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  • 1
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    Antimatter Requirements and Energy Costs for Near-Term Propulsion Applications (1999)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: The superior energy density of antimatter annihilation has often been pointed to as the ultimate source of energy for propulsion. However, the limited capacity and very low efficiency of present-day antiproton production methods suggest that antimatter may be too costly to consider for near-term propulsion applications. We address this issue by assessing the antimatter requirements for six different types of propulsion concepts, including two in which antiprotons are used to drive energy release from combined fission/fusion. These requirements are compared against the capacity of both the current antimatter production infrastructure and the improved capabilities that could exist within the early part of next century. Results show that although it may be impractical to consider systems that rely on antimatter as the sole source of propulsive energy, the requirements for propulsion based on antimatter-assisted fission/fusion do fall within projected near-term production capabilities. In fact, a new facility designed solely for antiproton production but based on existing technology could feasibly support interstellar precursor missions and omniplanetary spaceflight with antimatter costs ranging up to $6.4 million per mission.
    Keywords: Spacecraft Propulsion and Power
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    High-Energy Space Propulsion Based on Magnetized Target Fusion (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Magnetized target fusion is an approach in which a magnetized target plasma is compressed inertially by an imploding material wall. A high energy plasma liner may be used to produce the required implosion. The plasma liner is formed by the merging of a number of high momentum plasma jets converging towards the center of a sphere where two compact toroids have been introduced. Preliminary 3-D hydrodynamics modeling results using the SPHINX code of Los Alamos National Laboratory have been very encouraging and confirm earlier theoretical expectations. The concept appears ready for experimental exploration and plans for doing so are being pursued. In this talk, we explore conceptually how this innovative fusion approach could be packaged for space propulsion for interplanetary travel. We discuss the generally generic components of a baseline propulsion concept including the fusion engine, high velocity plasma accelerators, generators of compact toroids using conical theta pinches, magnetic nozzle, neutron absorption blanket, tritium reprocessing system, shock absorber, magnetohydrodynamic generator, capacitor pulsed power system, thermal management system, and micrometeorite shields.
    Keywords: Spacecraft Propulsion and Power
    Type: Jun 20, 1999 - Jun 23, 1999; Los Angeles, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The Performance Capabillities and Limitations of Gain-Limitated Propulsion Systems (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: Omniplanetary space flight requires new high-performance propulsion systems based on nuclear energy. Over the last several decades, many propulsion concepts have been discussed which will allow one-month missions to Mars and one-year missions to the outer planets. Such missions entail large mission velocities and vehicle accelerations, which in turn require both high exhaust velocities (and therefore, and extremely low mass-power ratios. High performance electric propulsion appears capable of enabling multi-month transits to Mars and the near-earth asteroids; however, the mass-power ratio of these systems appears too high to achieve large accelerations for outer planet missions. This presentation analyzed the round-trip mission times and distances. This analysis has shown that even high-performance power-limited systems cannot achieve the higher accelerations needed to meet fast missions to the outer planets. Gain-limited missions are necessary for those extremely aggressive missions. An analysis of spacecraft power systems via a power balance and examination of gain vs mass-power ratio has shown: (1) A minimum gain is needed to have enough power for thrust production and driver operation; (2) Increases in gain result in decreases in mass-power ratio, which in turn leads to greater achievable accelerations. However, there is an absolute minimum mass-power ratio for a given set of subsystems, even in the limit of infinite gain.
    Keywords: Spacecraft Propulsion and Power
    Type: Advanced Propulsion; Apr 05, 1999 - Apr 08, 1999; Huntsville, AL; United States
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    NASA TECHNICAL REPORTS
  • 4
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    Paving a Highway to Space (1999)
    In:  CASI
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    Publication Date: 2019-08-13
    Description: This paper presents the Paving a Highway to Space at the 49th JANNAF (Joint Army-Navy-NASA-Air force) Propulsion Meeting. The topics include: 1) Earth-To-Orbit; 2) Orbit and Beyond; 3) Duct Propulsion; 4) Electric Propulsion; 5) Beamed Energy Propulsion; 6) Externally-Effected Force; 7) Nuclear Propulsion; 8) The Road to Higher Power Densities and Performance; 9) Propulsion Technology Map; 10) Launch Applications; 11) Space Applications; and 12) Advanced High-Energy Concepts. This paper is presented in viewgraph form.
    Keywords: Spacecraft Propulsion and Power
    Type: Propulsion; Dec 14, 1999 - Dec 17, 1999; Tucson, AZ; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A Preliminary Model for Spacecraft Propulsion Performance Analysis Based on Nuclear Gain and Subsystem Mass-Power Balances (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Rapid transportation of human crews to destinations throughout the solar system will require propulsion systems having not only very high exhaust velocities (i.e., I(sub sp) 〉= 10(exp 4) to 10(exp 5) sec) but also extremely low mass-power ratios (i.e., alpha 〈= 10(exp -2) kg/kW). These criteria are difficult to meet with electric propulsion and other power-limited systems, but may be achievable with propulsion concepts that use onboard power to produce a net gain in energy via fusion or some other nuclear process. This paper compares the fundamental performance of these gain-limited systems with that of power-limited systems, and determines from a generic power balance the gains required for ambitious planetary missions ranging up to 100 AU. Results show that energy gain reduces the required effective mass-power ratio of the system, thus enabling shorter trip times than those of power-limited concepts.
    Keywords: Spacecraft Propulsion and Power
    Type: Jun 20, 1999; Los Angeles, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    The Performance Constraints of Gain-Limited Propulsion Systems (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Rapid transportation of human crews to destinations throughout the solar system will require propulsion systems having not only very high exhaust velocities (i.e., I(sub sp) greater or equal to 10(exp 4) to 10(exp 5) sec) but also extremely low mass-power ratios (i.e., alpha less than or equal to 10(exp -2) kg/kW). These criteria are difficult to meet with electric propulsion and other power-limited systems, but may be achievable with propulsion concepts that use onboard power to produce a net gain in energy via fusion or some other nuclear process. This paper compares the fundamental performance of these gain-limited systems with that of power-limited systems, and determines from a generic power balance the gains required for ambitious planetary missions ranging up to 100 AU. Results show that energy gain reduces the required effective mass-power ratio of the system, thus enabling shorter trip times than those of power-limited concepts.
    Keywords: Spacecraft Propulsion and Power
    Type: Jun 20, 1999 - Jun 25, 1999; Los Angeles, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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