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Journal articles on the topic 'Combustion and propulsion'

Author: Grafiati

Published: 3 June 2025

Last updated: 31 July 2025

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1

ORKISZ, Marek, Piotr WYGONIK, Michał KUŹNIAR, and Maciej KALWARA. "Comparative analysis of combustion engine and hybrid propulsion unit in aviation application in terms of emission of harmful compounds in the exhausts emitted to the atmosphere." Combustion Engines 178, no. 3 (2019): 213–17. http://dx.doi.org/10.19206/ce-2019-337.

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Comparative analysis of combustion and hybrid propulsion unit in aviation application in terms of emission of harmful compounds in the exhausts emitted to the atmosphere. For the propulsion of the AOS 71 motor glider, two types of propulsion were planned as de-velopment versions. The first analysed propulsion is based on a combustion engine, but of the Wankel type (LCR 814 engine with the power of 55 kW). The second designed propulsion is an hybrid based on a LCR 407 combustion engine with a power of 28 kW, which is connected in series with an electric generator propelling the engine (Emrax 22

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2

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 (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

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3

Fureby, C. "Large eddy simulation modelling of combustion for propulsion applications." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 367, no. 1899 (2009): 2957–69. http://dx.doi.org/10.1098/rsta.2008.0271.

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Predictive modelling of turbulent combustion is important for the development of air-breathing engines, internal combustion engines, furnaces and for power generation. Significant advances in modelling non-reactive turbulent flows are now possible with the development of large eddy simulation (LES), in which the large energetic scales of the flow are resolved on the grid while modelling the effects of the small scales. Here, we discuss the use of combustion LES in predictive modelling of propulsion applications such as gas turbine, ramjet and scramjet engines. The LES models used are described

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4

Duan, Runze, Yifan Cao, Hongbin Duan, et al. "Effect of the inner-surface baffles on the tangential acoustic mode in the cylindrical combustor." Open Physics 18, no. 1 (2020): 1215–22. http://dx.doi.org/10.1515/phys-2020-0187.

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Abstract The combustion instability in a propulsion system is a ubiquitous problem. The radial baffles usually installed on the injector faceplate eliminate the combustion instability (acoustic pressure oscillation) in the propulsion system. In this article, the longitudinal baffles are installed on the inner surface of the combustor wall to control the combustion instabilities. The first-order and second-order tangential modes are induced in the experiments. The effects of the parameters of the baffle on the acoustic pressure oscillation in the cylindrical combustor are investigated. The effe

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5

Pandey, K. M., and Pinku Debnath. "Review on Recent Advances in Pulse Detonation Engines." Journal of Combustion 2016 (2016): 1–16. http://dx.doi.org/10.1155/2016/4193034.

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Pulse detonation engines (PDEs) are new exciting propulsion technologies for future propulsion applications. The operating cycles of PDE consist of fuel-air mixture, combustion, blowdown, and purging. The combustion process in pulse detonation engine is the most important phenomenon as it produces reliable and repeatable detonation waves. The detonation wave initiation in detonation tube in practical system is a combination of multistage combustion phenomena. Detonation combustion causes rapid burning of fuel-air mixture, which is a thousand times faster than deflagration mode of combustion pr

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6

Rao, M. Srinivasa. "Flow Analyses of Integrated Liquid Fuel RAMJET Propulsion System." Defence Science Journal 74, no. 2 (2024): 288–92. http://dx.doi.org/10.14429/dsj.74.18510.

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A CFD study is performed to check the seamless flow behaviour of the Liquid Fuel Ramjet Propulsion system which includes, air intakes, combustor and nozzle. Resolving both supersonic and subsonic flow scales in the same domain makes the simulations complex. Addition of combustion with stiff chemistry makes the simulations more difficult. CFD simulations are carried out using commercially available CFD software. Liquid fuel is injected as discrete phase and the flow turbulence is modelled using Realizable k-ε turbulence model. Jet-A + air combustion has been simulated using combined finite rate

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Stalker, R. J., and A. Paull. "Experiments on cruise propulsion with a hydrogen scramjet." Aeronautical Journal 102, no. 1011 (1998): 37–44. http://dx.doi.org/10.1017/s0001924000065726.

