Evaluation of isotope propulsion engines with regard to design concepts and performance limitations; direct-heating devices, in which propellant is heated in radioisotope core, and direct-momentum devices, in which escaping particles impart thrust, are considered; since direct-heating devices must reject excess heat during off periods, self-cooled designs or designs integrated with power units are suggested; probable applications may be in orbit changes and satellite control; direct momentum devices are limited to low thrusts and low thrust-to-weight ratios by particle self-absorption, particle isotropy, radiation hazards, and charge neutralization.
Radioisotope propulsion
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 1 , n 5
1964
7 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Springer Verlag | 1968
|AIAA | 1964
|POODLE radioisotope propulsion technology.
NTRS | 1966
|Potentials of Radioisotope Electrostatic Propulsion
NTRS | 1963
|POTENTIALS OF RADIOISOTOPE ELECTROSTATIC PROPULSION
NTRS | 1963
|