Download or read book Rocket induced Magneto hydrodynamic Ejector written by John Cole and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Combustion and Magnetohydrodynamic Processes in Advanced Pulse Detonation Rocket Engines written by Lord Kahil Cole and published by . This book was released on 2012 with total page 227 pages. Available in PDF, EPUB and Kindle. Book excerpt: A number of promising alternative rocket propulsion concepts have been developed over the past two decades that take advantage of unsteady combustion waves in order to produce thrust. These concepts include the Pulse Detonation Rocket Engine (PDRE), in which repetitive ignition, propagation, and reflection of detonations and shocks can create a high pressure chamber from which gases may be exhausted in a controlled manner. The Pulse Detonation Rocket Induced Magnetohydrodynamic Ejector (PDRIME) is a modification of the basic PDRE concept, developed by Cambier (1998), which has the potential for performance improvements based on magnetohydrodynamic (MHD) thrust augmentation. The PDRIME has the advantage of both low combustion chamber seeding pressure, per the PDRE concept, and efficient energy distribution in the system, per the rocket-induced MHD ejector (RIME) concept of Cole, et al. (1995). In the initial part of this thesis, we explore flow and performance characteristics of different configurations of the PDRIME, assuming quasi-one-dimensional transient flow and global representations of the effects of MHD phenomena on the gas dynamics. By utilizing high-order accurate solvers, we thus are able o investigate the fundamental physical processes associated with the PDRIME and PDRE concepts and identify potentially promising operating regimes. In the second part of this investigation, the detailed coupling of detonations and electric and magnetic fields are explored. First, a one-dimensional spark-ignited detonation with complex reaction kinetics is fully evaluated and the mechanisms for the different instabilities are analyzed. It is found that complex kinetics in addition to sufficient spatial resolution are required to be able to quantify high frequency as well as low frequency detonation instability modes. Armed with this quantitative understanding, we then examine the interaction of a propagating detonation and the applied MHD, both in one-dimensional and two-dimensional transient simulations. The dynamics of the detonation are found to be affected by the application of magnetic and electric fields. We find that the regularity of one-dimensional cesium-seeded detonations can be ignificantly altered by reasonable applied magnetic fields (Bz & le 8T), but that it takes a stronger applied field (Bz> 16T) to significantly alter the cellular structure and detonation velocity of a two-dimensional detonation in the time in which these phenomena were observed. This observation is likely attributed to the additional coupling of the two-dimensional detonation with the transverse waves, which are not captured in the one-dimensional simulations. Future studies involving full ionization kinetics including collisional-radiative processes, will be used to examine these processes in further detail.
Download or read book The Pulse Detonation Rocket Induced MHD Ejector PDRIME Concept Preprint written by and published by . This book was released on 2008 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pulse detonation engines (PDEs) have received significant attention due to their potentially superior performance over constant pressure engines. However due to the unsteady chamber pressure, the PDE system will either be over- or under-expanded for the majority of the cycle, with substantial performance loss in atmospheric flight applications. Thrust augmentation, such as PDE-ejector configurations, can potentially alleviate this problem. Here, we study the potential benefits of using Magneto-hydrodynamic (MHD) augmentation by extracting energy from a Pulse Detonation Rocket Engine (PDRE) and applying it to a separate stream. In this PDRE-MHD Ejector (PDRIME) concept, the energy extracted from a generator in the nozzle is applied directly to a by-pass air stream through an MHD accelerator. The air stream is first shocked and raised to high-temperature, allowing thermal ionization to occur after appropriate seeding. The shock-processing of the high-speed air stream is accomplished by using the high initial PDRE nozzle pressures of the under-expanded phase. Thus, energy could be efficiently transferred from one stream to another. The present simulations involve use of a simple blowdown model for PDE behavior, coupled to quasi-1D and 2D numerical simulations of flow and MHD processes in the rest of the PDRIME configuration. Results show potential performance gains but some challenges associated with achieving these gains.