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AbstractMeasurements of drag have been made, in a shock tunnel, on a simple integrated vehicle-engine combination for hypersonic cruise with hydrogen scramjet propulsion. The test flow Mach number was 6·4, and the velocity was 2·45 kms-1. Zero drag, which is the necessary condition for cruise, was achieved as the equivalence ratio approached one. It was found that an analysis using established aerodynamic concepts was adequate for predicting drag in the case of no combustion. When combustion occurred results of direct connect experiments provided a qualitative guide to the measured levels of d

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8

Biró, Norbert, and Péter Kiss. "Emission Quantification for Sustainable Heavy-Duty Transportation." Sustainability 15, no. 9 (2023): 7483. http://dx.doi.org/10.3390/su15097483.

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Vehicles equipped with internal combustion engines (ICE) are major contributors to greenhouse gas (GHG) emissions and dependence on fossil fuels. Alternatives such as electric, hydrogen fuel cell and biofuel-based propulsions are being considered as a replacement for the well-established ICE vehicles to reduce GHG emissions and provide sustainable transportation. This paper will compare various heavy-duty vehicle (HDV) propulsion combinations using a well-to-wheel (WTW) analysis, separated into two parts: Well-to-Tank (WTT) and Tank-to-Wheel (TTW). The WTW analysis of ICE HDV is based on a Eur

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Kinoshita, Y., J. Kitajima, Y. Seki, and A. Tatara. "Experimental Studies on Methane-Fuel Laboratory Scale Ram Combustor." Journal of Engineering for Gas Turbines and Power 117, no. 3 (1995): 394–400. http://dx.doi.org/10.1115/1.2814108.

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The laboratory scale ram combustor test program has been investigating fundamental combustion characteristics of a ram combustor, which operates from Mach 2.5 to 5 for the super/hypersonic transport propulsion system. In our previous study, combustion efficiency had been found poor, less than 70 percent, due to a low inlet air temperature and a high velocity at Mach 3 condition. To improve the low combustion efficiency, a fuel zoning combustion concept was investigated by using a subscale combustor model first. Combustion efficiency more than 90 percent was achieved and the concept was found v

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10

Nikolayev, O. D., I. D. Bashliy, D. V. Klymenko, and N. V. Khoriak. "Interaction of the acoustic oscillations of the combustion products in the chamber of a propulsion system with structural vibrations." Technical mechanics 2025, no. 1 (2025): 28–35. https://doi.org/10.15407/itm2025.01.028.

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The most critical operating conditions of propulsion system chambers are often due to the development of dynamic processes characterized by excess values of operational parameters. Pressure surges and a sharp increase in the local temperature of the combustion products may result in a structural failure of the combustion chamber and a critical behavior of the propulsion system, to the point of combustion termination. An approach was developed to solving problems of propulsion system dynamics – assessment of the effect of the acoustic oscillations of the combustion products in the chamber with

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11

Bolivar, Nelson Enrique, and Ivaylo T. Vasilev. "Non-Combustion ⁴He Powered Propulsion." European Journal of Engineering and Technology Research 6, no. 2 (2021): 101–6. http://dx.doi.org/10.24018/ejers.2021.6.2.2283.

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One of the biggest hurdles nowadays rocket propulsion is the large use of fuel. The amount of fuel and the burning efficiency defines how long the rocket engine can work which intimately limits the range and the load capacity of the rockets and spaceships. This according to the Newton third law is unavoidable - in order to move forward you need to leave something behind. There have been several attempts in the past to create an engine which doesn't use fuel in the common sense, like the M drive, but so far all of them were unsuccessful. In this article we attempt to explore a novel principle,

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Bolivar, Nelson Enrique, and Ivaylo T. Vasilev. "Non-Combustion ?He Powered Propulsion." European Journal of Engineering and Technology Research 6, no. 2 (2021): 101–6. http://dx.doi.org/10.24018/ejeng.2021.6.2.2283.

