Pulsed thermionic converter study. Final report. [Space nuclear electric propulsion]

Technical Report · Thu Apr 01 00:00:00 EST 1976

OSTI ID:7220307

A nuclear electric propulsion concept using a thermionic reactor inductively coupled to a magnetoplasmadynamic accelerator (MPD arc jet) is described, and the results of preliminary analyses are presented. In this system, the MPD thruster operates intermittently at higher voltages and power levels than the thermionic generating unit. A typical thrust pulse from the MPD arc jet is characterized by power levels of 1 to 4 MWe, a duration of 1 msec, and a duty cycle of approximately 20%. The thermionic generating unit operates continuously but with a lower power level of approximately 0.4 MWe. Energy storage between thrust pulses is provided by building up a large current in an inductor using the output of the thermionic converter array. Periodically, the charging current is interrupted, and the energy stored in the magnetic field of the inductor is utilized for a short duration thrust pulse. The results of the preliminary analysis show that a coupling effectiveness of approximately 85 to 90% is feasible for a nominal 400 KWe system with an inductive unit suitable for a flight vehicle. (Author)

• Research Organization: Rasor Associates, Inc., Sunnyvale, CA (USA)
• DOE Contract Number: NAS7-100; JPL-954219
• OSTI ID: 7220307
• Report Number(s): N-77-12123; NASA-CR-149234
• Country of Publication: United States
• Language: English

Related Subjects

21 SPECIFIC NUCLEAR REACTORS AND ASSOCIATED PLANTS
ION PROPULSION
SPACE PROPULSION REACTORS
THERMIONIC REACTORS
MHD GENERATORS
PLASMA JETS
PULSES
DIRECT ENERGY CONVERTERS
MOBILE REACTORS
POWER REACTORS
PROPULSION
PROPULSION REACTORS
REACTORS
SPACE POWER REACTORS
NESDPS Office of Nuclear Energy Space and Defense Power Systems
210600* - Power Reactors
Auxiliary
Mobile Package
& Transportable