48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit 2012
DOI: 10.2514/6.2012-4114
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The Case and Development Path for Fusion Propulsion

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Cited by 6 publications
(7 citation statements)
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“…In contrast, a working nuclear fusion core producing thrust through direct exhaust of hot plasma, could readily generate up to *1000 km/s exhaust velocities, corresponding to *10 keV/amu [8], several hundred times higher exhaust velocities than today's high power chemical and nuclear thermal rocket engines. Lesser exhaust velocities could in principle be obtained as needed, through the co-expansion of additional cold propellant, to increase the propellant mass and optimize the exhaust velocity for individual mission requirements [9].…”
Section: Fusion's Unique Applicationmentioning
confidence: 99%
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“…In contrast, a working nuclear fusion core producing thrust through direct exhaust of hot plasma, could readily generate up to *1000 km/s exhaust velocities, corresponding to *10 keV/amu [8], several hundred times higher exhaust velocities than today's high power chemical and nuclear thermal rocket engines. Lesser exhaust velocities could in principle be obtained as needed, through the co-expansion of additional cold propellant, to increase the propellant mass and optimize the exhaust velocity for individual mission requirements [9].…”
Section: Fusion's Unique Applicationmentioning
confidence: 99%
“…There are many pre-conceptual point designs for fusion rocket cores, ranging from generic fusion rocket systems studies [11,12], to levitated dipoles [13], to mirror machines [14], to field reversed configurations [15], and magnetized target fusion [8,16]. Even ST tokamaks [17] and laser fusion sources [18] have been suggested (although present incarnations aren't reactors, and even so, are much too massive).…”
Section: Fusion's Unique Applicationmentioning
confidence: 99%
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“…However, both fissionand fusion-based propulsion schemes, are well understood and realizable at power levels, while at the same time the mass of fuel, propellant, structure, and shielding severely limit their space flight capabilities. A survey of rocket-engine performance for solar system missions beyond the Moon-Earth system has compared chemical and nuclear fission and fusion power sources [11]. One conclusion reached is that chemical rockets have reached their practical limits, epitomized by long-duration, low-payload-mass missions.…”
Section: The Thrustermentioning
confidence: 99%
“…Therefore, in both cases, the rocket relies on nuclear fission to generate propulsion. The nuclear fission propulsion is limited by thermal inefficiencies and that fusion could provide more and better mission options because of its higher power conversion efficiency and higher energy-content fuel [11].…”
Section: The Thrustermentioning
confidence: 99%