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Relevant bibliographies by topics / Ramjet engines

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Academic literature on the topic 'Ramjet engines'

Author: Grafiati

Published: 4 June 2021

Last updated: 31 July 2024

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Journal articles on the topic "Ramjet engines"

1

Liu, K., and T. Cui. "Combustor-inlet interactions in a low-order dynamic model of ramjet engines." Aeronautical Journal 124, no. 1282 (July 29, 2020): 2001–18. http://dx.doi.org/10.1017/aer.2020.64.

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ABSTRACTThe coexistence of multiple stable states is indicative of self-organising processes occurring in the course of the combustor-inlet interactions in a ramjet engine and give rise to the appearance of various nonlinear phenomena. This paper provides a dynamic model that can describe the multiple stable states and the corresponding nonlinear effects to further investigate the dynamic interactions between combustor and inlet in a ramjet engine. Our study shows the whole engine can display distinct dynamic behaviours ranging from irreversibility to hysteresis and to various mode transitions, depending on different physical parameters. With the model, we also illustrate the role of the instability of the normal shock wave in impacting the whole engine’s nonlinear dynamics. Additionally, we extend the previous studies of the classification of combustor-inlet interactions from a static framework to a dynamic framework, which helps to clarify the transient processes of the nonlinear interactions. This work offers a quantitative illustration of the combustor-inlet interactions in a ramjet engine by revealing its nonlinear dynamics and associated characteristics, therefore advancing our understanding of the nonlinear phenomena that exhibit in ramjet engines.

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2

FUNAKI, Katsumi. "Characteristics of ramjet engines." Journal of the Japan Society for Aeronautical and Space Sciences 35, no. 402 (1987): 329–38. http://dx.doi.org/10.2322/jjsass1969.35.329.

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3

Zhao, Dongsheng, Zhijun Wei, Duanyang He, Li Dalin, and Huang Chujiu. "Effect of different particle sizes on combustion characteristics of DCR engines." Journal of Physics: Conference Series 2746, no. 1 (May 1, 2024): 012012. http://dx.doi.org/10.1088/1742-6596/2746/1/012012.

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Abstract The ramjet engine has undergone rapid development in recent decades, and the dual combustion chamber ramjet (DCR) engine was proposed in the last century. Boron, with its high volumetric and gravimetric heating values, is one of the most attractive fuel additives for ramjet engines. However, due to the problem of low combustion efficiency, boron is difficult to achieve high efficiency combustion in practical applications. In order to investigate the combustion characteristics of boron-containing gas solid phase components in DCR engines, the Realizable k-ε model, finite rate/vortex dissipation model and boron particle King model ignition combustion calculation program were written. A three-dimensional full-scale two-phase flow numerical simulation was carried out in the combustion chamber of the DCR engine to calculate the effects of different particle sizes on the combustion characteristics. Through the analysis of the simulation results, the particle size affects the ignition time of boron particles and is positively correlated with the combustion efficiency, but with a non-linear growth. A smaller particle size can promote the ignition of boron particles, improve the solid phase combustion efficiency and achieve efficient combustion.

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4

Кислов, Олег Владимирович, and Михаил Анатольевич Шевченко. "ОСОБЕННОСТИ РАСЧЕТА И РЕГУЛИРОВАНИЯ ДВУХКОНТУРНОГО ТУРБОРЕАКТИВНОГО ДВИГАТЕЛЯ С ФОРСАЖНОЙ КАМЕРОЙ СГОРАНИЯ В НАРУЖНОМ КОНТУРЕ НА ПРЯМОТОЧНЫХ РЕЖИМАХ РАБОТЫ." Aerospace technic and technology, no. 6 (November 27, 2020): 15–23. http://dx.doi.org/10.32620/aktt.2020.6.02.

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A promising direction in aviation is the creation of anaircraft for supersonic cruise speeds (Mach 3...4). It is known that ramjet engines are more preferable for Mach numbers larger 3. However, they do not have starting thrust and uneconomical at subsonic flight speeds. At the same time, at subsonic flight speeds, turbofan engines are the most expedient. The combination of the positive properties of turbofan engines at subsonic speeds and a ramjet engines at supersonic speeds is possible by using duct-burning turbofan engine, which can operate at the ramjet mode with the blocked gas turbine duct at supersonic flight conditions. At this mode, duct-burning turbofan engine turns into ramjet engine, which, however, has special features due to the presence of fan in front of the combustion chamber, which operates in turbine mode or in zero power mode and also because of the outlet jet, which has annular shape, flows out from the duct causes the appearance of bottom drag. The presence of bottom drag requires both the development of a mathematical model for its calculation and taking into account its influence on the choice of the control law for the nozzle outlet area. The article presents a mathematical model of the working process of duct-burning turbofan engine at ramjet mode, taking into account the presence of fan in the flow path and bottom drug. Using the developed mathematical model, the regularities of changes in the internal and effective thrust, as well as the specific fuel consumption, depending on the relative fuel consumption and the critical section of the nozzle at a given altitude and flight speed are established. The critical section of the nozzle is the main regulating factor, and the relative fuel consumption is related to the main regulating factor - the fuel consumption. These patterns are useful for choosing a control program.There is such a combination of regulating factors whichprovides two extremes in the regularities of trust and specific fuel consumption changes: the mode of minimum specific fuel consumption and the mode of maximum thrust. In addition, the influence of gas underexpansion in the nozzle on the thrust-economic parameters of the engine and the required area of the nozzle outlet section were estimated. The obtained regularities are advisable to use when engine control program is chosen.

