Multiphase Detonations for Pulse Detonation Rocket Engines PDF Download
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Languages : en
Pages : 0
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Recent efforts in PDRE research at AFRL-West have focused on basic studies of the detonation or constant-volume combustion of multiphase mixtures. A collaborative effort is under way for developing models appropriate for PDRE application studies. This effort includes a new facility for the collection of data on liquid oxygen/gaseous fuel detonations. The facility has been designed to provide accurate and flexible control over the initial conditions of the multiphase mixtures and complete characterization of detonation parameters including initiation energies, wave speeds, pressures and rates of heat transfer. Model development is being performed by Metacomp Technologies and University of Colorado. A second experimental effort is examining the feasibility of a monopropellant-fueled pulse combustor. Analytical and numerical studies have shown the performance benefits of this approach and a preliminary system study has shown that there are significant benefits in satellite applications. An experimental demonstration of the concept is under way.
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Languages : en
Pages : 0
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Book Description
Recent efforts in PDRE research at AFRL-West have focused on basic studies of the detonation or constant-volume combustion of multiphase mixtures. A collaborative effort is under way for developing models appropriate for PDRE application studies. This effort includes a new facility for the collection of data on liquid oxygen/gaseous fuel detonations. The facility has been designed to provide accurate and flexible control over the initial conditions of the multiphase mixtures and complete characterization of detonation parameters including initiation energies, wave speeds, pressures and rates of heat transfer. Model development is being performed by Metacomp Technologies and University of Colorado. A second experimental effort is examining the feasibility of a monopropellant-fueled pulse combustor. Analytical and numerical studies have shown the performance benefits of this approach and a preliminary system study has shown that there are significant benefits in satellite applications. An experimental demonstration of the concept is under way.
Author: K. Kailasanath
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Jiun-Ming Li
Publisher: Springer
ISBN: 3319689061
Category : Technology & Engineering
Languages : en
Pages : 246
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Book Description
This book focuses on the latest developments in detonation engines for aerospace propulsion, with a focus on the rotating detonation engine (RDE). State-of-the-art research contributions are collected from international leading researchers devoted to the pursuit of controllable detonations for practical detonation propulsion. A system-level design of novel detonation engines, performance analysis, and advanced experimental and numerical methods are covered. In addition, the world’s first successful sled demonstration of a rocket rotating detonation engine system and innovations in the development of a kilohertz pulse detonation engine (PDE) system are reported. Readers will obtain, in a straightforward manner, an understanding of the RDE & PDE design, operation and testing approaches, and further specific integration schemes for diverse applications such as rockets for space propulsion and turbojet/ramjet engines for air-breathing propulsion. Detonation Control for Propulsion: Pulse Detonation and Rotating Detonation Engines provides, with its comprehensive coverage from fundamental detonation science to practical research engineering techniques, a wealth of information for scientists in the field of combustion and propulsion. The volume can also serve as a reference text for faculty and graduate students and interested in shock waves, combustion and propulsion.
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Languages : en
Pages : 377
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The current focus on utilizing detonations for air-breathing propulsion has shifted from long-term studies of the possibility of fuel energy transformation in stabilized oblique detonation waves to investigations and practical development of propulsion engines operating on propagating detonations in a pulse mode. Contrary to the oblique-detonation concept that is applicable to hypersonic flight at velocities comparable or higher than the Chapman-Jouguet detonation velocity of the fuel-air mixture, the concept of a pulse detonation engine (PDE) is attractive for both subsonic and supersonic flight with the PDE as a main propulsion unit or as an afterburner in turbojet or turbofan propulsion system. In particular, PDE-based propulsion is attractive for flight Mach number up to about 4. Within this range of Mach number, solid rocket motors are known to be very efficient in terms of simplicity and high-speed capability, but they have a limited powered range. Turbojet and turbofan engines, due to their high specific impulse, provide longer range and heavier payloads, but at flight Mach number exceeding 2-3, they get too expensive. Ramjets and ducted rockets designed for flight Mach number up to 4 require solid rocket boosters to accelerate them to the ramjet take over speed, which increase the complexity and volume of a propulsion system. Combined-cycle engines, such as turborockets or turboramjets, are also very complex and expensive for similar applications.
