): 11–23. http://dx.doi.org/10.1243/pime_proc_1989_203_049_01.

Full text

Abstract:

The major factors determining the choice of engine cycle for a combat aircraft are the requirements of the design mission and those of aircraft speed and agility. The requirement for jet-borne flight in short take-off vertical landing (STOVL) aircraft imposes further demands on cycle and configuration. The changing nature of combat aircraft requirements is the reason for changes in engine design. Specific thrust is shown to be the major parameter defining engine suitability for a particular role. An examination of mixed turbofan characteristics shows that specific thrust is also the key to understanding the relationships between engine characteristics. The future development of combat engines is discussed, in particular the implications of stoichiometric limits on cycle temperatures and the benefits of variable cycle engines are examined. Recent work on advanced STOVL (ASTOVL) aircraft is reviewed and aircraft/engine concepts designed to meet the requirements of the role are assessed. Experience shows that the technology for these advanced engines must be fully demonstrated before production to minimize the risks and costs of the development programme.

APA, Harvard, Vancouver, ISO, and other styles

41

Jansen, Ralph H., Cheryl L. Bowman, Sean Clarke, David Avanesian, Paula J. Dempsey, and Rodger W. Dyson. "NASA electrified aircraft propulsion efforts." Aircraft Engineering and Aerospace Technology 92, no. 5 (December 6, 2019): 667–73. http://dx.doi.org/10.1108/aeat-05-2019-0098.

Full text

Abstract:

Purpose This paper aims to review national aeronautics and space administration (NASA’s) broad investments in electrified aircraft propulsion (EAP). NASA investments are guided by an assessment of potential market impacts, technical key performance parameters, and technology readiness attained through a combination of studies, enabling fundamental research and flight research. Design/methodology/approach The impact of EAP varies by market and NASA is considering three markets as follows: national/international, on-demand mobility and short-haul regional air transport. Technical advances in key areas have been made that indicate EAP is a viable technology. Flight research is underway to demonstrate integrated solutions and inform standards and certification processes. Findings A key finding is that sufficient technical advances in key areas have been made, which indicate EAP is a viable technology for aircraft. Significant progress has been made to reduce EAP adoption barriers and further work is needed to transition the technology to a commercial product and improve the technology, so it is applicable to large transonic aircraft. Practical implications Significant progress has been made to reduce EAP adoption barriers and further work is needed to transition the technology to a commercial product and improve the technology, so it is applicable to large transonic aircraft. Originality/value This paper will review the activities of the hybrid gas-electric subproject of the Advanced Air Transport Technology Project, the Revolutionary Vertical Lift Technology Project and the X-57 Flight Demonstration Project, and discuss the potential EAP benefits for commercial and military applications. This paper focuses on the vehicle-related activities, however, there are related NASA activities in air space management and vehicle autonomy activities, as well as a breakthrough technology project called the Convergent Aeronautics Solutions Project. The target audience is people interested in EAP.

APA, Harvard, Vancouver, ISO, and other styles

42

Immer, Marc, and Philipp Georg Juretzko. "Advanced aircraft performance analysis." Aircraft Engineering and Aerospace Technology 90, no. 4 (May 8, 2018): 627–38. http://dx.doi.org/10.1108/aeat-11-2016-0205.

Full text

Abstract:

