Numerical Modeling of a Pulsed Electromagnetic Plasma Thruster Experiment

Cassibry, Jason; Thio, Francis; Markusic, Thomas E.; Wu, S. T.

doi:10.2514/1.16215

Cited by 13 publications

(5 citation statements)

References 18 publications

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“…In 1999, Thio et al [45] described an MTF approach that could provide a specific impulse of 7.7 × 10 4 s, power-to-mass ratios up to 1.14 MW∕kg at repetition rate ω 100 Hz, thrust of 340 kN, jet power of 128 GW, and total system mass of 112 tons. Pulsed electromagnetic plasma accelerators were tested [46] and modeled [47] as potential drivers for the plasma liner. The NASA MSFC Advanced Concepts Office conducted a detailed mission analysis for a human-piloted mission to Callisto, summarized in a 140 page analysis of interplanetary mission with human crew using the PJMIF as propulsion [48].…”

Section: B Major Nasa Programsmentioning

confidence: 99%

Case and Development Path for Fusion Propulsion

Cassibry¹,

Cortez²,

Stanić³

et al. 2015

Journal of Spacecraft and Rockets

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This paper discusses the importance of fusion propulsion for interplanetary space travel, illustrates why the magnetoinertial fusion parameter space may facilitate the most rapid, economic path for development, justifies the choice of pulsed Z pinch, and provides a potential development path leading up to a technical readiness level 9 system. Round trips of less than one year to Mars are only possible using fusion propulsion systems. Such a system will require an onboard nuclear fission reactor for reliable startups, and so fission and fusion developments for space are mutually beneficial. The paper reviews the more than 50 year history of fusion research and summarizes results from a recent study of the fusion parameter space for terrestrial power, which suggests magnetoinertial fusion can provide the smallest, most economical approach for a fusion propulsion system. Emerging experimental data and theory show pulsed Z-pinch fusion solves some of the most deleterious instabilities and scales to fusion breakeven within reach of current pulsed power facilities. The paper illustrates a potential development path to a technical readiness level 9 flight system, starting from an assumed technical readiness level 2 for the current state of fusion propulsion. Nomenclature a = acceleration, m∕s 2 g 0 = gravitational acceleration at Earth's surface, m∕s 2 J = mission difficulty parameter, m 2 ∕s 3 k = ratio of tank to propellant mass m = mass, kg _ m = mass flow rate, kg∕s N = total number of stages, number of fusion reactions n = number density P = power, W R = distance traveled, m T = total trip time and time, s t = time, s V = reacting volume, m 3 v j = jet or exhaust velocity, m∕s Y = fusion energy yield, J α = propulsion system specific mass, kg∕W β = mission type multiplication factor γ = ratio of propulsion system to initial mass of nth stage Δv = velocity increment, m∕s λ = payload mass fraction τ = characteristic time, s Subscripts burn = propulsive burn c, coast = unpowered coasting conf = confinement d = dwell, as in dwell time τ d f = final fus = fusion jet = jet, as in for jet power P jet n = number of the stage opt = optimum p = propulsion time pay = payload pn = propulsion time for nth stage (as in for T pn ) pr = propellant ps = propulsion system t = tank 0 = initial 1, 2 = dummy subscripts indicating different species

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Section: B Major Nasa Programsmentioning

confidence: 99%

Case and Development Path for Fusion Propulsion

Cassibry¹,

Cortez²,

Stanić³

et al. 2015

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

show abstract

“…There is an increasing need for precision from the control of micro/nano satellites, which can be achieved by optimizing µPPT processes. Since experiments are cost-intensive, numerical methods are often used to simulate the working processes of the µPPT, so as to explore the effects of relevant parameters on improving performance [6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Theoretical Modeling and Parameter Analysis of Micro-Pulsed Plasma Thruster

et al. 2018

Energies

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In this paper, a new numerical modeling method that combines a modified electromechanical model with a Teflon ablation model is proposed to simulate the working process of micro-pulsed plasma thruster (µPPT). The ablation mass accumulation during the discharge process and the non-Fourier effect during the ablation process are considered to improve simulation accuracy. Simulation results are in good agreement with experimental results. Furthermore, the influence of both the electrical and structural parts on the performance of µPPT was investigated by applying the combined model. It was proven that large capacitance of the capacitor and large gap-to-plate-width ratios can effectively improve the comprehensive performance of the thruster concluding the specific impulse, impulse bit, and efficiency. The results not only validate the theoretical model, but also guide the design and operation optimization of µPPT.

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“…The plume characteristics have been studied by many researchers [1][2][3][4][5][6][7][8][9][10][11] because it is of interest in the contamination assessment of electric thrusters and important for the investigation of plume-spacecraft interactions. The plasma plume of a rectangular geometry ablative PPT using solid Teflon for propellant is investigated.…”

Section: Introductionmentioning

confidence: 99%

“…The pulsed plasma thrusters (PPTs) characterized by high specific impulse, low electric power requirements, accurate thrust control, and simple propellant feeding system have many space applications, such as orbit maintenance, attitude control, and orbit insertion of satellite missions. The plume characteristics have been studied by many researchers [1][2][3][4][5][6][7][8][9][10][11] because it is of interest in the contamination assessment of electric thrusters and important for the investigation of plume-spacecraft interactions. The plasma plume of a rectangular geometry ablative PPT using solid Teflon for propellant is investigated.…”

Section: Introductionmentioning

confidence: 99%

“…Both experimental [1][2][3][4][5][6][7] and numerical [8][9][10][11] studies of the plume characteristics of the laboratory PPT have been carried out. Gatsonis et al [1,2], Eckman et al [3], Bryne [4], and Zwahlen [5] measured the profiles of electron temperature, density, and velocity of the plume field using the triple and quadruple Langmuir probe.…”

Section: Introductionmentioning

confidence: 99%

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Three-dimensional particle simulation of the plume of a pulsed plasma thruster

Qian

Wang

2009

Proceedings of the Institution of Mechanical Engineers, Part G:

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The plume characteristics of a pulsed plasma thruster (PPT) are considered necessary in the evaluation of plume/spacecraft interactions. In this article, the rarefied plasma plume of a laboratory PPT is characterized. First, a three-dimensional (3D) physical model with boundary conditions is presented. Then, the particle-in-cell and direct simulation Monte-Carlo hybrid methods are employed to study the flow field. The profiles of the plasma density and potential and their variations versus time are analysed. Also, the computational results are compared with experiment data as well as with results from existing two-dimensional (2D) simulations. The comparisons show that the computational model can predict the electron density of plume in both parallel and perpendicular planes. It is also shown that the 3D predictions are more accurate than those of the 2D model. Analysis of the plume backflow indicates that less than one thousandth of the mass that is released from the solid propellant enters the backflow region at the end of a pulse period.

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Numerical Modeling of a Pulsed Electromagnetic Plasma Thruster Experiment

Cited by 13 publications

References 18 publications

Case and Development Path for Fusion Propulsion

Case and Development Path for Fusion Propulsion

Theoretical Modeling and Parameter Analysis of Micro-Pulsed Plasma Thruster

Three-dimensional particle simulation of the plume of a pulsed plasma thruster

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