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Hu, Lichen, Feiyu Long, Borui Xie, and Xuanzhou Zhuang. "Four variants of turbofan, turbojet, turboprop and ramjet engines and their future prospects." Applied and Computational Engineering 11, no. 1 (September 25, 2023): 137–42. http://dx.doi.org/10.54254/2755-2721/11/20230222.

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A jet engine is a sophisticated machine that has revolutionized the aviation industry. It is a type of internal combustion engine that uses air as its oxidizer and fuel to produce thrust. The third law of motion, which states that there is an equivalent and opposite response to every action, governs how the engine functions. Compressed air is combined with fuel, ignited in the combustion chamber, and then expelled out of the jet engine at a high rate of speed to create propulsion. The development of jet engines has been a long and arduous process, with many different designs and configurations over the years. Early jet engines were inefficient, noisy, and prone to failure. However, technological advances have created more efficient and reliable engines in various applications, from commercial aviation to military aircraft and even spacecraft. The efficiency and reliability of jet engines have transformed air travel, enabling faster and more efficient travel over long distances. This has increased global connectivity, economic growth, and cultural exchange. However, jet engines also have environmental impacts, such as noise pollution and greenhouse gas emissions, which have led to the development of more environmentally friendly engines.

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Fureby, Christer, Guillaume Sahut, Alessandro Ercole, and Thommie Nilsson. "Large Eddy Simulation of Combustion for High-Speed Airbreathing Engines." Aerospace 9, no. 12 (December 1, 2022): 785. http://dx.doi.org/10.3390/aerospace9120785.

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Large Eddy Simulation (LES) has rapidly developed into a powerful computational methodology for fluid dynamic studies, between Reynolds-Averaged Navier–Stokes (RANS) and Direct Numerical Simulation (DNS) in both accuracy and cost. High-speed combustion applications, such as ramjets, scramjets, dual-mode ramjets, and rotating detonation engines, are promising propulsion systems, but also challenging to analyze and develop. In this paper, the building blocks needed to perform LES of high-speed combustion are reviewed. Modelling of the unresolved, subgrid terms in the filtered LES equations is highlighted. The main families of combustion models are presented, focusing on finite-rate chemistry models. The density-based finite volume method and the reaction mechanisms commonly employed in LES of high-speed H2-air combustion are briefly reviewed. Three high-speed combustor applications are presented: an experiment of supersonic flame stabilization behind a bluff body, a direct connect facility experiment as a transition case from ramjet to scramjet operation mode, and the STRATOFLY MR3 Small-Scale Flight Experiment. Several combinations of turbulence and combustion models are compared. Comparisons with experiments are also provided when available. Overall, the results show good agreement with experimental data (e.g., shock train, mixing, wall heat flux, transition from ramjet to scramjet operation mode).

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Avrashkov, V. N., E. S. Metelkina, and D. V. Meshcheryakov. "Investigation of High-Speed Ramjet Engines." Combustion, Explosion, and Shock Waves 46, no. 4 (July 2010): 400–407. http://dx.doi.org/10.1007/s10573-010-0054-0.

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Buchanan, C. R., A. J. T. Gemmill, and P. G. Martin. "Interaction of missile propulsion and aerodynamics." Aeronautical Journal 104, no. 1036 (June 2000): 271–77. http://dx.doi.org/10.1017/s0001924000091594.

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Abstract Some aspects of propulsion integration issues for ramjet powered missiles are outlined in this paper. The benefits of ramjet propulsion in the Mach 2-4 range over other types of airbreathing propulsion and rocket propulsion are well known. Compared with solid rocket motors, ramjet engines offer a much higher specific impulse and the capability of thrust management, enabling longer stand-off ranges and more flexible operation. An overview of the ramjet engine cycle is given, highlighting engine/intake matching issues. This is followed by a performance comparison between a generic ramjet and a solid rocket powered missile (the air-to-air configuration is examined by way of example in this paper). As well as overall performance, intake integration and missile steering issues are considered. A description of a wind tunnel test model, intake design and tunnel testing is given. The effects of design Mach number and side-wall removal have been investigated for twin ventral rectangular intake configurations. These tests were aimed at optimising performance at different flight conditions and improving tolerance to yawed flight. The impact of the alternative intake designs on missile performance is discussed.