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One of the biggest hurdles nowadays rocket propulsion is the large use of fuel. The amount of fuel and the burning efficiency defines how long the rocket engine can work which intimately limits the range and the load capacity of the rockets and spaceships. This according to the Newton third law is unavoidable - in order to move forward you need to leave something behind. There have been several attempts in the past to create an engine which doesn't use fuel in the common sense, like the M drive, but so far all of them were unsuccessful. In this article we attempt to explore a novel principle,

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13

Roy, G. D. "Propulsion Combustion: Fuels to Emissions." AIAA Journal 37, no. 7 (1999): 902–4. http://dx.doi.org/10.2514/2.7542.

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14

Yang, Vigor. "Combustion instabilities in propulsion systems." Journal of the Acoustical Society of America 107, no. 5 (2000): 2816. http://dx.doi.org/10.1121/1.429082.

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15

Fenlason, Jennifer. "Looking into Combustion." Aerospace Testing International 2024 (January 2024): 70–72. https://doi.org/10.12968/s1478-2774(25)50014-5.

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16

Bandyopadhyay, Atri, and Ankit Kumar Mishra. "Comparative Study on Hybrid Rocket Fuels for Space Launch Vehicles Moving in Higher Orbits." 4 1, no. 4 (2022): 13–19. http://dx.doi.org/10.46632/jame/1/4/3.

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The current research is focused on understanding the propulsive parameters of hybrid rocket motors. A comparative study is prepared from various research papers. The fuels paraffin wax, hydroxyl-terminated polybutadiene (HTPB) and polymethyl methacrylate (PMMA) with added additives (Al/Mg) were combined with two oxidizers, liquid oxygen (LOX), nitrous oxide (N2O). The propulsive parameters examined were the combustion efficiency, combustion or adiabatic flame temperature, characteristics velocity and regression rate. The propellant pair paraffin-N2O provided the highest performance for all par

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17

Lefebvre, A. H. "Fuel Effects on Gas Turbine Combustion—Ignition, Stability, and Combustion Efficiency." Journal of Engineering for Gas Turbines and Power 107, no. 1 (1985): 24–37. http://dx.doi.org/10.1115/1.3239693.

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An analytical study is made of the substantial body of experimental data acquired during recent Wright-Patterson Aero Propulsion Laboratory sponsored programs on the effects of fuel properties on the performance and reliability of several gas turbine combustors, including J79-17A, J79–17C (Smokeless), F101, TF41, TF39, J85, TF33, and F100. Quantitative relationships are derived between certain key aspects of combustion, notably combustion efficiency, lean blowout limits and lean light-off limits, and the relevant fuel properties, combustor design features, and combustor operating conditions. I

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18

DOGRA, Bharat Ankur, Mehakveer SINGH, Tejinder Kumar JINDAL, and Subhash CHANDER. "Technological advancements in Pulse Detonation Engine Technology in the recent past: A Characterized Report." INCAS BULLETIN 11, no. 4 (2019): 81–92. http://dx.doi.org/10.13111/2066-8201.2019.11.4.8.

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Pulse Detonation Engine (PDE), is an emerging and promising propulsive technology all over the world in the past few decades. A pulse detonation engine (PDE) is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. Theoretically, a PDE can be operate from subsonic to hypersonic flight speeds. Pulsed detonation engines offer many advantages over conventional air-breathing engines and are regarded as potential replacements for air-breathing and rocket propulsion systems, for platforms ranging from subsonic unmanned vehicles, long-range transportation, h

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19

Kim, Dongsuk, Majid Asli, and Klaus Höschler. "On the Potentials of the Integration of Pressure Gain Combustion with a Hybrid Electric Propulsion System." Aerospace 10, no. 8 (2023): 710. http://dx.doi.org/10.3390/aerospace10080710.

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As the issue of pollutant emissions from aviation propulsion escalates, research into alternative powertrains is gaining momentum. Two promising technologies are the Hybrid Electric Propulsion System (HEPS) and Pressure Gain Combustion (PGC). HEPS is expected to reduce pollutant emissions by decreasing fuel consumption, whereas PGC uses detonation in the combustor to increase the thermal efficiency of engines by elevating the total pressure during combustion. This study extensively explores the integration of these two emerging technologies, thoroughly assessing the advantages that arise from

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20

Smitha, D., M. R. S. Satyanarayana, and Sachin Srivastava. "Analysis of Combustion Characteristics of Can-Type and Annular-Type Combustion Chamber." Journal of Physics: Conference Series 2856, no. 1 (2024): 012004. http://dx.doi.org/10.1088/1742-6596/2856/1/012004.

