On a perspective of MHD technology in aerospace applications

Bityurin, V. A.; Zeigarnik, V. A.; Kuranov, Alexander

doi:10.2514/6.1996-2355

Cited by 41 publications

(18 citation statements)

References 2 publications

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“…As one of other MHD applications in Earth-reentry or planetaryentry flights, the concept of onboard-surface MHD power generators during Earth-reentry flights was proposed by Bityurin et al [4]. They also suggested, as an example of the usages of extracted electrical power, that the extracted electrical power could be used by a flight control system to optimize reentry trajectories and particular maneuvers.…”

Section: Introductionmentioning

confidence: 98%

Aerodynamic Heating of Reentry Body Equipped with Onboard-Surface Hall Magnetohydrodynamic Generator

Fujino

Yoshino

Ishikawa

2010

Journal of Propulsion and Power

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The generator performance and the aerodynamic heating of a reentry body equipped with an onboard-surface Hall-type magnetohydrodynamic power generator are examined under some different anode electrode configuration cases by means of two-dimensional numerical simulation. The reentry body with a nose radius of 1.35 m has a pair of electrodes on the wall surface. Flight altitude and velocity are set to 60 km and 5:6 km=s, respectively. The strength of an applied magnetic field is about 0.5 T. Numerical results demonstrate that the onboard-surface Hall-type magnetohydrodynamic power generator can effectively mitigate the wall heat flux at the stagnation point as well as extract the electrical power exceeding 1 MW when a ring-shaped anode electrode is placed on the wall surface away from the stagnation point. On the other hand, if a bowl-shaped anode electrode is placed to cover a wide wall surface including the stagnation point, an effective mitigation of the wall heat flux at the stagnation point by the magnetohydrodynamic interaction becomes impossible, although the electrical power exceeding 1 MW can be obtained. This is because a Hall electric field, strong enough to induce the strong magnetohydrodynamic interaction, cannot be obtained near the stagnation point, due to the electrically coupled circuit between the plasma and the bowl-shaped anode electrode. Nomenclature B = magnetic field vector, T B r , B z = components of magnetic flux density in the r and z directions, T B 0 = magnetic flux density at the stagnation point, T D s = effective diffusion coefficient of species s, m 2 =ŝ D s = average vibrational energy of molecule s, which is created or destroyed at rate _ ! s , J=kmol E = total energy, J=kg E = electric field vector, V=m E r , E z = components of electric field in the r and z directions, V=m e = electronic charge, C e r , e z = unit vectors in the r and z directions e ve = vibrational-electronic-electron energy, J=kg e v;s = vibrational energy of species s, J=kg e v;s = equilibrium vibrational energy of species s, J=kg H = total enthalpy, J=kg h s = enthalpy of species s, J=kg h ve;s = vibrational-electronic-electron enthalpy of species s, J=kg I = load current, A I s = first ionization energy of species s, J=kmol J = vector of electric current density, A=m 2 J r , J , J z = components of electric current density in the r, , and z directions, A=m 2 k b = Boltzmann's constant, J=K k b;i = backward reaction rate coefficient for reaction i, m 3 =kmol s or m 6 =kmol 2 s k f;i = forward reaction rate coefficient for reaction i, m 3 =kmol s M e = molecular weight of electron, kg=kmol M s = molecular weight of species s, kg=kmol m = mobility of electron, m 2 =V s m e = mass of electron, kg n e = number density of electron, 1=m 3 n s = number density of species s, 1=m 3 _ n e;s= molar rate of production of species s by electron impact ionization, kmol=m 3 s P = electrical power extracted by magnetohydrodynamic power generator P 1 = freestream pressure, Pa p = static pressure, Pa p e = partial pressure of ...

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Section: Introductionmentioning

confidence: 98%

Aerodynamic Heating of Reentry Body Equipped with Onboard-Surface Hall Magnetohydrodynamic Generator