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Timoshenko, V. I., V. P. Halynskyi, and Yu V. Knyshenko. "Theoretical studies on rocket/space hardware aerogas dynamics." Technical mechanics 2021, no. 2 (June 29, 2021): 46–59. http://dx.doi.org/10.15407/itm2021.02.046.

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This paper presents the results of theoretical studies on rocket/space hardware aerogas dynamics obtained from 2016 to 2020 at the Department of Aerogas Dynamics and Technical Systems Dynamics of the Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine along the following lines: rocket aerodynamics, mathematical simulation of the aerogas thermodynamics of a supersonic ramjet vehicle, jet flows, and the hydraulic gas dynamics of low-thrust control jet engines. As to rocket aerodynamics, computational methods and programs (CMPs) were developed to calculate supersonic flow past finned rockets. The chief advantage of the CMPs developed is computational promptness and ease of adding wings and control and stabilization elements to rocket configurations. A mathematical simulation of the aerogas thermodynamics of a supersonic ramjet vehicle yielded new results, which made it possible to develop a prompt technique for a comprehensive calculation of ramjet duct flows and generalize it to 3D flow past a ramjet vehicle. Based on marching methods, CMPs were developed to simulate ramjet duct flows with account for flow past the airframe upstream of the air inlet, the effect of the combustion product jet on the airframe tail part, and its interaction with a disturbed incident flow. The CMPs developed were recommended for use at the preliminary stage of ramjet component shape selection. For jet flows, CMPs were developed for the marching calculation of turbulent jets of rocket engine combustion products with water injection into the jet body. This made it possible to elucidate the basic mechanisms of the effect of water injection, jet–air mixing, and high-temperature rocket engine jet afterburning in atmospheric oxygen on the flow pattern and the thermogas dynamic and thermalphysic jet parameters. CMPs were developed to simulate the operation of liquid-propellant low-thrust engine systems. They were used in supporting the development and ground firing tryout of Yuzhnoye State Design Office’s radically new system of control jet engines fed from the sustainer engine pipelines of the Cyclone-4M launch vehicle upper stage. The computed results made it possible to increase the informativity of firing test data in flight simulation. The CMPs developed were transferred to Yuzhnoye State Design Office for use in design calculations.

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Bogomolov, Iaroslav, and Vladimir Malinin. "DETERMINATION OF BREAKING CHARACTERISTICS IN THE PRE-COMBUSTION CHAMBER OF A COMBINED RAMJET ENGINE ON A POWDERED ALUMINUM FUEL TAKING INTO ACCOUNT AIR BRAKING IN AIR INTAKE DEVICE." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 65 (2021): 105–11. http://dx.doi.org/10.15593/2224-9982/2021.65.11.

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The paper considers a combined ramjet engine powered by powdered aluminum fuel . The prototype was a combined solid-fuel ramjet engine. The advantages of the engine under consideration are given. An example of the combustion of finely dispersed aluminum powder is considered, from which it follows that the initial temperature of the aluminum powder will affect the stall characteristics in the pre-chamber. The following characteristics of the PAF ramjet were determined: the temperature of air stagnation in the air intake device, the temperature of the mixture of aluminum powder and the stalled air flow, the excess air ratio, and the stall characteristics in the pre-chamber taking into account the air stagnation temperatures. All parameters are de-termined for engine operating altitudes equal to 0.5, 10 and 18 km. A comparison is made of the limiting flame propagation ve-locities under standard conditions and with an incident air flow. Based on the obtained values of the characteristics, the interval of values of the coefficient of air sampling from the inlet to the pre-chamber of the ramjet engine on the PAF was determined, corresponding to the maximum possible areas of the engine operating parameters. Using the obtained values of characteristics, the combustion process of powdered aluminum in the pre-chamber of a ramjet engine takes place without flame blowout, which excludes unstable operation of the propulsion system as a whole. The use of powdered aluminum makes it possible to regulate the thrust in a wide range of values, and a high initial temperature of the air entering the pre-chamber for repeated switching on and off of the engine. Based on the available data, the type of engines under consideration is suitable for combat missiles of various classes, but the most suitable for aircraft-based missiles.

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Dissertations / Theses on the topic "Ramjet engines"

1

Goodman, J. S. "Thermal analysis of ramjet engines." Thesis, University of Oxford, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.445768.

