A spherical torus nuclear fusion reactor space propulsion vehicle concept for fast interplanetary piloted and robotic missions

Williams, Craig H.; Borowski, Stanley K.; Dudzinski, Leonard A.; Juhasz, Albert J.

doi:10.2514/6.1999-2704

Cited by 13 publications

(8 citation statements)

References 7 publications

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“…6 unless a divertor is employed. 7 So, if the energetic ion escapes the tokamak toroidal field due to the drift motion, there are no obstacles to prevent it from leaving the spacecraft. It has been shown 1 that due to magnetic field ripples and a statistically preferable direction of motion of energetic ions, this can create a thrust.…”

Section: Iiia the Tokamak Toroidal Reactormentioning

confidence: 99%

Magnetic Fusion Engine

Gorelenkov¹,

Zakharov²,

Paluszek³

et al. 2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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A new concept for an interplanetary and interstellar missions is discussed, which is based on a compact spherical tokamak fusion reactor and can potentially revolutionize human space flights by providing safe and affordable in-space transportation. The goal of this paper is an assessment of the concept employing the recent advances in fusion research. This concept, in contrast to other fusion concepts, utilizes the natural drift motion of charged particles in order to create a directed flux of energetic particles. The momentum of either energetic positive particles or fusion neutrons can be used either directly for propulsion or to heat the hydrogen propellant. One-way trip times are expected to be on a short time scale, such as one to three months for the trip to Mars. Both the exhaust velocity and thrust of the engine may be modulated. This permits the engine to be optimized for a wide variety of missions.

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Section: Iiia the Tokamak Toroidal Reactormentioning

confidence: 99%

Magnetic Fusion Engine

Gorelenkov¹,

Zakharov²,

Paluszek³

et al. 2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…In a detailed analysis for the most compact tokamak concept, the spherical torus, spacecraft masses of 4000 MT were projected. [1] The maximum launch mass would need to be less than 200 MT if current chemical rockets are used for launch to LEO.…”

Section: Introductionmentioning

confidence: 99%

Mission Design Architecture for the Fusion Driven Rocket

Pancotti¹,

Slough²,

Kirtley³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The future of manned space exploration and development of space depends critically on the creation of a dramatically more proficient propulsion system for in-space transportation. This has been recognized for many years, creating a persuasive reason for investigating the applicability of nuclear power in rockets. Nuclear fuel contains energy densities that dwarf the energy of any chemical combustion. However, many such nuclear based propulsion system are not truly feasible as space-based sytems due to size, complexity, cost, or potential hazard. The Fusion Driven Rocket (FDR) described in this work offers a realistic approach to fusion propulsion systems. FDR allows for direct energy transfer to the propellant requiring no conversion to electricity. Addtionally, the propellant requires no significant tankage mass by being a solid, yet can still be rapidly heated and accelerated to high exhaust velocity (> 20 km/s). But perhaps most importantly, unlike many other fusion and fission concepts, there is no significant physical interaction with the spacecraft thereby limiting thermal heat load, spacecraft damage, and radiator mass. This paper will discuss the basic physics of the FDR and the fusion method employed as well as focus on in-depth analysis of the mission architectures enabled by the FDR. Nomenclature α cap , = specific mass of the capacitors α SEP = solar panel specific mass B = magnetic field C = fusion constant, 4.3 x 10 -8 D-T = Deuterium -Tritium ∆V = change in velocity for a mission or transfer ΔT = length of mission or transfer E in = energy input into fusion reaction E out = energy released from the fusion reaction E k = kinetic or propulsive energy f = frequency of operation η T = thrust efficiency ETO = Earth to Orbit FDR = Fusion Driven Rocket FRC = Field Reversed Configuration g 0 = gravitational constant, 9.81 m/s 2 G F = total fusion gain G I = gain from fusion igniton ICF = Interial Confinment Fusion LEO = Low Earth Orbit MIF = Magneto Inertial Fusion M L = liner mass MR = mass ratio M i = initial mass of spacecraft M f = final mass of spacecraft M S = mass of structure M P = mass of propellant M PL = mass of payload P SEP = power from solar panels 2 I sp = specific impulse R = radius of target ρ = density of target SEP = Solar Electric Power V L = linear velocity ϕ ion = Ionization energy, 75 MJ/kg

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“…The nozzle jet efficiency (η j ) is the effectiveness of converting transport power out of the reactor into directed jet power in the thrust exhaust as defined in Equation (2). The η J for this class of systems remains largely conjecture, consequently a value of 0.8 (i.e.…”

Section: Mission Analysismentioning

confidence: 99%