Reactor thrust during boost in a high altitude trajectory Metadata

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  • Main Title Reactor thrust during boost in a high altitude trajectory


  • Author: Moyer, J.H.
    Creator Type: Personal


  • Sponsor: United States. Department of Energy.
    Contributor Type: Organization
    Contributor Info: USDOE, Washington, DC (United States)


  • Name: Lawrence Livermore National Laboratory
    Place of Publication: California
    Additional Info: Lawrence Livermore National Lab., CA (United States)


  • Creation: 1962-11-12


  • English


  • Content Description: Reactor startup of a submarine based missile must be accomplished during boost., so that at burnout the reactor maximum wall temperature is at or near the design value. Because cooling air must be supplied during this period, there exists the possibility of obtaining some thrust to augment the booster. To find how much reactor thrust might be available, a representative high altitude boost trajectory was selected. This is shown together with an estimated pressure recovery curve for the inlet. It has been assumed that by some appropriate means the flow rate passed by the inlet exactly matches that demanded by the reactor and nozzle. Hot day conditions are assumed. The missile power plant was the Tory II-C reactor with its design point-optimized nozzle throat area of 750 square inches. Nozzle expansion is complete. The reactor maximum wall temperature was assumed to be constant at design (2500 degrees F) from time zero. Thus the thrust computed at any time is the maximum possible within the reactor design temperature limitation, and provides a guide to a desirable startup time. Available thrust and reactor exit conditions were obtained with the digital codes Dash N and Nomac.
  • Physical Description: 9 p.


  • Keyword: Reactor Start-Up
  • Keyword: Missiles
  • STI Subject Categories: 21 Nuclear Power Reactors And Associated Plants
  • Keyword: Power Distribution
  • Keyword: Temperature Distribution
  • Keyword: Power Density
  • Keyword: D Codes
  • Keyword: Propulsion Systems
  • Keyword: Design
  • Keyword: Computer Calculations
  • Keyword: Submarines
  • Keyword: Thrusters
  • Keyword: Air Flow
  • Keyword: Limiting Values
  • Keyword: N Codes
  • Keyword: Flow Rate
  • Keyword: Nozzles
  • Keyword: Propulsion Reactors
  • Keyword: Launching
  • STI Subject Categories: 45 Military Technology, Weaponry, And National Defense


  • Other Information: DN: Declassified


  • Name: Office of Scientific & Technical Information Technical Reports
    Code: OSTI


  • Name: UNT Libraries Government Documents Department
    Code: UNTGD

Resource Type

  • Report


  • Text


  • Other: DE97050857
  • Report No.: UCRL-ID--125505
  • Grant Number: W-7405-ENG-48
  • Office of Scientific & Technical Information Report Number: 446034
  • Archival Resource Key: ark:/67531/metadc675032


  • Display Note: OSTI as DE97050857