A thermonuclear propulsion stage intended to ensure the transfer and injection into geosynchronous equatorial orbit of a space vehicle initially placed in low orbit by the Europa 3 launch vehicle is discussed. The propulsion system would consist of an orthocylindrical core of minimum specific mass comprised of a bed of porous spherules, with a specific impulse between 800 and 820 sec. The fuel will be uranium monocarbide, which would heat cold hydrogen to high temperature prior to its discharge as the propellant. A suitable configuration is described, and operating procedures are outlined. (Author)
On the Utilization of Thermonuclear Propulsion for an Upper Stage of the Europa 3 Launcher
1973
23 pages
Report
No indication
English
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