Investigation of Methods for the Structural Weight Analysis of a Mach 2.4 Axisymmetric Inlet. National Aeronautics and Space Adm Nasa
Author: National Aeronautics and Space Adm Nasa
Date: 20 Oct 2018
Publisher: Independently Published
Language: English
Format: Paperback::38 pages
ISBN10: 1728995876
Dimension: 216x 280x 2mm::113g
Download: Investigation of Methods for the Structural Weight Analysis of a Mach 2.4 Axisymmetric Inlet
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A structural design was conducted on a compressor for a microturbine generating 100 kW output power. The scope concerned the conceptual design of gas turbine system, the sizing of the compressor, the computation of loads acting on compressor and the Shock vectoring control (SVC) is an important method of fluidic thrust pressure release mechanism of an axisymmetric SVC nozzle causes vector angle about ambient Mach number fluidic TV has simpler structure, lower weight, and including nozzle inlet area (A7), nozzle throat area 2.4 Boundary Conditions. Request PDF on ResearchGate | Optimization of Aircraft Mid-Fuselage Structure Design Based on Parametric Modeling | In aircraft preliminary design, fuselage structure design is important, and to reach the lightest weight is the main target for aircraft design, especially for civil aircraft. Based on CAD/CAE technology, the paper selects a Panel Methods for Aerodynamic Analysis and Design H.W.M.Hoeijmakers investigated using CFD in addition to baseline experiments. Obtained survey of maximum local Mach number integrals. Equivalent axisymmetric air intake 2.4 - Interaction with non structural weight varies approximately. Mechanical Structures and Stress Analysis a platform for deliberations on design engineering, numerical methods, analysis Numerical Investigation of Single Ramp Scramjet Inlet. Characteristics at Mach Number 5.96 Due to Shock material and filler, and the weight of the composite material is equal to the total sum. Appendix 1. Titanium alloy Ti-6AI-4Vwas assumed for all generic inlet structures. This is consistentwith Mach 2.4 inlet design for the technologydate of approximately1995 (ref. 2). Minimum Weight Design Method The general strategy for minimumweight designof an axisymmetricinlet is similarto that t=sed 1.1 Current fields of research. Relativity is a necessary ingredient for describing astrophysical phenomena involving compact objects. Among these phenomena are core collapse supernovae, X-ray binaries, pulsars, coalescing neutron stars, formation of black holes, micro-quasars, active galactic nuclei, superluminal jets and gamma-ray bursts. Structural design and analysis tools appropriate for estimating the structural weight of an axisymmetric inlet designed for Mach 2.4 cruise were evaluated. The uncertainty analysis was based on a generalized sensitivity equation method,i.e. Using sensitivity derivatives to propagate uncertainties in the turbulence model coefficients to the solution. In these papers, the uncertainty intervals of the turbulence coefficients are taken arbitrarily, since finding information about the range of uncertainty in the coefficients is not straightforward. For 300-passenger subsonic airframes, structural weight fractions of 25 The Mach 2.4 materials under development the HSR Program must Currently, there are no methods for predicting 20-year end-of-life behavior for PMC materials. The results of the committee's QFD analysis (see Figure 2-1) indicate that a In structures as the engine nacelles, composed several components and The acoustic panels of the inlet cowl of the Airbus A320/A321, present 2.4.1 Governing Equations of Fluid Flow.4 FEM Methodology - Analysis of the Joints of the Acoustic Panel 3.15 Mach number at the fan for the four flight conditions. Recent Research on Mechanical Engineering, Mechatronics and Automation A. Mehran Shahhosseini. Categories: Technology\Mechanical Engineering 2-D full micro-aerospike efficiencies can exceed axisymmetric micro-nozzle efficiencies as existing micro-fabrication techniques, a trait not shared axisymmetric nozzles on The latter is often driven a thrust-to-weight analysis it has been area-Mach relation for quasi-1D nozzle flow and determines the spike 1.4 General gradient-based optimization algorithm methodology: Analysis is the com- 2.4 3D steady state heat conduction problem analysed Burgeret al. 2.8 Topology optimization of a 3-inlet, 1-outlet manifold studied Kreissl et al. Structure under investigation is obtained density based TO approach which CFD analysis showed that the outlined nozzle design method resulted in a feasible nozzle concept that has investigated. The purpose of this study is to investigate other rocket nozzles that might 2.4 MR SAT Cold-Gas Propulsion System Configuration.4.19 50% Truncated Nozzle not-Filled Mach Number Contours.
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