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2

Del, Rio Francesco. "Distortion mechanism in supersonic combustion ramjet engines." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2018.

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Il mio lavoro di tesi è stato incentrato sulla progettazione e la realizzazione di un prototipo di isolator (componente necessaria per il funzionamento dei motori scramjet, utilizzati per velivoli aerospaziali ipersonici) in grado di generare tramite un opportuno dispositivo il meccanismo fluidodinamico che in letteratura viene definito "distortion mechanism". Tramite la tecnica fotografica denominata Schlieren, la quale sfrutta i gradienti di densità all’interno del fluido in esame, ho fotografato le onde di shock generate dal meccanismo suddetto, rendendo così possibile la comprensione del comportamento di queste onde e delle loro interazioni con il boundary layer, con le pareti, ma soprattutto dell’influenza che esse hanno sulle prestazioni di un eventuale propulsore. Da qui è partita una analisi sulle interazioni shock-shock e shock-boundary layer: quest’ultimo fenomeno è di grande interesse in quanto si è notato che non solo viene attivato un meccanismo di distorsione dell’onda stessa, ma che addirittura si manifesta la separazione dello strato limite, generando complessi fenomeni fluidodinamici e termodinamici i quali decrementano l’efficienza non solo dell’isolator bensì del motore stesso.È stato infine previsto come le onde di shock che si propagavano nell’isolator avrebbero potuto affliggere il mixing e la combustione nell’ultimo stage del prototipo, evidenziando le conseguenze che avrebbero generato sull’efficienza generale del ciclo termodinamico. Per concludere il mio lavoro di tesi ho sviluppato alcuni tools in ambiente Matlab utili per poter calcolare le proprietà termodinamiche di un fluido che entra in un inlet di uno scramjet. Per motivi di complessità del problema e per la non assoluta certezza dei fenomeni fluidodinamici e termodinamici che realmente accadono in questi motori (in 3-D), le equazioni utilizzate all’interno del codice sono utili per un’analisi di un fluido quasi monodimensionale.

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3

Reuter, Dierk Martin. "Investigation of combustion instability in ramjet combustors." Diss., Georgia Institute of Technology, 1988. http://hdl.handle.net/1853/12271.

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Davis, James Arthur. "Acoustic-vortical-combustion interaction in a solid fuel ramjet simulator." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/12947.

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5

Hall, Philip D. "Design of a coaxial split flow pulse detonation engine." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2006. http://library.nps.navy.mil/uhtbin/hyperion/06Jun%5FHall.pdf.

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Thesis (M.S. in Mechanical Engineering)--Naval Postgraduate School, June 2006.
Thesis Advisor(s): Jose O. Sinibaldi, Christopher M. Brophy. "June 2006." Includes bibliographical references (p. 41-42). Also available in print.

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De, Groot Wim A. (Wim Adrianus). "Laser Doppler diagnostics of the flow behind a backward facing step." Diss., Georgia Institute of Technology, 1985. http://hdl.handle.net/1853/15801.

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Najafiyazdi, Alireza. "Theoretical and numerical analysis of supersonic inlet starting by mass spillage." Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=111524.

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Supersonic inlet starting by mass spillage is studied theoretically and numerically in the present thesis. A quasi-one-dimensional, quasi-steady theory is developed for the analysis of flow inside a perforated inlet. The theory results in closed-form relations applicable to flow starting by the mass spillage technique in supersonic and hypersonic inlets.
The theory involves three parameters to incorporate the multi-dimensional nature of mass spillage through a wall perforation. Mass spillage through an individual slot is studied to determine these parameters; analytical expressions for these parameters are derived for both subsonic and supersonic flow conditions. In the case of mass spillage from supersonic flows, the relations are exact. However, due to the complexity of flow field, the theory is an approximation for subsonic flows. Therefore, a correction factor is introduced which is determined from an empirical relation obtained from numerical simulations.
A methodology is also proposed to determine perforation size and distribution to achieve flow starting for a given inlet at a desired free-stream Mach number. The problem of shock stability inside a perforated inlet designed with the proposed method is also discussed.
The method is demonstrated for some test cases. Time-realistic CFD simulations and experimental results in the literature confirm the accuracy of the theory and the reliability of the proposed design methodology.

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8

Sarisin, Mustafa Nevzat. "Design Of A Connected Pipe Test Facility For Ramjet Applications." Master's thesis, METU, 2005. http://etd.lib.metu.edu.tr/upload/12606078/index.pdf.