Fujino

Yoshino

Ishikawa

2010

Journal of Propulsion and Power

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“…Nomenclature A = cross-sectional area C D = drag coefficient c p = specific heat at constant pressure D = diameter of body d = diameter of filament G,G = spatial distribution functions for energy deposition I = impulse L = streamwise length ' = characteristic length M = freestream Mach number _ m = mass flow rate P = power p = pressure Q = energy added per unit volume per time Q o = magnitude of energy deposition (energy per unit volume per time) Q T = energy deposited in V in time interval e q = energy added per unit mass per time q o = magnitude of energy deposition (energy per unit mass per time) q T = energy per mass deposited in V in time interval e R = gas constant for air T = temperature T = temporal distribution function for energy deposition U = freestream velocity V = volume v = velocity = f = 1 = ratio of specific heats E f = energy added e , i , L = dimensionless time scales ", " 0 = energy deposition parameters = efficiency of energy deposition = density $ = ratio of energy added to energy required to choke the flow = dimensionless time parameter e = duration of energy pulse Subscripts f = filament 1 = freestream I. Overview I N RECENT years, there has been intense activity in developing a fundamental understanding and practical applications of flow control at high speed using energy deposition. This interest is reflected in numerous conferences and workshops, including the Weakly Ionized Gas Workshops [1-8], the St. Petersburg Workshops [9-12], and the Institute for High Temperatures Workshops [13][14][15][16][17][18][19]. The scope of this research is broad.…”

mentioning

confidence: 98%

“…I N RECENT years, there has been intense activity in developing a fundamental understanding and practical applications of flow control at high speed using energy deposition. This interest is reflected in numerous conferences and workshops, including the Weakly Ionized Gas Workshops [1][2][3][4][5][6][7][8], the St. Petersburg Workshops [9][10][11][12], and the Institute for High Temperatures Workshops [13][14][15][16][17][18][19]. The scope of this research is broad.…”

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confidence: 99%

Survey of Aerodynamic Drag Reduction at High Speed by Energy Deposition

Knight

2008

Journal of Propulsion and Power

233

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A selected survey of aerodynamic drag reduction at high speed is presented. The dimensionless governing parameters are described for energy deposition in an ideal gas. The types of energy deposition are divided into two categories. First, energy deposition in a uniform supersonic flow is discussed. Second, energy deposition upstream of a simple aerodynamic body is examined. Both steady and unsteady (pulsed) energy deposition are examined for both categories, as well as the conditions for the formation of shock waves and recirculation regions. The capability of energy deposition to reduce drag is demonstrated experimentally. Areas for future research are briefly discussed. Nomenclature A = cross-sectional area C D = drag coefficient c p = specific heat at constant pressure D = diameter of body d = diameter of filament G,G = spatial distribution functions for energy deposition I = impulse L = streamwise length ' = characteristic length M = freestream Mach number _ m = mass flow rate P = power p = pressure Q = energy added per unit volume per time Q o = magnitude of energy deposition (energy per unit volume per time) Q T = energy deposited in V in time interval e q = energy added per unit mass per time q o = magnitude of energy deposition (energy per unit mass per time) q T = energy per mass deposited in V in time interval e R = gas constant for air T = temperature T = temporal distribution function for energy deposition U = freestream velocity V = volume v = velocity = f = 1 = ratio of specific heats E f = energy added e , i , L = dimensionless time scales ", " 0 = energy deposition parameters = efficiency of energy deposition = density $ = ratio of energy added to energy required to choke the flow = dimensionless time parameter e = duration of energy pulse Subscripts f = filament 1 = freestream I. Overview I N RECENT years, there has been intense activity in developing a fundamental understanding and practical applications of flow control at high speed using energy deposition. This interest is reflected in numerous conferences and workshops, including the Weakly Ionized Gas Workshops [1-8], the St. Petersburg Workshops [9-12], and the Institute for High Temperatures Workshops [13][14][15][16][17][18][19]. The scope of this research is broad. It encompasses a wide variety of energy deposition techniques (e.g., plasma arcs, laser pulse, microwave, electron beam, glow discharge, etc.) and a wide range of applications (e.g., drag reduction, lift and moment enhancement, improved combustion and mixing, modification of shock structure, etc.).The objective of this paper is to provide a selective survey of research on aerodynamic drag reduction at high speed using energy deposition. The research is reviewed principally from the viewpoint of ideal gas dynamics to elucidate the thermal effects of energy deposition on supersonic flow. In general, nonideal gas effects are not considered (except insofar as they naturally occur in the experiments cited herein) and are the topic of a future survey.The remainder of this paper is d...

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“…The interest to the supersonic §ow control by means of the electromagnetic ¦eld has been renewed after papers [1,2], in which several new ¦elds have been proposed. These proposals could be conditionally classi¦ed as (i) the §ow control and (ii) the power generation.…”

Section: Introductionmentioning

confidence: 99%