SELECTION OF POWER REQUIREMENTS FOR NUCLEAR-ELECTRIC SPACECRAFT MISSIONS

Technical Report · Wed May 24 04:00:00 EDT 1961

OSTI ID:4035994

Davis, J P

A method is presented for bracketing propulsion power requirements for spacecraft missioms consistent with specific launch vehicle boost constraints and anticipated stateof-the-art reactor-conversion system development. A Mars orbiter mission is taken as an illustrative example of the basic approach. Having selected launch vehicle, payload, and flight time, the distribution of powerplant and propellant weight is discussed. Curves are presented which indicate the minimum power requirement for the mission, the power range which affords maximum powerplant design flexibility, and the powerplant specific weights which must be attained to accomplish the mission. The interplay between mission requirements and powerplant development is indicated. An indication is given that a nuclear electric plant in the power range of 100 kw(e) propulsion at a specific weight in the range of 35 lb/kw(e) can accomplish a useful Mars orbiter mission in a reasonable flight time and delivering a useful scientific payload. Data are presented for two Jupiter missions. (auth)

• Research Organization: California Inst. of Tech., Pasadena. Jet Propulsion Lab.
• NSA Number: NSA-15-023163
• OSTI ID: 4035994
• Report Number(s): JPL-TR-32-114
• Country of Publication: United States
• Language: English

Related Subjects

ELECTRICITY
GENERAL AND MISCELLANEOUS
JUPITER
MARS PLANET
ORBITS
PAYLOAD
PLANETS
PROPULSION
REACTORS
SPACE FLIGHT
SPACE VEHICLES