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ABSTRACT DESIGN OF A CONNECTED PIPE TEST FACILITY FOR RAMJET APPLICATIONS SARISIN, Mustafa Nevzat M.S., Department of Mechanical Engineering Supervisor: Asst. Prof. Dr. Abdullah ULAS Co-Supervisor: Prof. Dr. Kahraman ALBAYRAK April 2005, 164 pages Development of the combustor of a ramjet can be achieved by connected pipe testing. Connected pipe testing is selected for combustor testing because pressure, temperature, Mach number, air mass flow rate can be simulated by this type of testing. Real time trajectory conditions and transition from rocket motor (booster) to ramjet operation can also be tested. The biggest advantage of connected pipe testing is the low operation cost and simplicity. Air mass flow rate requirement is less than the others which requires less air storage space and some components like supersonic nozzle and ejector system is not necessary. In this thesis, design of a connected pipe test facility is implemented. Three main systems are analyzed
air storage system, air heater system and test stand. Design of air storage system includes the design of pressure vessel and pressure &
flow regulation system. Pressure and flow regulation system is needed to obtain the actual flow properties that the combustor is exposed to during missile flight. Alternatives for pressure and air mass flow rate regulation are considered in this study. Air storage system designed in this thesis is 27.8 m3 at 50 bar which allows a test duration of 200 seconds at an average mass flow rate of 3 kg/s. Air heater system is utilized to heat the air to simulate the aerodynamic heating of the inlet. Several different combustion chamber configurations with different flame holding mechanisms are studied. The most efficient configuration is selected for this study. Combustion analysis of the air heater is performed by FLUENT CFD Code. Combustion process and air heater designs are validated using experimental data. Designed air heater system is capable of supplying air at a temperature range of 400-1000 K and mass flow rate range of 1.5-8 kg/s at Mach numbers between 0.1-0.5 and pressure between 2-8 bar. Finally the design of the test stand and ramjet combustor analysis are completed. 3D CAD models of the test stand are generated. Ramjet combustor that will be tested in the test setup is modeled and combustion analysis is performed by FLUENT CFD Code. The ramjet engine cruise altitude is 16 km and cruise Mach number is 3.5. Key-words: Air Breathing Engines, Ramjet, Connected Pipe, Direct Connect, Vitiator.

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9

Piper, Ross H. "Design and testing of a combustor for a turbo-ramjet for UAV and missile applications." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Mar%5FPiper.pdf.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, March 2003.
Thesis advisor(s): Garth V. Hobson, Raymond P. Shreeve. Includes bibliographical references (p. 81-82). Also available online.

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Gabruk, Robert S. "The characterization of the flowfield of a dump combustor." Thesis, This resource online, 1990. http://scholar.lib.vt.edu/theses/available/etd-05092009-040628/.

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Books on the topic "Ramjet engines"

1

Northam, G. Burton. Supersonic combustion ramjet research at Langley. New York: AIAA, 1986.

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Kremer, Frans G. J. Thermodynamische Stromungsbeschreibung eines Staustrahltriebwerks mit Unterschallverbrennung zur Bestimmung der Triebwerkskrafte und Momente. Koln: Deutsche Forschungsanstalt fur Luft- und Raumfahrt, 1991.

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Snyder, Christopher. A parametric study of a gas-generator airturbo ramjet (ATR). [Washington, DC]: National Aeronautics and Space Administration, 1986.

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Snyder, Christopher. The design and performance estimates for the propulsion module for the booster of a TSTO vehicle. [Washington, DC]: National Aeronautics and Space Administration, 1991.

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Artëmov, Oleg Aleksandrovič. Prjamotočnye vozdušno-reaktivnye dvigateli: (rasčet charakteristik) : monografija. Moskva: Kompanija Sputnik+, 2006.

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Seokkwan, Yoon, and United States. National Aeronautics and Space Administration., eds. Numerical study of chemically reacting flows using an LU scheme. [Washington, DC: National Aeronautics and Space Administration, 1988.

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Wittenberg, H. Some fundamentals on the performance of ramjets with subsonic and supersonic combustion. Rijswijk, The Netherlands: TNO Prins Maurits Laboratory, 2000.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Experimental and analytical methods for the determination of connected-pipe ramjet and ducted rocket internal performance. Neuilly sur Seine, France: AGARD, 1994.

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Burkardt, Leo A. RAMSCRAM: A flexible ramjet/scramjet engine simulation program. [Washington, DC]: National Aeronautics and Space Administration, 1990.

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Dash, Sanford M. Computational models for the analysis/design of hypersonic scramjet nozzles - Part 1: Combustor and nozzle models. New York: AIAA, 1986.

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Book chapters on the topic "Ramjet engines"

1

Ingenito, Antonella. "Ramjet Engines Performance." In Subsonic Combustion Ramjet Design, 19–34. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-66881-5_4.

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Ingenito, Antonella. "Fundamentals of Ramjet Engines." In Subsonic Combustion Ramjet Design, 5–7. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-66881-5_2.