Purpose The preliminary aircraft design process comprises multiple disciplines. During performance analysis, parameters of the design mission have to be optimized. Mission performance optimization is often challenging, especially for complex mission profiles (e.g. for unmanned aerial vehicles [UAVs]) or hybrid-electric propulsion. Therefore, the purpose of this study is to find a methodology that supports aircraft performance analysis and that is applicable to complex profiles and to novel designs. Design/methodology/approach As its core element, the developed method uses a computationally efficient C++ software “Aircraft Performance Program” (APP), which performs a segment-based mission computation. APP performs a time integration of the equations of motion of a point mass in the vertical plane. APP is called via a command line interface from a flexible scripting language (Python). On top of APP’s internal radius of action optimization, state-of-the-art optimization packages (SciPy) are used. Findings The application of the method to a conventional climb schedule shows that the definition of the top of climb has a significant influence on the resulting optimum. Application of the method to a complex UAV mission optimization, which included maximizing the radius of action, was successful. Low computation time enables to perform large parametric studies. This greatly improves the interpretation of the results. Research limitations/implications The scope of the paper is limited to the methodology that allows for advanced performance analysis at the conceptual and preliminary design stages with an emphasis on novel propulsion concepts. The methodology is developed using existing, validated methods, and therefore, this paper does not contain comprehensive validation. Other disciplines, such as cost analysis, life-cycle assessment or market analysis, are not considered. Practical implications With the proposed method, it is possible to obtain not only the desired optimum mission performance but also off-design performance of the investigated design. A thorough analysis of the mission performance provides insight into the design’s capabilities and shortcomings, ultimately aiding in obtaining a more efficient design. Originality/value Recent developments in the area of hybrid or hybrid-electric propulsion systems have shown the need for performance computation tools aiding the related design process. The presented method is especially valuable when novel design concepts with complex mission profiles are investigated.

APA, Harvard, Vancouver, ISO, and other styles

43

Hession, Sandra, and Janet King. "Motility—The Power of Propulsion." Gastroenterology Nursing 31, no. 2 (March 2008): 166. http://dx.doi.org/10.1097/01.sga.0000316589.74360.45.

Full text

APA, Harvard, Vancouver, ISO, and other styles

44

Grzesiak, Szymon. "Alternative Propulsion Plants for Modern LNG Carriers." New Trends in Production Engineering 1, no. 1 (October 1, 2018): 399–407. http://dx.doi.org/10.2478/ntpe-2018-0050.

Full text

Abstract:

Abstract This paper shows the latest evolution trends of propulsion plants of modern LNG tankers. Features of conventional and advanced steam plants were confronted with propulsion plants such as Dual Fuel – Diesel electric and plants equipped with slow speed two stroke diesel engines. Propulsion plants were compared in terms of plant efficiency, reliability and environmental. The shipyard’s order book and the active fleet of LNG carriers with a capacity above 65000 m3 were analyzed.

APA, Harvard, Vancouver, ISO, and other styles

45

Bogdanov, A., A. Ivanovsky, and P. Adamovich. "Modern and advanced control algorithms for synchronous propulsion motors." Transactions of the Krylov State Research Centre 4, no. 382 (2017): 103–12. http://dx.doi.org/10.24937/2542-2324-2017-4-382-103-112.

Full text

APA, Harvard, Vancouver, ISO, and other styles

46

Barkhoudarian, S., G. S. Cross, and Carl F. Lorenzo. "Advanced instrumentation for next-generation aerospace propulsion control systems." Journal of Propulsion and Power 12, no. 1 (January 1996): 205–6. http://dx.doi.org/10.2514/3.24012.

Full text

APA, Harvard, Vancouver, ISO, and other styles

47

Stanley, Douglas O., and T. A. Talay. "Propulsion system optimization for Advanced Manned Launch System vehicles." Journal of Spacecraft and Rockets 27, no. 3 (May 1990): 246–52. http://dx.doi.org/10.2514/3.26132.

Full text

APA, Harvard, Vancouver, ISO, and other styles

48

Palaszewski, Bryan. "Lunar missions using advanced chemical propulsion - System design issues." Journal of Spacecraft and Rockets 31, no. 3 (May 1994): 458–65. http://dx.doi.org/10.2514/3.26461.

Full text

APA, Harvard, Vancouver, ISO, and other styles

49

Paniagua, Guillermo, Szabolcs Szokol, Hiromasa Kato, Giovanni Manzini, and Richard Varvill. "Contrarotating Turbine Aerodesign for an Advanced Hypersonic Propulsion System." Journal of Propulsion and Power 24, no. 6 (November 2008): 1269–77. http://dx.doi.org/10.2514/1.35612.

Full text

APA, Harvard, Vancouver, ISO, and other styles

50

Blythe, Alan. "Potential application of advanced propulsion systems to civil aircraft." Journal of Aircraft 25, no. 2 (February 1988): 141–46. http://dx.doi.org/10.2514/3.45554.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Journal articles on the topic 'Advanced Propulsion'

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles