Multidisciplinary Optimization of Airbreathing Hypersonic Vehicles. Bowcutt, K., G. Journal of Propulsion and Power, 2001. ![Multidisciplinary Optimization of Airbreathing Hypersonic Vehicles [pdf]](https://bibbase.org/img/filetypes/pdf.svg "pdf")
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Website doi abstract bibtex Airbreathing hypersonic aircraft and missiles are characterized by a high degree of interdependence between airframe and engine. For nonaxisymmetric vehicles the propulsion system exerts a major inn uence on vehicle lift and pitching moment; this in turn inn uences vehicle stability, control, and overall mission performance. Because of strong interactions between the airframe and engine, conceptual design of this class of vehicle requires a multidisciplinary design optimization (MDO) process that can simultaneously account for the impact of selected geometric variables on all vehicle subsystems. This paper describes the development and implementation of an MDO design system that combines propulsion and external aerodynamic forces, mass properties and internal volumetric modeling, and performs geometric optimization of a hypersonic cruise missile to maximize overall mission range. The result is a conn guration with range 46% greater than the initial baseline. Such a dramatic performance increase is indicative not only of the power of optimization, but of the diff culty in conn guring hypersonic vehicles to synergize the interaction of all vehicle components without MDO methods. Nomenclature D = drag g = gravitational acceleration I sp = specii c impulse I yy = pitch moment of inertia K = centrifugal relief factor L = lift L p = propulsive lift`chine lift`lift`chine = chine length`cowl length`length`cowl = nozzle cowl length M ® = pitching-moment derivative P q = pitch acceleration R = range r E = Earth's radius T = thrust in ight direction Q T = thrust magnitude T 2 = time to double V = velocity W = weight W 0 = weight modii ed by centrifugal relief Q W = required cruise aerodynamic lift w f = fuel ow rate x eng = engine axial location ® = angle of attack µ cant = engine cant angle µ nose = upper-body nose angle µ T = thrust vector angle
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title = {Multidisciplinary Optimization of Airbreathing Hypersonic Vehicles},
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year = {2001},
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abstract = {Airbreathing hypersonic aircraft and missiles are characterized by a high degree of interdependence between airframe and engine. For nonaxisymmetric vehicles the propulsion system exerts a major inn uence on vehicle lift and pitching moment; this in turn inn uences vehicle stability, control, and overall mission performance. Because of strong interactions between the airframe and engine, conceptual design of this class of vehicle requires a multidisciplinary design optimization (MDO) process that can simultaneously account for the impact of selected geometric variables on all vehicle subsystems. This paper describes the development and implementation of an MDO design system that combines propulsion and external aerodynamic forces, mass properties and internal volumetric modeling, and performs geometric optimization of a hypersonic cruise missile to maximize overall mission range. The result is a conn guration with range 46% greater than the initial baseline. Such a dramatic performance increase is indicative not only of the power of optimization, but of the diff culty in conn guring hypersonic vehicles to synergize the interaction of all vehicle components without MDO methods. Nomenclature D = drag g = gravitational acceleration I sp = specii c impulse I yy = pitch moment of inertia K = centrifugal relief factor L = lift L p = propulsive lift`chine lift`lift`chine = chine length`cowl length`length`cowl = nozzle cowl length M ® = pitching-moment derivative P q = pitch acceleration R = range r E = Earth's radius T = thrust in ight direction Q T = thrust magnitude T 2 = time to double V = velocity W = weight W 0 = weight modii ed by centrifugal relief Q W = required cruise aerodynamic lift w f = fuel ow rate x eng = engine axial location ® = angle of attack µ cant = engine cant angle µ nose = upper-body nose angle µ T = thrust vector angle},
bibtype = {article},
author = {Bowcutt, Kevin G},
doi = {10.2514/2.5893},
journal = {Journal of Propulsion and Power},
number = {6}
}
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