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Ingenito, Antonella. "Material Selection for Ramjet Engines." In Subsonic Combustion Ramjet Design, 99–113. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-66881-5_11.

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El-Sayed, Ahmed F. "Pulsejet, Ramjet, and Scramjet Engines." In Fundamentals of Aircraft and Rocket Propulsion, 315–401. London: Springer London, 2016. http://dx.doi.org/10.1007/978-1-4471-6796-9_5.

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Babu, V. "Ramjet and Scramjet Engine." In Fundamentals of Propulsion, 135–53. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-79945-8_8.

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Mühleck, P., H. Schütz, and F. Kremer. "Influence of the Flight Trajectory on the Exhaust Gas Composition of a H2-Fueled Air-Breathing Ramjet Engine." In Orbital Transport, 427–37. Berlin, Heidelberg: Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-45720-3_32.

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Gairola, S. P., Abhay Dashmana, Sanjeev Kumar Joshi, and Sanjeev Dhama. "RAMJET ENGINES." In Futuristic Trends in Mechanical Engineering Volume 3 Book 1, 63–81. Iterative International Publisher, Selfypage Developers Pvt Ltd, 2024. http://dx.doi.org/10.58532/v3bgme1ch6.

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The theory, characteristics, construction, and design of subsonic and supersonic ramjet engines are discussed in this chapter. The information is based on domestic and foreign sources that have been published as books and magazine articles. "The theory of the fundamental engine components, including diffusers, combustion chambers, and The operation of the entire engine—as well as the jet nozzles—is taken into account. Energy sources include molecular and even atomic fuels. The goal of this Chapter is for engineers with expertise in building aircraft engines, as well as for students who have completed higher education in aviation institutes and are knowledgeable about the basics of gas dynamics and thermodynamics.

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Verma, Kumari Ambe, K. M. Pandey, K. K. Sharma, and Dhiren R. Patel. "Review of the Role of Geometrical Modification of Scramjet Combustor on Performance Characteristics." In Materials and Technologies for a Green Environment, 150–78. BENTHAM SCIENCE PUBLISHERS, 2023. http://dx.doi.org/10.2174/9789815051216123010007.

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The current scenario in the field of aviation is focused on hypersonic-speed vehicles. To achieve the required performance, engines have to be designed in such a way that their outcome should be maximum. Nowadays high-speed performance engines have utilized a type of air-breathing engine amongst which, the scramjet is found appropriate. However, the engine can only perform under atmospheric area because the supersonic combustion ramjet engine utilizes the atmospheric air as an oxidizer. Nonetheless, engines do not comprise any rotating or moving parts. So, to complete the mixing and chemical kinetics, engine geometry has special dimensions. The present chapter is focused on a rigorous review of the geometrical modification of the combustor and fuel injector. The impact of mixed fuel, different types of working fuels, and variable inflow conditions have been explored to uncover the beneficial effects on scramjet combustion performance. Since numerous authors have explored different aspects of the ongoing challenges in scramjet hence a summary has been drawn to acquire a suitable model for future work.

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Sandeep, Juluru. "Design and Performance of Hypersonic Intake for Scramjet Engine." In Hypersonic and Supersonic Flight - Advances in Aerodynamics, Materials, and Vehicle Design [Working Title]. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.107840.

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Rockets are the only vehicles to reach hypersonic speeds with non-airbreathing engines carrying both fuel and oxidizer increasing budget of space exploration. So, the desire to achieve hypersonic speeds at low cost has led to the development of air-breathing engines known as supersonic combustion ramjet engines or scramjet engines. The most complex part in the development of the scramjet engine is the intake. Free-stream hypersonic speed flow will be compressed in intake and processed into the combustor as per the required pressure and temperature. The high-pressurized flow can be provided to the combustor based on the strength of shocks attained in the intake due to ramps. So, the design of intake depends on the number of ramps and the angle of ramp, which decides the strength of shock for compression. All the scramjet intakes designed based on oblique shock theory will start efficiently in the designed conditions, but the main problem is unstarting the performance of intake at off-design conditions. It is very important to know the flow behavior at off-design conditions to enhance the operating range of the engine. So, in this chapter, a detailed procedure for the design of hypersonic intake and techniques to mitigate the unstarting conditions of scramjet engines is discussed.

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Munévar, Gonzalo. "Humankind in Outer Space." In The Dimming of Starlight, 176—C7N50. Oxford University PressNew York, 2023. http://dx.doi.org/10.1093/oso/9780197689912.003.0007.