Download or read book Pulse Detonation Rocket Magnetohydrodynamic Power Experiment written by R. J. Litchford and published by . This book was released on 2003 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book AIAA 1995 Space Programs and Technologies Conference written by and published by . This book was released on 1995 with total page 284 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Magnetohydrodynamics Accelerator Research Into Advanced Hypersonics MARIAH written by and published by . This book was released on 1997 with total page 658 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 29th Plasmadynamics and Lasers Conference written by and published by . This book was released on 1998 with total page 434 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Scramjet Engine written by Corin Segal and published by Cambridge University Press. This book was released on 2009-06-22 with total page 271 pages. Available in PDF, EPUB and Kindle. Book excerpt: Demand for high-speed propulsion has renewed development of the supersonic combustion ramjet engine (Scramjet engine) for hypersonic flight applications.
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1995 with total page 510 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Announcements Index written by and published by . This book was released on 1996-10 with total page 1416 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Magnetohydrodynamic Ejector written by R. Neal Harvey and published by . This book was released on 1964 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book ASME 65 APM 25 written by W. H. Heiser and published by . This book was released on 1965 with total page 4 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Engineering Aspects of Magnetohydrodynamics written by and published by . This book was released on 1997 with total page 532 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Magnetohydrodynamic Species Separation in a Gaseous Nuclear Rocket written by R. A. Gross and published by . This book was released on 1963 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt: The possibility of steady flow separation of U 235 from hydrogen by magnetohydrodynamically spinning the fluid in a cylindrical vortex is treated. A gaseous nuclear rocket configuration is described and its model analyzed. The hydro magnetic equations are solved for the velocity distribution, pressure field, concentration of uranium and hydrogen, electrical power required, and dissipation rates as a function of Hartmann number, and radial Reynold's number. Results of gaseous reactor criticality calculations are given for both unshielded and shielded configura tions. Some properties of a hydrogen plasma are presented. Potential rocket performance is given and some further technical problems dis cussed. The technology involved in this rocket concept is complex and little experience is available. However, the results of this analysis are encouraging and the means of attaining a large thrust rocket with very high specific impulse are seen. (Author).
Download or read book Computational Study of Variable Area Ejector Rocket Flowfields microform written by Jason Etele and published by National Library of Canada = Bibliothèque nationale du Canada. This book was released on 2004 with total page 328 pages. Available in PDF, EPUB and Kindle. Book excerpt: Access to space has always been a scientific priority for countries which can afford the prohibitive costs associated with launch. However, the large scale exploitation of space by the business community will require the cost of placing payloads into orbit be dramatically reduced for space to become a truly profitable commodity. To this end, this work focuses on a next generation propulsive technology called the Rocket Based Combined Cycle (RBCC) engine in which rocket, ejector, ramjet, and scramjet cycles operate within the same engine environment. Using an in house numerical code solving the axisymmetric version of the Favre averaged Navier Stokes equations (including the Wilcox ko turbulence model with dilatational dissipation) a systematic study of various ejector designs within an RBCC engine is undertaken. It is shown that by using a central rocket placed along the axisymmetric axis in combination with an annular rocket placed along the outer wall of the ejector, one can obtain compression ratios of approximately 2.5 for the case where both the entrained air and rocket exhaust mass flows are equal. Further, it is shown that constricting the exit area, and the manner in which this constriction is performed, has a significant positive impact on the compression ratio. For a decrease in area of 25% a purely conical ejector can increase the compression ratio by an additional 23% compared to an equal length unconstricted ejector. The use of a more sharply angled conical section followed by a cylindrical section to maintain equivalent ejector lengths can further increase the compression ratio by 5--7% for a total increase of approximately 30%.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 1572 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Channel wall Limitations in the MHD Induction Generator written by Edward S. Pierson and published by . This book was released on 1966 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
