Estimation of possibility of use of MHD control in scramjet

Kopchenov, V. I.; Vatazhin, A. B.; Gouskov, O.

doi:10.2514/6.1999-4971

Cited by 23 publications

(10 citation statements)

References 6 publications

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“…Those functions can only be performed in ways that do not bring the flow to stagnation, since the total temperature of the flow passing through the combustor is too high and the pressure losses associated with the entropy rise through shocks would be too great. While it has been proposed to use an MHD device in the inlet to optimize the performance of the engine, [3][4][5][6][13][14][15][16][17] the lack of conductivity of the air makes that approach very costly. In flight regimes below approximately Mach 12, the temperature of the air in the inlet is so low that, even with alkali seeding, the conductivity is too low for power extraction or control.…”

Section: Drag Reduction and Lift Enhancement On Re-entry Vehiclesmentioning

confidence: 99%

Plasma-Enhanced, Hypersonic Performance Enabled by MHD Power Extraction

Miles

Steeves

Smith

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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This paper reviews work underway on the development of new technologies that will enhance the performance of hypersonic vehicles through plasma-related processes and the utilization of MHD to provide the large power levels that are required to drive these processes. Three technologies are discussed for plasma-enhanced hypersonic performance. These include: (1) the use of off-body plasmas for drag reduction, steering, and enhanced inlet performance; (2) the use of surface or near-surface plasmas for mitigating local heating and controlling separation; and (3) the use of electron beam and plasma processes for controlling combustion for enhanced performance inside the engine and for local heat addition applications in other regions of the flow path. For realistic scale vehicles, the energies required for these applications exceed the present capability of on-board auxiliary power units, and, therefore, will require power to be generated directly from the hypersonic air passing over the vehicle or through the engine. In the high Mach number regime characteristic of re-entry vehicles, there is sufficient heating of the air to allow MHD power extraction using equilibrium ionization of alkali vapor seed material. By replacing a portion of the vehicle surface with a hollow core truss structure containing an embedded magnet coil, hundreds of kilowatts of power can be extracted during re-entry and used for vehicle control or other applications. At lower Mach numbers, MHD power extraction can be done downstream of the engine, then the temperature of the exhaust can be high enough to allow conductivity to be achieved with alkali seeding. This MHD generated power extracted from the flow aft of the engine can be used for plasma control upstream of the engine as well as for engine performance enhancement. Some aspects of this reverse energy bypass concept are analyzed in the paper, including plasma heating of the inlet flow that would allow elimination of the isolator, snowplow surface arcs for boundary layer and separation control, and electron beam and microwaves for initiation and control of combustion. I. Introduction

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Section: Drag Reduction and Lift Enhancement On Re-entry Vehiclesmentioning

confidence: 99%

Plasma-Enhanced, Hypersonic Performance Enabled by MHD Power Extraction

Miles

Steeves

Smith

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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“…At off-design Mach numbers, energy addition to or extraction from the flow, using plasmas and various magnetohydrodynamic devices, can be considered as an alternative to a variable geometry inlet [2][3][4][5][6][7][8][9][10][11][12][13][14][15]. An important advantage of plasma-based methods of inlet and isolator control is their flexibility, controllability, and fast response.…”

Section: Scramjet Inlet Control By Plasma-induced Heating: the Reversmentioning

confidence: 99%

“…Weakly ionized plasmas together with electric and magnetic fields can offer interesting opportunities for flight performance enhancement by using energetic effects (energy addition and extraction and volumetric body forces) in place of traditional variable-geometry aerodynamic methods [2][3][4][5][6][7][8][9][10][11][12][13][14][15]. Weakly ionized plasmas together with electric and magnetic fields can offer interesting opportunities for flight performance enhancement by using energetic effects (energy addition and extraction and volumetric body forces) in place of traditional variable-geometry aerodynamic methods [2][3][4][5][6][7][8][9][10][11][12][13][14][15].…”

Section: Introductionmentioning

confidence: 99%

Weakly Ionized Plasmas in Hypersonics: Fundamental Kinetics and Flight Applications

