A PRELIMINARY STUDY OF THERMONUCLEAR ROCKET PROPULSION

Journal Article · Mon May 01 04:00:00 EDT 1961 · J. Brit. Interplanet. Soc.

OSTI ID:4843804

Roth, J R

The feasibility of applying controlled thermonuclear power to rocket propulsion is investigated. Such application is shown to be possible within the existing framework of knowledge of thermonuclear processes. The limiting values of reaction temperature, particle density, plasma volume, and power output are derived from theoretical and practical considerations. Relationships are derived which predict the size, mass, thrust, specific impulse, and mass flow of thermonuclear rocket engines. All parameters of interest are calculated for two hypothetical thermonuclear rocket engines, the smaller of which operates near the minimum practical power output, and the larger of which operates at the maximum practicable power density. It is shown that thermonuclear rockets cannot operate in a planetary atmosphere, and that their thrust-to-mass ratio must necessarily be of the order of 10/sup -4/. The advantages and limitations of thermonuclear rocket propulsion are discussed, and it is examined as a possible means of interstellar flight. (auth)

• Research Organization: Cornell Univ., Ithaca, N.Y.
• NSA Number: NSA-15-027270
• OSTI ID: 4843804
• Journal Information: J. Brit. Interplanet. Soc., Journal Name: J. Brit. Interplanet. Soc. Vol. Vol: 18
• Country of Publication: Country unknown/Code not available
• Language: English

Related Subjects

ATMOSPHERE
DENSITY
GENERAL AND MISCELLANEOUS
OPERATION
PARTICLES
PLASMA
POWER
PROPULSION
ROCKETS
SPACE FLIGHT
TEMPERATURE
THERMONUCLEAR REACTIONS