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Abstract High performance is always desired for the propulsion system and the assortment of a better combustion type is also a vital part of the propulsion system. The analysis of different designs of combustion chambers and comparison of their combustion characteristics. In this paper, the assessment of Can-type and Annular-type combustion chambers and the design developed with SOLIDWORKS software and analysis done with ANSYS FLUENT. The systematic and translucent method approaches reduce the design complexity and time. The combustion with turbulence interface was examined to analyze with pre

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21

Rakhshani, B., T. Murmu, T. Leslie, D. Gopalasingam, and W. Zhang. "The Latest Development of Powering Aircraft (Aviation) with Hydrogen and Assessing the Technology Readiness." Journal of Physics: Conference Series 2968, no. 1 (2025): 012015. https://doi.org/10.1088/1742-6596/2968/1/012015.

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Abstract To meet the aviation emissions reduction targets, the performance characteristics in terms of power output, fuel consumption and propulsive efficiencies of hydrogen-powered aircraft have been reviewed and assessed. The design performance of an aircraft model (regional turboprop ATR 72-600) retrofitted with hydrogen-based propulsive systems was investigated, and comparisons are made against the conventional jet-fuelled propulsion. The hydrogen retrofit constituted two configurations; a fuel cell (FC) powered and direct combustion design. The power characteristics of the three propulsiv

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22

Candel, S., D. Durox, T. Schuller, N. Darabiha, L. Hakim, and T. Schmitt. "Advances in combustion and propulsion applications." European Journal of Mechanics - B/Fluids 40 (July 2013): 87–106. http://dx.doi.org/10.1016/j.euromechflu.2013.01.002.

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23

Bruno, Claudio, and Antonella Ingenito. "Some Key Issues in Hypersonic Propulsion." Energies 14, no. 12 (2021): 3690. http://dx.doi.org/10.3390/en14123690.

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This paper summarizes and discusses some critical aspects of flying hypersonically. The first is the L/D (lift over drag) ratio determining thrust and that in turn depends on the slenderness Küchemann’s τ parameter. This second parameter is found to depend on the relative importance of wave versus friction drag. Ultimately, all engineering drag is argued to depend on vorticity formed at the expense of the vehicle kinetic energy, thus requiring work by thrust. Different mixing strategies are discussed and shown to depend also on mechanisms forming vorticity when the regime is compressible. Supe

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24

Hosseini, Seyed, Evan Owens, John Krohn, and James Leylek. "Experimental Investigation into the Effects of Thermal Recuperation on the Combustion Characteristics of a Non-Premixed Meso-Scale Vortex Combustor." Energies 11, no. 12 (2018): 3390. http://dx.doi.org/10.3390/en11123390.

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In small-scale combustors, the ratio of area to the combustor volume increases and hence heat loss from the combustor’s wall is significantly enhanced and flame quenching occurs. To solve this problem, non-premixed vortex flow is employed to stabilize flames in a meso-scale combustion chamber to generate small-scale power or thrust for propulsion systems. In this experimental investigation, the effects of thermal recuperation on the characteristics of asymmetric non-premixed vortex combustion are studied. The exhaust gases temperature, emissions and the combustor wall temperature are measured

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Alsaidi, Saleh B., Jeongmoo Huh, and Mohamed Y. E. Selim. "Combustion of Date Stone and Jojoba Solid Waste in a Hybrid Rocket-like Combustion Chamber." Aerospace 11, no. 3 (2024): 181. http://dx.doi.org/10.3390/aerospace11030181.