Author: Fouad Sabry
Publisher: One Billion Knowledgeable
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 349
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Book Description
What Is Pulse Detonation Engine 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 combustion chamber between each detonation wave and the next. Theoretically, a PDE can operate from subsonic up to a hypersonic flight speed of roughly Mach 5. An ideal PDE design can have a thermodynamic efficiency higher than other designs like turbojets and turbofans because a detonation wave rapidly compresses the mixture and adds heat at constant volume. Consequently, moving parts like compressor spools are not necessarily required in the engine, which could significantly reduce overall weight and cost. PDEs have been considered for propulsion since 1940. Key issues for further development include fast and efficient mixing of the fuel and oxidizer, the prevention of autoignition, and integration with an inlet and nozzle. To date, no practical PDE has been put into production, but several testbed engines have been built and one was successfully integrated into a low-speed demonstration aircraft that flew in sustained PDE powered flight in 2008. In June 2008, the Defense Advanced Research Projects Agency (DARPA) unveiled Blackswift, which was intended to use this technology to reach speeds of up to Mach 6 How You Will Benefit (I) Insights, and validations about the following topics: Chapter 1: Pulse Detonation Engine Chapter 2: Nuclear Pulse Propulsion Chapter 3: Rotating Detonation Engine Chapter 4: AIMStar Chapter 5: Antimatter-catalyzed nuclear pulse propulsion Chapter 6: Antimatter rocket Chapter 7: Nuclear electric rocket Chapter 8: Nuclear power in space Chapter 9: Nuclear propulsion Chapter 10: Nuclear thermal rocket Chapter 11: Project Pluto Chapter 12: Fission-fragment rocket (II) Answering the public top questions about pulse detonation engine. (III) Real world examples for the usage of pulse detonation engine in many fields. (IV) 17 appendices to explain, briefly, 266 emerging technology in each industry to have 360-degree full understanding of pulse detonation engine' technologies. Who This Book Is For Professionals, undergraduate and graduate students, enthusiasts, hobbyists, and those who want to go beyond basic knowledge or information for any kind of pulse detonation engine.
Author: R. J. Litchford
Publisher:
ISBN:
Category : Detonation waves
Languages : en
Pages : 52
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Author: S Penner
Publisher: Elsevier
ISBN: 0323153186
Category : Technology & Engineering
Languages : en
Pages : 381
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Book Description
Progress in Astronautics and Rocketry, Volume 6: Detonation and Two-Phase Flow compiles technical papers presented at the ARS Propellants, Combustion, and Liquid Rockets Conference held in Palm Beach, Florida on April 26-28, 1961. This book provides an excellent illustration of research and development on a selected group of problems relating to detonations, two-phase nozzle flow, and combustion in liquid fuel rocket engines. This volume is divided into two parts. Part 1 covers the entire range of physical conditions under which detonation may be initiated or sustained, such as high explosives, solid propellants, liquid sprays, and gases. Experimental and theoretical studies are also discussed, including the significant progress of the basic phenomena involved in transition from deflagration to detonation, and nature of stable detonations in dilute sprays and other systems. The perennial problems associated with high frequency instabilities in liquid fuel rocket engines are considered in Part 2. This publication is valuable to students and investigators working in the field of propulsion research and development.
Author: Gabriel D.. Roy
Publisher:
ISBN: 9785945880122
Category :
Languages : en
Pages : 347
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Author:
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Category :
Languages : en
Pages : 0
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Detonations of flowing mixtures of cryogenic gaseous hydrogen and liquid oxygen at mixture densities of 3-6 Kg/cu m and varying liquid oxygen fractions have been studied. Wave speeds, pressures, and the time required to effect detonation-to-deflagration transition are reported. Data taken at cryogenic conditions are compared with data taken at equal initial densities and equivalence ratios, but at ambient temperature, as well as with equilibrium, Chapman-Jouget calculations. This work has been undertaken to support development of pulse detonation rocket engines. These results will be directly applicable to the development of the next generation of repetitively pulsed, multi-tube test articles and will also be used to qualify computational models under development for use in system application studies.
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Languages : en
Pages : 0
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Book Description
Compilation of abstracts from the conference entitled International Colloquium: Advances in Experimentation & Computation of Detonations. Demands on engines used for propulsion and stationary power are increasing, since current applications involve extreme operating conditions and wide variations in load. While performance is the key focus on propulsion engines, fuel cost and hence lower specific fuel consumption is the driving factor for stationary engines. Though piston engines are extensively used, gas turbines have taken the lead as primary engines for air, sea and land power plant operations. It is time to focus our attention on alternate engine concepts. Considering the rapid energy release, flexibility, easy scalability, and low fuel consumption, engines based on pulsed detonation waves offer a significant potential. Further multi tube detonation engine with controlled sequential detonations might provide thrust vectoring without external mechanisms. Though detonation phenomena and its various aspects have been studied extensively over the past several decades, and have been utilized in devices, application of detonation to propulsion or stationary power engines is not yet realized. There has been a global resurgence on applied detonation research focussing on propulsion engines. However funds for research and development have been frugal globally, and have been decreasing. So it is timely and appropriate to review the accomplishments in detonation research, disseminate the current state of the art, and to plan for future cooperative efforts that can bring back substantial return for research investment. With this in mind, we have organized the International Colloquium on Advances in Experimentation & Computation of Detonations.