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Abstract This chapter discusses humankind in outer space. Teleoperators and robots do some aspects of space exploration more efficiently; humans have advantages in other aspects. The poorly designed Space Shuttle set back both machine and human exploration. Large-scale human colonization will need faster spaceships, or large exploring O’Neill “colonies” with artificial gravity (from rotation). The obstacle to light-speed spaceships is Einstein’s velocity-addition formula, not Einstein’s mass equation. For near-relativistic spaceships, the obstacle is the gigantic amount of fuel it would carry. The Bussard ramjet would scoop hydrogen ions from space as fuel. Whitmire catalytic nuclear ramjet would be more efficient. Thorne proposes using Wheeler wormholes to travel faster than light, but his proposal is mired in time-travel paradoxes. Alcubierre argued that an engine that contracts space-time in front of the starship and expands space-time behind it (general theory of relativity) would allow the starship to go arbitrarily faster than light.

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Conference papers on the topic "Ramjet engines"

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"Hypersonic Methane Rocket-Ramjet Engines for RLV." In 55th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.iac-04-s.5.12.

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Sakata, Kimio, Hiroyuki Nouse, and Mitsuhiro Minoda. "Some Topics of Research on Hypersonic Airbreathing Engines at National Aerospace Laboratory." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-256.

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Some research tupics on hypersonic airbreathing engines conducted at National Aerospace Laboratory in Japan (NAL) are introduced. Variable Cycle engine (VCE) for the next generation supersonic transports (SST), Combined turbo-ramjet engine for hypersonic transports (HST) and turbo-engines, such as Airturbo-ramjet engine (ATR), and Scramjet engine for Space Plane propulsion systems are being studied. Engine system design to make evaluate capability for Space Plane and system optimization are described. Component studies; supersonic air-intake with mixed and internal compression configuration, hydrogen fueled ram-combustor, supersonic combustion chamber, high temperature and highly loaded turbo-component, regenerative heat exchanger and noise reduction nozzle are being conducted and some results are presented. In the material study, carbon/carbon composites, metal compound metal matrix composites and functionally gradient material (FGM) are also investigated and evaluated for application to high temperature and/or light weight structures.

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YANG, V., and F. E. CULICK. "Nonlinear analysis of pressure oscillations in ramjet engines." In 24th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1.

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Burkardt, Leo A., and Leo C. Franciscus. "RAMSCRAM: A Flexible RAMJET/SCRAMJET Engine Simulation Program." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-323.

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With the resurgence of interest in high supersonic and hypersonic flight there is a need to simulate airbreathing engines which may be used in this flight regime. To meet this requirement the RAMSCRAM code was developed. The code calculates one-dimensional flow properties at each component interface and the overall performance of the engine. It uses equilibrium thermodynamics which accounts for dissociation and allows for any fuel or combination of fuels. The program can simulate ramjet, scramjet, rocket, and ducted rocket engines.

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Zellner, B., W. Sterr, and O. Herrmann. "Integration of Turbo-Expander- and Turbo-Ramjet-Engines in Hypersonic Vehicles." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-204.

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Turbo-Expander-Ramjet and Turbo-Ramjet are two engine concepts considered for hypersonic aircraft designs with a flight regime between Mach 0 and 7. To establish any performance or integration aspects for these two combined-cycle engine types, an extended study of a variety of influence parameters is necessary, because the interaction between aircraft and propulsion system is even stronger than on conventional aircraft. In fact, the propulsion system is very sensitive to intake and nozzle/afterbody design at these high speeds.

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Reynolds, John, Miles Nesman, Singh Brijendra, and Felix Torres. "Process-based Development Cost Model for Ramjet-Scramjet Engines." In AIAA Space 2003 Conference & Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-6344.

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Kremer, Frans G. J. "Balance of Moments for Hypersonic Vehicles." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-251.

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Ramjet engines propelling hypersonic flight vehicles will be highly integrated into the vehicle, resulting in strong interactions between the vehicle and the engine. An assessment of these interactions in relation to the flight mission is made by simple but adequate modeling of the flight vehicle aerodynamics and the engine performance. Especially moments associated with the propulsion system are of interest. This paper deals with the pitch moments introduced by the ramjet related forces, which are evaluated by one-dimensional engine performance and by modeling of the inlet and nozzle flow. Furthermore, it discusses the balance of moments for the first stage of a two stage transportation system for an ascent trajectory.

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Sachs, G., M. Heller, and L. Wahlberg. "Robust control of a hypersonic experimental vehicle with ramjet engines." In Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-3728.

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HARTUNG, L. "Orbit-on-demand vehicle propelled by air-turborocket/ramjet engines." In 22nd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1847.

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Yao, Yao, Xiaobo Zhang, Mingyang Zhang, and Zhanxue Wang. "Modeling and Cycle Parameter Matching of a High-Speed Variable Cycle Turbofan-Ramjet Engine." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-80505.

