Description of the design and testing of two distinct thrustor concepts which use ammonia propellant and have a specific impulse as high as 310 sec during pulsed operation. Considerations of thrustor design, material selection, and system testing are discussed in the light of performance, lifetime, and nuclear safety requirements. Results of a detailed study of the advantages and disadvantages of the use of such a thrustor are presented.
Development of a radioisotope-fueled thruster for satellite propulsion.
Joint Propulsion Specialist Conference ; 1972 ; New Orleans, LA, US
1972-11-01
Conference paper
No indication
English
Springer Verlag | 1968
|AIAA | 1964
|Engineering Index Backfile | 1964
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