Scramjet Driven MHD Power Demonstration - HVEPS Program

Lineberry, J.T.; Begg, Lester L.; Castro, Joaquin H.; Litchford, Ron J.

doi:10.2514/6.2006-3080

Cited by 19 publications

(9 citation statements)

References 2 publications

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“…The main objective was specification to engineering evaluation of hypersonic on-board MHD power generation system. [1] The first series of power generation experiments were completed at the end of 2006. In this paper, outline of this experiments were introduced and comparison between experimental results and numerical ones.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation for hypersonic vehicle on-board magnetohydrodynamic power generation

Harada

Kikuchi

Lineberry

2008

2008 IEEE 2nd International Power and Energy Conference

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As one of the practical application of magnetohydrodynamic (MHD) electric power generation, hypersonic vehicle electric power system (HVEPS) program started from 2001. Scramjet driven MHD power generation experiments were conducted and reasonable output electric power was successfully extracted. We carried out 1-and 3-dimensional numerical simulations in order to explain experimental results. To predict inlet conditions precisely, we had to assume adequate combustion efficiency in the scramjet combustor. Hall potential distribution in the main part of generator channel agreed well with 1-d results using adequate non-uniformity G-factor. Although end effects could be explained by the 3-d simulation, effect of nonuniformity must be studied further.

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Section: Introductionmentioning

confidence: 99%

Numerical simulation for hypersonic vehicle on-board magnetohydrodynamic power generation

Harada

Kikuchi

Lineberry

2008

2008 IEEE 2nd International Power and Energy Conference

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“…This electric current leads to a voltage difference across plasma due to interaction of charged particles' motion with an external applied magnetic field that is transverse to both the electric and magnetic fields. The Hall effects become the principal mechanisms for the Magnetohydrodynamics (MHD) electric generator [12], ion thruster [13], and the scramjet MHD energy bypass concept [14].…”

Section: Introductionmentioning

confidence: 99%

Modeling Plasma via Electron Impact Ionization

Shang

2018

Aerospace

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Variable and potential plasma applications in aerospace engineering are exemplified by ion thrusters, flow control by plasma actuator, enhanced ignition and combustion stability. The operational environments span a range from the rarefied to continuum gasdynamic regimes; however, the ionization process in practical applications is mostly by electron impact. The fundamental ionization mechanisms by electron impact consist of electron secondary mission and the cascading process. In an alternating electric field, unsteady and random micro discharges or streamers are always presented; therefore the discharge physics imposes a formidable challenge for incisive understanding. Meanwhile, the ionized species constitute hundreds of metastable chemical species; under this circumstance the physics-based modeling for analyzing the inhomogeneous medium becomes necessary. A summary of the physics-based modeling for electron impact ionization from the Boltzmann distribution equation to the inelastic particle kinetics formulation is delineated.

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“…From these reasons, a disk-shaped MHD accelerator can be used as an assisted system for a scramjet or single engine. For example, it can be applied to a combined system with a scramjet [1][2][3][4][5] because the MHD accelerator system produces thrust efficiently (greater than ion engine but lower than chemical systems). However to produce thrust, a 90 degree nozzle attached as shown in Fig.…”

Section: Introductionmentioning

confidence: 99%

“…A magnetohydrodynamics (MHD) accelerator is a significant candidate for a space propulsion system using a scramjet MHD bypass system. [1][2][3][4][5][6][7][8] This MHD bypass system is simple in principle and useful because part of the MHD accelerator can generate considerable acceleration and high-speed gas (plasma) due largely to the interaction of the working gas and the applied magnetic field when supplying an electric field (extracted energy from MHD generator part). However, most of published works focus on the linear MHD accelerator, [1][2][3][4][5][6][7][8] which has some disadvantages.…”

Section: Introductionmentioning

confidence: 99%

Fundamental Performance of Disk-shaped Magnetohydrodynamics Accelerator

Takeshita

Buttapeng

Furuya

et al. 2011

Trans. Japan Soc. Aero. S Sci.

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This paper investigates the acceleration performance of a disk-shaped magnetohydrodynamics (MHD) accelerator. Quasi-1-dimensional (Q1D) numerical simulation employing the MacCormack scheme was developed. For the longer channel length of 0.9 m, thermal loss was estimated at over 60% and effective acceleration could not be achieved owing to large heat loss and large friction loss. For shorter channel lengths, thermal loss can be reduced below 20% owing to the smaller heat and the friction losses. However, with too short a channel length, accelerator performance was decreased by the MHD compression due to excessive Faraday current density. The effect of ratio of cross sectional area on performance was also studied. For a larger area ratio, the gas can be accelerated smoothly throughout the MHD channel. However, for the excessive expansion case of a sevenfold channel, gas velocity near the exit decreased due to transition to a ''generator mode''. For the best acceleration performance, the design channel length should be as short as possible preventing compression at the channel inlet. The area ratio should be large enough to prevent the compression but not too large, to prevent transition to a ''generator mode''.

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Scramjet Driven MHD Power Demonstration - HVEPS Program

Cited by 19 publications

References 2 publications

Numerical simulation for hypersonic vehicle on-board magnetohydrodynamic power generation

Numerical simulation for hypersonic vehicle on-board magnetohydrodynamic power generation

Modeling Plasma via Electron Impact Ionization

Fundamental Performance of Disk-shaped Magnetohydrodynamics Accelerator

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