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The performance of two solid biomass wastes, date stone and jojoba solid waste, was experimentally examined for their potential application in combustion and propulsion systems. The fuels were tested in a hybrid rocket-like combustion environment, and the test result was analyzed with combustion and propulsion parameters. The performance of both fuels was comparatively evaluated and compared with a conventional hydrocarbon fuel in a hybrid rocket, with paraffin wax serving as a baseline. A compression device was introduced to compress the solid biomass wastes into a circular-shaped fuel grain

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26

Lupchian, Mariana. "Influence of propulsion installation performance on travel efficiency." Technium: Romanian Journal of Applied Sciences and Technology 2, no. 7 (2020): 50–53. http://dx.doi.org/10.47577/technium.v2i7.1644.

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This paper presents an analysis of exploitation parameters for naval propulsion plant at different operating regimes. For naval propulsion plant with internal combustion engines, is considered as independent variables which give its operating regimes. Functional parameters of analysis of navigational regimes considered representative of the operation of the ship. Propulsion of the ship is provided by a fixed pitch propeller that allows modification propulsion performance by adjusting a single parameter function: speed propeller.

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27

Blagojevic, Ivan, Sasa Mitic, Dragan Stamenkovic, and Vladimir Popovic. "The future (and the present) of motor vehicle propulsion systems." Thermal Science 23, Suppl. 5 (2019): 1727–43. http://dx.doi.org/10.2298/tsci180307177b.

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Limited reserves of oil and the increasing environmental effect of its usage as a motor fuel represent global issue related to the constantly increasing number of motor vehicles. Therefore, the reduction of the fossil fuel consumed and the emission produced in internal combustion engines is the primary goal of the development of motor vehicle propulsion systems. In that sense, the present and the future of motor vehicles relies on hybrid drive systems, electric drive systems and drive systems which use hydrogen as a fuel (either by its combustion or by production of electric energy with the he

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Kinoshita, Y., T. Oda, and J. Kitajima. "Research on a Methane-Fueled Low NOx Combustor for a Mach 3 Supersonic Transporter Turbojet Engine." Journal of Engineering for Gas Turbines and Power 123, no. 4 (2000): 787–95. http://dx.doi.org/10.1115/1.1377009.

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Methane-fueled low NOx combustor research had been conducted under the Japanese supersonic/hypersonic propulsion research program. A unique form of premixture jet swirl combustor (PJSC) was proposed for the ultra low NOx combustor of a Mach 3 turbojet engine. Fuel-air mixing tests and fundamental combustion tests were conducted to obtain the design data and combustion characteristics in the first phase of the research. A single can-type combustor was fabricated and high-temperature and high-pressure combustion tests were carried out for the evaluation on NOx emission reduction capability of th

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Tran Tuan, Vu, Phuong Nguyen Huy, Surasak Phoemsapthawee, and Sangkla Kreuawan. "E-Engine for a Long-Tail Boat, an Application in ASEAN (Association of Southeast Asian Nations)-Design and Comparison with Internal Combustion Engine." World Electric Vehicle Journal 12, no. 1 (2021): 36. http://dx.doi.org/10.3390/wevj12010036.

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An Electric propulsion (E-propulsion) system for ASEAN (Association of Southeast Asian Nations) long-tail boat is proposed in this article. It offers several advantages over a traditional internal combustion engine propulsion system. Besides low noise and zero-emission, characteristics of electric engine (E-engine) allow regenerative braking and starting the propeller in the water. A design of E-engine has been achieved through finite element analyses and lump-parameter thermal simulations. It shows better performances than Honda GX270 internal combustion engine in terms of volume, weight, tor

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Nasir, Sheharyar, Shumail Sahibzada, and Farrukh Sher Malik. "Physics-Informed Neural Networks for Predicting Combustion Dynamics in Rocket Engine Chambers." International Journal of Innovative Research in Computer Science and Technology 13, no. 4 (2025): 41–44. https://doi.org/10.55524/ijircst.2025.13.4.4.

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Accurately predicting combustion dynamics within rocket engine chambers is essential for ensuring propulsion system stability, efficiency, and safety. Traditional high-fidelity Computational Fluid Dynamics (CFD) methods offer detailed insights but are computationally expensive and often impractical for real-time applications. This study introduces Physics-Informed Neural Networks (PINNs) as a novel, efficient alternative for modeling combustion dynamics in rocket propulsion systems. PINNs integrate the governing partial differential equations (PDEs)—including mass, momentum, energy, and specie

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Chang, C. T., K. Tacina, C. Lee, et al. "NASA Glenn Combustion Research for Aeronautical Propulsion." Journal of Aerospace Engineering 26, no. 2 (2013): 251–59. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000289.

