Mar 082011

Not the best quality image (coming from microfilm), but this shows a NASA-Lewis concept for a gas core nuclear rocket engine, circa 1960. Specific impulse was to be 2200 seconds, thrust 98,000 pounds, T/W 0.68, reactor diameter 16.6 feet, overall reactor length, 16.6 feet. The fuel would reach 20,000 degrees R, while the Hydrogen would get to 10,000 degrees R.

 Posted by at 1:19 am
  • Michel Van

    interestingly, here the lettering FUEL and PROPELLANT last is hydrogene
    but how is Fuel (Uranium hexafluoride? ) handled:
    pump with trubopumps from fueltank into engine or pressure feed ?
    and who is fuel stored under control and cooled ?