Preliminary Analysis and Design of a Rocket-based Combined Cycle Engine for Efficient Access to Space PDF Download
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Author: Lawanna Harris
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Languages : en
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Author: Lawanna Harris
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Languages : en
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781724006851
Category : Science
Languages : en
Pages : 32
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An analysis of the Independent Ramjet Stream (IRS) cycle is presented. The IRS cycle is a variation of the conventional ejector-Ramjet, and is used at low speed in a rocket-based combined-cycle (RBCC) propulsion system. In this new cycle, complete mixing between the rocket and ramjet streams is not required, and a single rocket chamber can be used without a long mixing duct. Furthermore, this concept allows flexibility in controlling the thermal choke process. The resulting propulsion system is intended to be simpler, more robust, and lighter than an ejector-ramjet. The performance characteristics of the IRS cycle are analyzed for a new single-stage-to-orbit (SSTO) launch vehicle concept, known as "Trailblazer." The study is based on a quasi-one-dimensional model of the rocket and air streams at speeds ranging from lift-off to Mach 3. The numerical formulation is described in detail. A performance comparison between the IRS and ejector-ramjet cycles is also presented. Yungster, S. and Trefny, C. J. Glenn Research Center NASA/TM-1999-209393, NAS 1.15:209393, E-11824, AIAA Paper 99-2393, ICOMP-99-05
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Languages : en
Pages : 36
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Category : Airplanes
Languages : en
Pages : 604
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Languages : en
Pages : 20
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Author: Shaye Yungster
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Category : Chemical equilibrium
Languages : en
Pages : 20
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Category :
Languages : en
Pages : 28
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Author: Alessandro Mogavero
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Category :
Languages : en
Pages : 0
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One means to reduce both the cost and the risk associated with space missions is to employ a vehicle designed within the re-usable, airliner-like 'space plane' paradigm. Key to the practicality of such vehicles is the further development of Combined Cycle Propulsion technology. In this thesis, a new engineering tool called the HYbrid PRopulsion Optimizer (HyPro) is presented, with the aim of analysing the performance of diverse engine concepts. The tool is conceived to be modular and flexible, and makes use of parsimonious modelling, in order to describe the engine at an high level of abstraction and to be fast in execution.A configurational optimizer has also been developed in order to automatically generate new design concepts, optimizing the engine cycle structure. It is conceived to be used at the beginning of development in order to perform an automatic and objective trade-off of possible propulsion solutions.In this work the model has been implemented for Rocket-Based Combined Cycle, and it has been verified and validated against analytical models, computational fluid dyanamic analyses and experimental data. The design proposed by the optimizer in these conditions was coherent with manually designed Combined Cycle Propulsion engines, demonstrating the HyPro's capability to converge on good solutions.The results, although preliminary, are very promising and represent a novelty in the field, since a configurational optimization, in the field of propulsion concepts, has never been attempted before.The results presented here demonstrate that the configurational optimization of engine design is viable.The next steps to produce a practical optimizer, which delivers robust and innovative engine solutions, are the addition of modelling capabilities beyond the Rocket-Based Combined Cycle and analysis discipline beyond the pure performances.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721568871
Category :
Languages : en
Pages : 26
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The GTX program at NASA Glenn Research Center is designed to develop a launch vehicle concept based on rocket-based combined-cycle (RBCC) propulsion. Experimental testing, cycle analysis, and computational fluid dynamics modeling have all demonstrated the viability of the GTX concept, yet significant technical issues and challenges still remain. Our research effort develops a unique capability for dynamic CFD simulation of complete high-speed propulsion devices and focuses this technology toward analysis of the GTX response during critical mode transition events. Our principal attention is focused on Mode 1/Mode 2 operation, in which initial rocket propulsion is transitioned into thermal-throat ramjet propulsion. A critical element of the GTX concept is the use of an Independent Ramjet Stream (IRS) cycle to provide propulsion at Mach numbers less than 3. In the IRS cycle, rocket thrust is initially used for primary power, and the hot rocket plume is used as a flame-holding mechanism for hydrogen fuel injected into the secondary air stream. A critical aspect is the establishment of a thermal throat in the secondary stream through the combination of area reduction effects and combustion-induced heat release. This is a necessity to enable the power-down of the rocket and the eventual shift to ramjet mode. Our focus in this first year of the grant has been in three areas, each progressing directly toward the key initial goal of simulating thermal throat formation during the IRS cycle: CFD algorithm development; simulation of Mode 1 experiments conducted at Glenn's Rig 1 facility; and IRS cycle simulations. The remainder of this report discusses each of these efforts in detail and presents a plan of work for the next year. Edwards, Jack R. and McRae, D. Scott and Bond, Ryan B. and Steffan, Christopher (Technical Monitor) Glenn Research Center NASA/CR-2003-212193, E-13796, NAS 1.26:212193
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Languages : en
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