Macheret

2005

AIP Conference Proceedings

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Articles you may be interested inEffect of dielectric barrier discharge plasma actuators on non-equilibrium hypersonic flows A high-order numerical method to study hypersonic boundary-layer instability including high-temperature gas effects Phys. Fluids 23, 084108 (2011); 10.1063/1.3614526Modeling of the plasma generated in a rarefied hypersonic shock layer A kinetic-theory approach for computing chemical-reaction rates in upper-atmosphere hypersonic flows Abstract. The paper reviews some of the recent studies of applications of weakly ionized plasmas to supersonic/hypersonic flight. Plasmas can be used simply as means of delivering energy (heating) to the flow, and also for electromagnetic flow control and magnetohydrodynamic (MHD) power generation. Plasma and MHD control can be especially effective in transient off-design flight regimes. In cold air flow, nonequilibrium plasmas must be created, and the ionization power budget determines design, performance envelope, and the very practicality of plasma/MHD devices. The minimum power budget is provided by electron beams and repetitive high-voltage nanosecond pulses, and the paper describes theoretical and computational modeling of plasmas created by the beams and repetitive pulses. The models include coupled equations for non-local and unsteady electron energy distribution function (modeled in forwardback approximation), plasma kinetics, and electric field. Recent experimental studies at Princeton University have successfully demonstrated stable diffuse plasmas sustained by repetitive nanosecond pulses in supersonic air flow, and for the first time have demonstrated the existence of MHD effects in such plasmas. Cold-air hypersonic MHD devices are shown to permit optimization of scramjet inlets at Mach numbers higher than the design value, while operating in self-powered regime. Plasma energy addition upstream of the inlet throat can increase the thrust by capturing more air (Virtual Cowl), or it can reduce the flow Mach number and thus eliminate the need for an isolator duct. In the latter two cases, the power that needs to be supplied to the plasma would be generated by an MHD generator downstream of the combustor, thus forming the "reverse energy bypass" scheme. MHD power generation on board reentry vehicles is also discussed.

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“…(Other options are examined in the Billig report Hypersonic Applications and Technologies for USAF. 5 ) Option A of Figure 24 has a staging Mach number of 4 to 5. The first stage, which is powered by hydrocarbon-fueled turboramjet engines, can be employed with the second stage for space-access missions, or by itself as a future strike aircraft.…”

Section: Space Accessmentioning

confidence: 99%

“…Later analyses of the AYAKS concept predicted a much lower performance increase. 4,5,6,7,8 All of these studies were limited to a thermodynamic treatment of the gas flow or a Eulerean treatment of flow variables and shocks, both inviscid (Euler) and viscous (Navier-Stokes) flow. They were essentially limited to conservation of energy and assumed that all of the flow energy could be extracted as electricity with no losses and that the electrical power could be used to accelerate the flow, again with no losses.…”

Section: F-4mentioning

confidence: 99%

Why and Whither Hypersonics Research in the US Air Force

Fuchs¹,

Chaput²,

Frost³

et al. 2000

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This report summarizes the deliberations and conclusions of the 2000 Air Force Scientific Advisory Board (SAB) study on Why and Whither Hypersonics Research in the US Air Force. In this study the committee describes the operational requirements of a hypersonic system and presents a research program for air breathing hypersonics to meet the operational requirements. We define a program resulting in an operational air breathing hypersonic space launch system in about 2025. This program includes several exit ramps and potential options. The exit ramps would lead to either an operational rocket-based reusable launch system or continuation of the expendable course the Air Force is currently on. A Red Team Panel was part of the study team and provides alternatives to the air breathing hypersonic systems to meet the operational requirements. The study results represent an outstanding collaboration between the scientific and operational communities and among government, industry, and academia. The Study committee wishes to thank the many individuals who contributed to the deliberations and the report, as listed in Appendix A. In addition to Scientific Advisory Board members, many ad hoc members devoted their time. The team would also like to thank all the organizations that gave presentations to our panel and hosted us as listed in Appendix D. The Air Force Academy provided outstanding technical writers-Capt Susan Hastings, Capt David Jablonski, and Capt Matthew Murdoughwho provided fantastic support in preparing this report. Lt Col Dan Heale from the Air Force Research Laboratory served as an outstanding executive officer for the Investment Panel as well as provided a liaison role with Air Force Materiel Command. The Study committee would like to recognize the SAB Secretariat and support staff, in particular Maj Doug Amon, and the ANSER team, especially Ms Kristin Lynch, who provided invaluable administrative and logistical assistance in pulling together the myriad of inputs into this final report. Their efforts are greatly appreciated. Finally, this report reflects the collective judgment of the SAB and hence is not to be viewed as the official position of the United States Air Force.

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Estimation of possibility of use of MHD control in scramjet

Cited by 23 publications

References 6 publications

Plasma-Enhanced, Hypersonic Performance Enabled by MHD Power Extraction

Plasma-Enhanced, Hypersonic Performance Enabled by MHD Power Extraction

Weakly Ionized Plasmas in Hypersonics: Fundamental Kinetics and Flight Applications

Why and Whither Hypersonics Research in the US Air Force

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