AN ELECTROSTATIC PROPULSION SYSTEM WITH A DIRECT NUCLEAR ELECTROGENERATOR

Journal Article · Sat Dec 01 04:00:00 EST 1962 · Aerospace Eng.

OSTI ID:4751685

Low, Jr, C A; Mickelsen, W R

A preliminary study is presented to establish the theoretical feasibility of the direct nuclear electrostatic propulsion system and to provide an estimate of the possible mass/power ratio of an overall system. The general theory behind the direct nuclear electrogenerator and propulsion system is presented and various radioisotopes are evaluated for their suitability for space propulsion power. Electrogenerator cell design and energy losses are discussed. lwo exampies of 500 kw electrogenerator and propulsion system designs are examined in detail, one using Po-210 and the other Ce-Pr-144 as power source. Vehicle system performance is predicted for various mis, sions using these two systems and a 500 kw Th-228 system. It is concluded that for certain applications the radioisotope direct electrogenerator and colloidal ion rocket system has possibilities of superior performance. This system is theoretically capable of making very fast interplanetary flights with greater payloads than other electric propulsion systems currently proposed or under development. (H.D.R.)

• Research Organization: National Aeronautics and Space Administration, Cleveland
• NSA Number: NSA-17-005645
• OSTI ID: 4751685
• Journal Information: Aerospace Eng., Journal Name: Aerospace Eng. Vol. Vol: 21: No. 12
• Country of Publication: Country unknown/Code not available
• Language: English

Related Subjects

CERIUM 144
COLLOIDS
ELECTRICITY
HEATING
LOSSES
MAGNETOHYDRODYNAMICS
PAYLOAD
PLANETS
PLANNING
POLONIUM 210
POWER
PRASEODYMIUM 144
PROPULSION
RADIOISOTOPES
ROCKETS
SPACE APPLICATIONS AND TECHNOLOGY
SPACE FLIGHT
THERMIONICS
THERMOELECTRIC CELLS
THORIUM 228
USES
VELOCITY
WEIGHT