Operating characteristics and requirements for the NERVA flight engine

Author:

ALTSEIMER J.1,MADER G.1,STEWART J.1

Affiliation:

1. AEROJET NUCLEAR SYSTEMS CO., SACRAMENTO, CALIF.

Publisher

American Institute of Aeronautics and Astronautics

Reference4 articles.

1. Figure 2 - Nuclear-Vehicle Configuration Delivered

2. u @ 7%*rev. 6"LL CLOYFLICUI C*DIU< Figure 3 - Nuclear-Vehicle Configured for LIlnar

3. pro ellant is also conserved during shdtdown by throttfing the thrust to the throttle point before ramping down the temperature. More importantly, a short hold (1-3 minutes) at the throttle point during shutdown results in a reduction in propellant consumption far delayed neutron power and fissionproduct decay heat absorption.

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3. Fusion Energy in Space Propulsion;1995-01-01

4. Innovative Technology for an Inertial Electrostatic Confinement (IEC) Fusion Propulsion Unit;Fusion Energy in Space Propulsion;1995-01-01

5. Author Index;Fusion Energy in Space Propulsion;1995-01-01

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