Author: K. K. Gupta
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages :

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Author: K. K. Gupta
Publisher:
ISBN:
Category :
Languages : en
Pages : 18

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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722349103
Category :
Languages : en
Pages : 66

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A nonlinear simulation is developed to model the longitudinal motion of a vehicle in hypersonic flight. The equations of motion pertinent to this study are presented. Analytic expressions for the aerodynamic forces acting on a hypersonic vehicle which were obtained from Newtonian Impact Theory are further developed. The control surface forces are further examined to incorporate vehicle elastic motion. The purpose is to establish feasible equations of motion which combine rigid body, elastic, and aeropropulsive dynamics for use in nonlinear simulations. The software package SIMULINK is used to implement the simulation. Also discussed are issues needing additional attention and potential problems associated with the implementation (with proposed solutions). Salas, Juan and Lovell, T. Alan and Schmidt, David K. Unspecified Center...

Author: K. K. Gupta
Publisher:
ISBN:
Category : Aeroelasticity
Languages : en
Pages : 11

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Author:
Publisher:
ISBN:
Category : Hypersonic planes
Languages : en
Pages : 532

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Author: Ernst Heinrich Hirschel
Publisher: Springer Science & Business Media
ISBN: 354089974X
Category : Technology & Engineering
Languages : en
Pages : 512

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In this book selected aerothermodynamic design problems in hypersonic vehicles are treated. Where applicable, it emphasizes the fact that outer surfaces of hypersonic vehicles primarily are radiation-cooled, an interdisciplinary topic with many implications.

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722255732
Category :
Languages : en
Pages : 34

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An integrated computational model of a generic hypersonic vehicle was developed for the purpose of determining the vehicle's performance characteristics, which include the lift, drag, thrust, and moment acting on the vehicle at specified altitude, flight condition, and vehicular configuration. The lift, drag, thrust, and moment are developed for the body fixed coordinate system. These forces and moments arise from both aerodynamic and propulsive sources. SCRAMjet engine performance characteristics, such as fuel flow rate, can also be determined. The vehicle is assumed to be a lifting body with a single aerodynamic control surface. The body shape and control surface location are arbitrary and must be defined. The aerodynamics are calculated using either 2-dimensional Newtonian or modified Newtonian theory and approximate high-Mach-number Prandtl-Meyer expansion theory. Skin-friction drag was also accounted for. The skin-friction drag coefficient is a function of the freestream Mach number. The data for the skin-friction drag coefficient values were taken from NASA Technical Memorandum 102610. The modeling of the vehicle's SCRAMjet engine is based on quasi 1-dimensional gas dynamics for the engine diffuser, nozzle, and the combustor with heat addition. The engine has three variable inputs for control: the engine inlet diffuser area ratio, the total temperature rise through the combustor due to combustion of the fuel, and the engine internal expansion nozzle area ratio. The pressure distribution over the vehicle's lower aft body surface, which acts as an external nozzle, is calculated using a combination of quasi 1-dimensional gas dynamic theory and Newtonian or modified Newtonian theory. The exhaust plume shape is determined by matching the pressure inside the plume, calculated from the gas dynamic equations, with the freestream pressure, calculated from Newtonian or Modified Newtonian theory. In this manner, the pressure distribution along the vehicle after body expa...

Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781731319258
Category : Science
Languages : en
Pages : 150

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Aerodynamic, propulsion, and mass models for a generic, horizontal-takeoff, single-stage-to-orbit (SSTO) configuration are presented which are suitable for use in point mass as well as batch and real-time six degree-of-freedom simulations. The simulations can be used to investigate ascent performance issues and to allow research, refinement, and evaluation of integrated guidance/flight/propulsion/thermal control systems, design concepts, and methodologies for SSTO missions. Aerodynamic force and moment coefficients are given as functions of angle of attack, Mach number, and control surface deflections. The model data were estimated by using a subsonic/supersonic panel code and a hypersonic local surface inclination code. Thrust coefficient and engine specific impulse were estimated using a two-dimensional forebody, inlet, nozzle code and a one-dimensional combustor code and are given as functions of Mach number, dynamic pressure, and fuel equivalence ratio. Rigid-body mass moments of inertia and center of gravity location are functions of vehicle weight which is in turn a function of fuel flow. Shaughnessy, John D. and Pinckney, S. Zane and Mcminn, John D. and Cruz, Christopher I. and Kelley, Marie-Louise Langley Research Center AERODYNAMIC CHARACTERISTICS; AERODYNAMIC FORCES; ASCENT TRAJECTORIES; COMPUTERIZED SIMULATION; CONTROL SYSTEMS DESIGN; FORCE DISTRIBUTION; HYPERSONIC VEHICLES; MATHEMATICAL MODELS; MOMENT DISTRIBUTION; PANEL METHOD (FLUID DYNAMICS); AERODYNAMIC COEFFICIENTS; ANGLE OF ATTACK; CENTER OF GRAVITY; DEGREES OF FREEDOM; DYNAMIC PRESSURE; HYPERSONICS; MACH NUMBER; MOMENTS OF INERTIA; PROPULSION; SPECIFIC IMPULSE...

Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 552

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