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On the Utilization of Thermonuclear Propulsion for an Upper Stage of the Europa 3 Launcher.

N7322623

Publication Date	1973
Personal Author	Blanc, P.
Page Count	22
Abstract	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)
Keywords	Europa 3 launch vehicle Nuclear propulsion Propulsion system configurations Equatorial orbits Propulsion system performance Translations
Source Agency	National Aeronautics and Space Administration
NTIS Subject Category	81J - Reciprocation & Rotating Combustion Engines
Corporate Authors	Scientific Translation Service, Santa Barbara, Calif.
Supplemental Notes	Tran- Transl. Into English of Sur Lutilisation de La Propulsion Nucleo-thermique pour Un Etage Superieur Du Lanceur Europa 3, Papper Presented At Intern. Astronaut. Congr., 23d, Veinna, 8-15 Oct. 1972 Vienna, Intern. Astronaut. Federation, 1972 22 P
Document Type	Technical Report
NTIS Issue Number	197315
Contract Number	NASW-2483

On the Utilization of Thermonuclear Propulsion for an Upper Stage of the Europa 3 Launcher.

On the Utilization of Thermonuclear Propulsion for an Upper Stage of the Europa 3 Launcher.
N7322623

Publication Date	1973
Personal Author	Blanc, P.
Page Count	22
Abstract	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)
Keywords	Europa 3 launch vehicle Nuclear propulsion Propulsion system configurations Equatorial orbits Propulsion system performance Translations
Source Agency	National Aeronautics and Space Administration
NTIS Subject Category	81J - Reciprocation & Rotating Combustion Engines
Corporate Authors	Scientific Translation Service, Santa Barbara, Calif.
Supplemental Notes	Tran- Transl. Into English of Sur Lutilisation de La Propulsion Nucleo-thermique pour Un Etage Superieur Du Lanceur Europa 3, Papper Presented At Intern. Astronaut. Congr., 23d, Veinna, 8-15 Oct. 1972 Vienna, Intern. Astronaut. Federation, 1972 22 P
Document Type	Technical Report
NTIS Issue Number	197315
Contract Number	NASW-2483