System Optimization for Maximizing Reconnaissance Mission Range of a Hypersonic Cruise Vehicle PDF Download
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Author: H. G. Kauffman
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Languages : en
Pages :
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Author: H. G. Kauffman
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Category :
Languages : en
Pages :
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Author:
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Category : Aeronautics
Languages : en
Pages : 440
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Category : Aeronautics
Languages : en
Pages : 712
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A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
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Category : Aeronautics
Languages : en
Pages : 654
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Author:
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Category : Aeronautics
Languages : en
Pages : 1048
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Author: Richard C. Walker
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Category :
Languages : en
Pages : 137
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An optimization of air breathing hypersonic cruise vehicles was performed in order to determine basic configuration characteristics and performance trends. A distinctive feature of the investigation is that prediction techniques such as the method of characteristics were used to determine the flow field surrounding the vehicle; therefore, any interaction between the aerodynamic and propulsive flow fields is accounted for in a fundamental manner. The general class of vehicles considered in the study cruise in the Mach 8-12 speed regime, utilize a hydrogen fueled supersonic combustion ramjet engine, and can be geometrically characterized as two-dimensional wedgelike shapes. Configurations were optimized for maximum cruise range as determined from the Breguet range equation which incorporates a measure of the aerodynamic, propulsive, and volumetric efficiencies of a configuration. A generalized configuration model was defined by a discrete parameters which transformed the variational problem to a static or discrete optimization problem. The direct method of function optimization, utilizing search algorithms such as random point and adaptive creeper techniques, was employed to determine the value of the parameters defining the optimum configuration for cruise at design Mach numbers of 8, 10, and 12. The design parameter space in the vicinity of the optimum point was explored to show performance sensitivity. (Author).
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Category :
Languages : en
Pages : 566
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Author:
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Category : Aeronautics
Languages : en
Pages : 638
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Author: National Aeronautics and Space Adm Nasa
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ISBN: 9781729060445
Category :
Languages : en
Pages : 40
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The class of hypersonic vehicle configurations with single stage-to-orbit (SSTO) capability reflect highly integrated airframe and propulsion systems. These designs are also known to exhibit a large degree of interaction between the airframe and engine dynamics. Consequently, even simplified hypersonic models are characterized by tightly coupled nonlinear equations of motion. In addition, hypersonic SSTO vehicles present a major system design challenge; the vehicle's overall mission performance is a function of its subsystem efficiencies including structural, aerodynamic, propulsive, and operational. Further, all subsystem efficiencies are interrelated, hence, independent optimization of the subsystems is not likely to lead to an optimum design. Thus, it is desired to know the effect of various subsystem efficiencies on overall mission performance. For the purposes of this analysis, mission performance will be measured in terms of the payload weight inserted into orbit. In this report, a trajectory optimization problem is formulated for a generic hypersonic lifting body for a specified orbit-injection mission. A solution method is outlined, and results are detailed for the generic vehicle, referred to as the baseline model. After evaluating the performance of the baseline model, a sensitivity study is presented to determine the effect of various subsystem efficiencies on mission performance. This consists of performing a parametric analysis of the basic design parameters, generating a matrix of configurations, and determining the mission performance of each configuration. Also, the performance loss due to constraining the total head load experienced by the vehicle is evaluated. The key results from this analysis include the formulation of the sizing problem for this vehicle class using trajectory optimization, characteristics of the optimal trajectories, and the subsystem design sensitivities. Lovell, T. Alan and Schmidt, D. K. Unspecified Center NAG1-1540...
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Category : Aeronautics
Languages : en
Pages : 340
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