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Abstract Variable cycle turbofan-ramjet (VCTR) engine is a promising propulsion system candidate for future Mach 4+ vehicles. Compared with conventional turbine engines, the VCTR engine has a higher thrust-to-weight ratio, a smaller diameter and a more compact structure. A component-based simulation model is developed to explore the operating characteristics of a high-speed VCTR concept. Modeling methods of variable-geometry components are characterized in this paper, and then the way to build the VCTR model solver is described. The VCTR engine simulation model is validated by the numerical and experimental results of double bypass variable cycle engines from NASA technical reports. Performance and control law of the VCTR engine along the flight trajectory with flight Mach number varying from 0.5 to 4.0 are obtained to maximize net thrust and compared with that of a conventional two-spool afterburning mixed-flow turbofan (MFTF). Results show that the VCTR’s performance is highly dependent on the fan characteristics and limited by various operating constraints, such as fan surge margin, turbine inlet temperature, and compressor discharge temperature. In addition, the thrust level of the MFTF with the variable-area low-pressure turbine is close to the VCTR engine.

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Reports on the topic "Ramjet engines"

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Culick, F. E., F. E. Marble, and E. E. Zukoski. Mechanisms of Exciting Pressure Oscillations in Ramjet Engines. Fort Belvoir, VA: Defense Technical Information Center, June 1985. http://dx.doi.org/10.21236/ada172546.

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Aaron Koopman. RAMGEN ROTOR CARTRIDGE FOR THE PRE-PROTOTYPE RAMGEN ENGINE. Office of Scientific and Technical Information (OSTI), September 2003. http://dx.doi.org/10.2172/833214.

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Holcomb, Franklin H., Chang W. Sohn, Gunnar Tamm, Daniel Brown, Daniel Mahoney, Peter Baldwin, Karen Belshaw, Aaron Koopman, and Dennis Witmer. Ramgen Power Systems for Military Engine Applications. Fort Belvoir, VA: Defense Technical Information Center, May 2007. http://dx.doi.org/10.21236/ada477898.

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Aaron Koopman. DEVELOPMENT AND TESTING OF A PRE-PROTOTYPE RAMGEN ENGINE. Office of Scientific and Technical Information (OSTI), July 2003. http://dx.doi.org/10.2172/826018.

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Ramgen Power Systems. DEVELOPMENT AND TESTING OF A PRE-PROTOTYPE MACH 2 RAMGEN ENGINE. Office of Scientific and Technical Information (OSTI), September 2001. http://dx.doi.org/10.2172/799768.

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Friesen, H. N. Radiological effluents released from nuclear rocket and ramjet engine tests at the Nevada Test Site 1959 through 1969: Fact Book. Office of Scientific and Technical Information (OSTI), June 1995. http://dx.doi.org/10.2172/101088.

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Noone, Emily, and Lydia Harriss. Hypersonic missiles. Parliamentary Office of Science and Technology, June 2023. http://dx.doi.org/10.58248/pn696.

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This POSTnote looks at hypersonic missile technologies, efforts to develop them, potential applications, and the possible challenges they may present for missile defence and global stability. Key Points: • Hypersonic missiles combine speeds of over five times the speed of sound with significant manoeuvrability during flight. • Their manoeuvrability enables them to change trajectory during flight, making their flight-path and target difficult to predict. • They fly at lower altitudes than ballistic missiles, which means that they may be harder to track at long distances with some surface-based sensors, such as certain radar. • There are two main types of hypersonic missile: hypersonic glide vehicles (HGVs) and hypersonic cruise missiles (HCMs). • HGVs are mounted onto rocket boosters for launch and may be accelerated to speeds of Mach 20 or more. The glider then separates from the booster and flies unpowered in the Earth’s upper atmosphere at altitudes of 30-80 km, before diving towards the target. • HCMs typically have a ramjet or scramjet engine that enables them to reach hypersonic speeds at altitudes of 20-40 km. • China and Russia have reportedly deployed hypersonic missiles that could deliver conventional or nuclear weapons. The US is testing multiple hypersonic technologies. • The AUKUS agreement between the UK, US and Australia includes developing hyper-sonic and counter-hypersonic technologies. • Developing hypersonic missiles requires significant research and development challenges to be overcome, contributing to their high development and manufacturing costs. • The speed, manoeuvrability and altitude of hypersonic missiles may challenge existing missile defences, although their uses and effectiveness are still being assessed. • Defence analysts disagree about the potential implications of hypersonic missiles for global peace and stability. Some suggest they could increase the risk of conflict escalation, while others say that they will not alter the strategic balance between nuclear powers. • Arms control, export controls and other measures may help limit potential harm to peace and stability, but these approaches face challenges.

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