THE significant design parameters of an ion-propellant rocket engine are developed in terms of three independent parameters. These are: the ratio of the acceleration voltage to atomic or molecular weight of the propellant, gross weight of the vehicle, and thrust-to-weight ratio.Engineering trends are presented which will lead toward advanced study of ion thrust chambers, power generation systems, and propellants.This paper received the 1958 Manley Memorial Award.
The ION ROCKET ENGINE
Sae Technical Papers
Pre-1964 SAE Technical Papers ; 1906
1959-01-01
Aufsatz (Konferenz)
Englisch
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