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32

Vincent-Randonnier, Axel. "Propulsion aéronautique : études expérimentales de la combustion." Comptes Rendus. Mécanique 352, S1 (2024): 55–59. http://dx.doi.org/10.5802/crmeca.263.

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33

Nikolayev, O. D., I. D. Bashliy, and V. O. Sukachevskyi. "Features of the development of acoustic oscillations in the combustion product flow in power plant chambers when using propellant components derived from lunar regolith." Technical mechanics 2025, no. 2 (2025): 3–16. https://doi.org/10.15407/itm2025.02.003.

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Working processes in combustion chambers of various power plants (thermal power and marine plants, aircraft and rocket engines) are traditionally improved along a number of lines. Ensuring the thermoacoustic stability of power plants in their operating modes is one of the most important conditions for the efficient functioning of the combustion chamber. In situ Lunar Resource Utilization (ISLRU) is a technology that allows one to significantly accelerate space exploration. The expected increase in lunar exploration activity in the near future rises interest in in situ lunar resources (ISRU), e

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Serrano, José Ramón, Ricardo Novella, and Pedro Piqueras. "Why the Development of Internal Combustion Engines Is Still Necessary to Fight against Global Climate Change from the Perspective of Transportation." Applied Sciences 9, no. 21 (2019): 4597. http://dx.doi.org/10.3390/app9214597.

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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 (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

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Prisacariu, Vasile, Constantin Rotaru, Ionică Cîrciu, and Mihai Niculescu. "Numerical simulation and performances evaluation of the pulse detonation engine." MATEC Web of Conferences 234 (2018): 01001. http://dx.doi.org/10.1051/matecconf/201823401001.

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A pulse detonation engine (PDE) is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. The engine is pulsed because the mixture must be renewed in the combustor between each detonation wave. Theoretically, a PDE can operate from subsonic up to hypersonic flight speed. Pulsed detonation engines offer many advantages over conventional propulsion systems and are regarded as potential replacements for air breathing and rocket propulsion systems, for platforms ranging from subsonic unmanned vehicles, long range transports, high-speed vehicles, space laun

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37

McIntosh, A. C. "Combustion, fire, and explosion in nature - some biomimetic possibilities." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 221, no. 10 (2007): 1157–63. http://dx.doi.org/10.1243/09544062jmes541.

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In the current paper, three areas involving fire and/or explosions in nature are explored: (a) the knobcone pine, (b) the scotch broom seed, and (c) the combustion chamber of the bombardier beetle. Each is described and some possible biomimetic applications of each of these are discussed. The knobcone pine has a high temperature controlled unique gas emission insulating system. The Scottish broom has a mechanical, humidity controlled propulsion device for dispersing its seed, and the bombardier beetle has a mass ejection system which enables the propulsion of a liquid/gas mixture to a throw ra

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Yoon, Wonjae, Vikas Khandu Bhosale, and Hosung Yoon. "Performance Evaluation of Ammonium Dinitramide-based Monopropellant in a 1N Thruster." Aerospace 11, no. 2 (2024): 110. http://dx.doi.org/10.3390/aerospace11020110.

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The development of propulsion systems based on green propellants, as an alternative to hydrazines, has been gaining interest within the space community. The study of Ammonium Dinitramide (ADN)-based liquid monopropellant, which is low-toxic and can deliver high performance, is the focal point of interest for Space Solutions Co., Ltd., Daejeon, Republic of Korea. A 1N ADN-based propulsion system was designed to evaluate the performance of the propellant. By combining a thermal and catalytic bed in a reactor, the performance of the propellant was examined in a designed thruster (chamber pressure

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Pielecha, Ireneusz, Wojciech Cieslik, and Filip Szwajca. "Energy Flow and Electric Drive Mode Efficiency Evaluation of Different Generations of Hybrid Vehicles under Diversified Urban Traffic Conditions." Energies 16, no. 2 (2023): 794. http://dx.doi.org/10.3390/en16020794.

