Structural Sizing of a 25,000-lb Payload, Air-Breathing Launch Vehicle for Single-Stage-to-Orbit PDF Download
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Languages : en
Pages : 18
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Languages : en
Pages : 18
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Author: Joseph M. Roche
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Category :
Languages : en
Pages : 10
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Category :
Languages : en
Pages : 28
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Author: Charles J. Trefny
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Category :
Languages : en
Pages : 20
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720363767
Category :
Languages : en
Pages : 60
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This is an interim user's manual for current procedures used in the Vehicle Analysis Branch at NASA Langley Research Center, Hampton, Virginia, for launch vehicle structural subsystem weight estimation based on finite element modeling and structural analysis. The process is intended to complement traditional methods of conceptual and early preliminary structural design such as the application of empirical weight estimation or application of classical engineering design equations and criteria on one dimensional "line" models. Functions of two commercially available software codes are coupled together. Vehicle modeling and analysis are done using SDRC/I-DEAS, and structural sizing is performed with the Collier Research Corp. HyperSizer program.Martinovic, Zoran N. and Cerro, Jeffrey A.Langley Research CenterSTRUCTURAL WEIGHT; SINGLE STAGE TO ORBIT VEHICLES; MATHEMATICAL MODELS; USER MANUALS (COMPUTER PROGRAMS); LAUNCH VEHICLES; FINITE ELEMENT METHOD; LOADS (FORCES); ITERATION; MASS RATIOS
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Category :
Languages : en
Pages : 16
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721506842
Category :
Languages : en
Pages : 26
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The primary objective of the GTX effort is to determine whether or not air-breathing propulsion can enable a launch vehicle to achieve orbit in a single stage. Structural weight, vehicle aerodynamics, and propulsion performance must be accurately known over the entire flight trajectory in order to make a credible assessment. Structural, aerodynamic, and propulsion parameters are strongly interdependent, which necessitates a system approach to design, evaluation, and optimization of a single-stage-to-orbit concept. The GTX reference vehicle serves this purpose, by allowing design, development, and validation of components and subsystems in a system context. The reference vehicle configuration (including propulsion) was carefully chosen so as to provide high potential for structural and volumetric efficiency, and to allow the high specific impulse of air-breathing propulsion cycles to be exploited. Minor evolution of the configuration has occurred as analytical and experimental results have become available. With this development process comes increasing validation of the weight and performance levels used in system performance determination. This paper presents an overview of the GTX reference vehicle and the approach to its performance validation. Subscale test rigs and numerical studies used to develop and validate component performance levels and unit structural weights are outlined. The sensitivity of the equivalent, effective specific impulse to key propulsion component efficiencies is presented. The role of flight demonstration in development and validation is discussed. Trefny, Charles J. and Roche, Joseph M. Glenn Research Center NASA/TM-2002-211495, E-13263, NAS 1.15:211495
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Category :
Languages : en
Pages : 18
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Author: Kendall K. Brown
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Category : Airplanes, Military
Languages : en
Pages : 52
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781730724664
Category : Science
Languages : en
Pages : 70
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Book Description
The purpose of the TA-2 contract was to provide advanced launch vehicle concept definition and analysis to assist NASA in the identification of future launch vehicle requirements. Contracted analysis activities included vehicle sizing and performance analysis, subsystem concept definition, propulsion subsystem definition (foreign and domestic), ground operations and facilities analysis, and life cycle cost estimation. This document is part of the final report for the TA-2 contract. The final report consists of three volumes: Volume 1 is the Executive Summary, Volume 2 is Technical Results, and Volume 3 is Program Cost Estimates. The document-at-hand, Volume 1, provides a summary description of the technical activities that were performed over the entire contract duration, covering three distinct launch vehicle definition activities: heavy-lift (300,000 pounds injected mass to low Earth orbit) launch vehicles for the First Lunar Outpost (FLO), medium-lift (50,000-80,000 pounds injected mass to low Earth orbit) launch vehicles, and single-stage-to-orbit (SSTO) launch vehicles (25,000 pounds injected mass to a Space Station orbit). McCurry, J. Marshall Space Flight Center...
