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  • 1
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    Optimum exhaust velocity for laser-driven rockets (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The laser-driven rocket in which remotely generated laser power is used to heat propellant belongs basically to the class of specific-impulse limited propulsion systems if difficult missions are considered. It was previously established that trip time reaches a minimum as specific impulse is varied for payload transfers from low earth orbit to synchronous orbit and return via laser-driven rocket propulsion, the computations being based on the perigee-propulsion laser drive described by Minovitch (1972). The present study shows that such minimum occur for all missions and that optimum specific impulse is primarily determined by the mission difficulty. More generally, this optimum specific impulse maximizes payload kinetic energy achievable with a fixed jet power and propulsion time. A formula relating propulsion time parameter to payload ratio is obtained for estimating mission capabilities of laser-driven rockets.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets; 12; Nov. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A thrust-sheet propulsion concept using fissionable elements (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A space propulsion concept is proposed and analyzed which consists of a thin sheet coated on one side with fissionable material, so that nuclear power is converted directly into propulsive power. Thrust is available both from ejected fission fragments and from thermal radiation. Optimum thicknesses are determined for the active and substrate layers. This concept is shown to have potential mission capability (in terms of velocity increments) superior to that of all other advanced propulsion concepts for which performance estimates are available. A suitable spontaneously fissioning material such as Cf-254 could provide an extremely high-performance first stage beyond earth orbit. In contrast with some other advanced nuclear propulsion concepts, there is no minimum size below which this concept is infeasible.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 76-1042 , International Electric Propulsion Conference; Nov 14, 1976 - Nov 17, 1976; Key Biscayne, FL
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    A thrust-sheet propulsion concept using fissionable elements (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A space propulsion concept is proposed and analyzed which consists of a thin sheet coated on one side with fissionable material, so that nuclear power is converted directly into propulsive power. Thrust is available both from ejected fission fragments and from thermal radiation. Optimum thicknesses are determined for the active and substrate layers. This concept is shown to have potential mission capability (in terms of velocity increments) superior to that of all other advanced propulsion concepts for which performance estimates are available. A suitable spontaneously fissioning material such as Cf254 could provide an extremely high-performance first stage beyond earth orbit. In contrast with some other advanced nuclear propulsion concepts, there is no minimum size below which this concept is infeasible.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-X-73469 , Intern. Electric Propulsion Conf.; Nov 14, 1976 - Nov 17, 1976; Key Biscayne, FL; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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