Z-Pinch fusion-based nuclear propulsion

Miernik, Janie H.; Statham, G.; Fabisinski, Leo; Maples, C. Dauphne; Adams, Robert B.; Polsgrove, Tara; Fincher, S.; Cassibry, Jason; Cortez, Ross; Turner, Matt; Percy, Thomas K.

doi:10.1016/j.actaastro.2012.02.012

Cited by 20 publications

(9 citation statements)

References 4 publications

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“…To wrap up this section on the history, Table 2 summarizes some of the most recent fusion propulsion concepts, including specific power α, specific impulse I sp , confinement particle number density n, pulse frequency if applicable, vehicle mass, and corresponding references [48,[66][67][68][69]76,[82][83][84][85][86][87][88][89]. To the authors' knowledge, the values in this table reflect some of the most recent performance estimates for each concept listed.…”

Section: Discussionmentioning

confidence: 98%

“…A more recent theoretical study also suggests that magnetic shear may provide stabilization [81]. A recent effort by NASA MSFC and the University of Alabama in Huntsville, was conducted for a crewed mission to Mars using a Z-pinch fusion propulsion system [82]. The vehicle design required a minimum mass in low Earth orbit of 500 t. Z pinch offered substantial improvements to previous concepts, including 30 and 90 day trip times to Mars with reusable vehicles and substantial payload margins.…”

Section: H Pulsed Z Pinchmentioning

confidence: 96%

“…It will once again be necessary to iterate between computational modeling and experimental data to determine how the Z-pinch and magnetic nozzle systems are coupled. Miernik et al [82] developed a simple model of this coupling in their analysis of the Z pinch for propulsion based on the Otto cycle, which is an appropriate energy balance model for analyzing single pulses. Assuming a pure DD plasma with an initial density of 6 × 10 28 m −3 , compression ratio of 5, target mass of 10 mg, pulse frequency of 1 Hz, nozzle efficiency of 50%, and confinement time of 200 ns, we can plot thrust and specific impulse (Fig.…”

Section: B Planned Experimentsmentioning

confidence: 99%

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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: Discussionmentioning

confidence: 98%

Section: H Pulsed Z Pinchmentioning

confidence: 96%

Section: B Planned Experimentsmentioning

confidence: 99%

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Case and Development Path for Fusion Propulsion

Cassibry¹,

Cortez²,

Stanić³

et al. 2015

Journal of Spacecraft and Rockets

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show abstract

“…The numbers shown in the figure reflect a fast trip to Mars carrying an Orion module and deep space habitat. The vehicle design leverages the prior analytical work found in [33,34]. The vehicle assumes a payload mass of 50 mT and a (one-way) propellant mass of 50 mT, consistent with the mission analysis in Section VI.…”

Section: Preliminary Vehicle Designmentioning

confidence: 94%

Preliminary Analysis of the Gradient Field Imploding Liner Fusion Propulsion Concept

LaPointe

Cassibry

Adams

et al. 2018

2018 Joint Propulsion Conference

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The advancement of human deep space exploration requires the continued development of energetic inspace propulsion systems, advancing from current chemical engines to nuclear thermal rockets to future high energy concepts such as nuclear fusion. This paper presents the initial results of a NASA Innovative Advanced Concepts (NIAC) Phase I study funded to investigate the feasibility of a new pulsed fusion propulsion concept based on the rapid implosion of a fuel target injected at high velocity into a strong stationary magnetic field. The proposed concept takes advantage of the significant advances in terrestrial magneto-inertial fusion designs while attempting to mitigate the most common engineering impediments to in-space propulsion applications. A semi-analytic numerical model used to estimate target compression physics and energy release is presented, leading to estimates for engine performance. A preliminary vehicle design concept is outlined, and representative trajectory analyses for rapid Mars and Saturn missions are provided. The paper concludes with an overview of proposed next steps for theoretical and experimental validation of the concept.

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“…Discussing the state of the art of the subject is however far beyond the scope of this paper. The authors will thus limit to saying that the z-pinch reactor (mentioned in the next), is one MIF device recognised by many as the most suitable for rockets [5,17,13]. What will be hereby discussed, instead, is the way thrust can be generated in a fusion rocket.…”

Section: Introductionmentioning

confidence: 99%

Pulsed fusion space propulsion: Computational Magneto-Hydro Dynamics of a multi-coil parabolic reaction chamber

2017

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Pulsed fusion propulsion might finally revolutionise manned space exploration by providing an affordable and relatively fast access to interplanetary destinations. However, such systems are still in an early development phase and one of the key areas requiring further investigations is the operation of the magnetic nozzle, the device meant to exploit the fusion energy and generate thrust. One of the last pulsed fusion magnetic nozzle design is the so called multi-coil parabolic reaction chamber: the reaction is thereby ignited at the focus of an open parabolic chamber, enclosed by a series of coaxial superconducting coils that apply a magnetic field. The field, beside confining the reaction and preventing any contact between hot fusion plasma and chamber structure, is also meant to reflect the explosion and push plasma out of the rocket. Reflection is attained thanks to electric currents induced in conductive skin layers that cover each of the coils, the change of plasma axial momentum generates thrust in reaction. This working principle has yet to be extensively verified and computational Magneto-Hydro Dynamics (MHD) is a viable option to achieve that. This work is one of the first detailed ideal-MHD analysis of a a multi-coil parabolic reaction chamber of this kind and has been completed employing PLUTO, a freely distributed computational code developed at the Physics Department of the University of Turin. The results are thus a preliminary verification of the chamber's performance. Nonetheless, plasma leakage through the chamber structure has been highlighted. Therefore, further investigations are required to validate the chamber design. Implementing a more accurate physical model (e.g. Hall-MHD or relativistic-MHD) is thus mandatory, and PLUTO shows the capabilities to achieve that.

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Z-Pinch fusion-based nuclear propulsion

Cited by 20 publications

References 4 publications

Case and Development Path for Fusion Propulsion

Case and Development Path for Fusion Propulsion

Preliminary Analysis of the Gradient Field Imploding Liner Fusion Propulsion Concept

Pulsed fusion space propulsion: Computational Magneto-Hydro Dynamics of a multi-coil parabolic reaction chamber

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