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Hybrid propulsion dedicated to light duty vehicles is seen as an evolutionary change from internal combustion engine (ICE) to electric propulsion. Widespread direct replacement of convection ICEs in the current energy system is impossible because ICEs are vehicles’ main source of mechanical energy. The hybrid powertrain uses the advantages of electric propulsion with the ability to charge the traction battery or have the internal combustion engine assist the system. The article compares different types of hybrid drives (with a small share of plug-in hybrid propulsion) under typical urban drivi

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Shen, Xuankun, and Aaron W. Costall. "Enhancing the Efficiency of Rotary Thermal Propulsion Systems." Energies 17, no. 9 (2024): 2112. http://dx.doi.org/10.3390/en17092112.

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Transport electrification is essential for reducing CO2 emissions, and technologies such as hybrid and range-extended electric vehicles will play a crucial transitional role. Such vehicles employ an internal combustion engine for on-board chemical energy conversion. The Wankel rotary engine should be an excellent candidate for this purpose, offering a high power-to-weight ratio, simplicity, compactness, perfect balance, and low cost. Until recently, however, it has not been in production in the automotive market, due, in part, to relatively low combustion efficiency and high fuel consumption a

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Cojocea, Andrei Vlad, Ionuț Porumbel, Mihnea Gall, and Tudor Cuciuc. "Experimental Thrust and Specific Impulse Analysis of Pulsed Detonation Combustor." Applied Sciences 14, no. 14 (2024): 5999. http://dx.doi.org/10.3390/app14145999.

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Detonation combustion represents a significant advancement in efficiency over traditional deflagration methods. This paper presents a Pulsed Detonation Combustor (PDC) model that is designed with an aerodynamic mixing chamber featuring Hartmann–Sprenger resonators and crossflow injection. This design enhances operational cycle frequency and enables sustained detonation over short distances (below 200 mm). The PDC’s performance was evaluated through a comprehensive full-factorial experimental campaign, incorporating four factors with four discrete levels each. Testing was conducted using both h

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Maimon, Aurel-Dan. "On the electric propulsion of rive ships." Analele Universităţii "Dunărea de Jos" din Galaţi. Fascicula XI, Construcţii navale/ Annals of "Dunărea de Jos" of Galati, Fascicle XI, Shipbuilding 47 (December 4, 2024): 143–49. https://doi.org/10.35219/annugalshipbuilding/2024.47.17.

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Electric propulsion for river ships is an exciting and promising development in the maritime industry. This technology involves using electric motors powered by batteries instead of traditional internal combustion engines. Advances in battery technology, such as lithium ion batteries, have made electric propulsion more viable and cost-effective. It is generally more efficient than internal combustion engines, leading to a better fuel economy and lower operational costs and it produces significantly less pollution compared to traditional engines, which burn heavy oil. This helps reduce greenhou

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Cameretti, Maria, Andrea Del Pizzo, Luigi Di Noia, Michele Ferrara, and Ciro Pascarella. "Modeling and Investigation of a Turboprop Hybrid Electric Propulsion System." Aerospace 5, no. 4 (2018): 123. http://dx.doi.org/10.3390/aerospace5040123.

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Hybrid electric propulsion in the aviation field is becoming an effective alternative propulsion technology with potential advantages, including fuel savings, lower pollution, and reduced noise emission. On the one hand, the aeroengine manufacturers are working to improve fuel consumption and reduce pollutant emissions with new combustion systems; on the other hand, much attention is given to reducing the weight of the batteries increasing the energy density. Hybrid electric propulsion systems (HEPS) can take advantage of the synergy between two technologies by utilizing both internal combusti

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Kost, Gabriel, and Andrzej Nierychlok. "Virtual Driver of Hybrid Wheeled Vehicle." Solid State Phenomena 180 (November 2011): 39–45. http://dx.doi.org/10.4028/www.scientific.net/ssp.180.39.

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This paper presents the application of wheeled vehicle based on a hybrid propulsion system. Describes control system structure and communication between different units of propulsion, intermediary devices and the fundamental issues of building such a network. Virtual propulsion of a wheeled vehicle hybrid drive designed for parallel connection structure of the drive units. This enabled the propulsion work more efficiently through the synergy of energy units – ICE and electric motor, and allowed ICE unit turn off in built-up areas. In the presented research results can be seen as a great contri

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Jang, Junseop. "A Study on the Submarine Air Independent Propulsion System: Focused on Submarines Currently in Operation." Journal of the Korea Institute of Military Science and Technology 24, no. 4 (2021): 418–25. http://dx.doi.org/10.9766/kimst.2021.24.4.418.

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Submarines are weapons systems that have been proven to be useful in battle since World War I and have continued to improve the efficiency of propulsion systems in order to be used efficiently on the battlefield. In particular, countries that unable to utilize nuclear propulsion systems make efforts to increase the efficiency of Air Independent Propulsion systems, and typical examples are fuel cells, Stirling engines and MESMA. It is also expected that the development of new propulsion systems such as hydrogen-reformer fuel cells, metal-air fuel cell and direct combustion propulsion systems wi

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Medhat, Moataz, Adel Khalil, and Mohamed A. Yehia. "A Numerical Study of Decarbonizing Marine Gas Turbine Emissions Through Ammonia/Hydrogen Fuel Blends." Journal of Physics: Conference Series 2304, no. 1 (2022): 012008. http://dx.doi.org/10.1088/1742-6596/2304/1/012008.

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Abstract The employment of gas turbine in combination with diesel engines and steam generators is a well-known power generation technique in modern marines and ship propulsion. Previously, it rendered its foundations in marine industry through higher power weight ratios and lower NOx emissions if compared to pure diesel engine driven marines. As climate change concerns are becoming more serious, the decarbonization of marine combustion products is becoming of environmental concern. In the present study a modified design of the burner and combustor was suggested to allow for the longer residenc

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Dias, David M., Pedro R. Resende, and Alexandre M. Afonso. "A Review on Micro-Combustion Flame Dynamics and Micro-Propulsion Systems." Energies 17, no. 6 (2024): 1327. http://dx.doi.org/10.3390/en17061327.

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This work presents a state-of-the-art review of micro-combustion flame dynamics and micro propulsion systems. In the initial section, we focus in on the different challenges of micro-combustion, investigating the typical length and time scales involved in micro-combustion and some critical phenomena such as flammability limits and the quenching diameter.We present an extensive collection of studies on the principal types of micro-flame dynamics, including flashback, blow-off, steady versus non-steady flames, mild combustion, stable flames, flames with repetitive extinction, and ignition and pu

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Ramesh, Davood, Hasan Karimi M., and Massoud Shahheidari. "Cycle optimization of the staged combustion rocket engines." Aircraft Engineering and Aerospace Technology 89, no. 2 (2017): 304–13. http://dx.doi.org/10.1108/aeat-12-2013-0229.

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Purpose The purpose of this paper is to introduce new and modified “staged combustion” cycles in the form of engineering algorithm as a possible propulsion contender for future aerospace vehicle to achieve the highest possible “total impulse” to “mass” of propulsion system. Design/methodology/approach In this regard, the mathematical cycle model is formed to calculate the engine’s parameters. In addition, flow conditions (pressure, temperature, flow rate, etc). in the chamber, nozzle and turbopump are assessed based on the results of turbo machinery power balance and initial data such as thrus

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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 (2021): e2102244118. http://dx.doi.org/10.1073/pnas.2102244118.

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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. Deto

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Karpuk, Stanislav, Yannik Freund, and Richard Hanke-Rauschenbach. "Potential of Hydrogen Fuel Cell Aircraft for Commercial Applications with Advanced Airframe and Propulsion Technologies." Aerospace 12, no. 1 (2025): 35. https://doi.org/10.3390/aerospace12010035.

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The present work demonstrates a comparative study of hydrogen fuel cells and combustion aircraft to investigate the potential of fuel cells as a visionary propulsion system for radically more sustainable medium- to long-range commercial aircraft. The study, which considered future airframe and propulsion technologies under the Se2A project, was conducted to quantify potential emissions and costs associated with such aircraft and to determine the benefits and drawbacks of each energy system option for different market segments. Future technologies considered in the present work include laminar

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