ELECTRICAL PROPULSION CAPABILITIES FOR LUNAR EXPLORATION

Journal Article · Fri Feb 01 04:00:00 EST 1963 · AIAA (Am. Inst. Aeron. Astronaut.) J.

DOI:https://doi.org/10.2514/3.1529· OSTI ID:4704042

Brown, H; Nicoll, Jr, H E

The logical result of a successful Apollo program can be expected to be a large scale operation involving manned lunar exploration and colonization. The potential role of electrical propulsion in such an operation is examined. Primary emphasis is placed on the identification of mission capabilities for providing logistic support. Electrical engine and nuclear-mechanical power conversion system experience is projected to the 1 to 10 Mw range and used to identify expected system characteristics. Both thermal arc and ion engines are considered. A basic mission profile is defined, and typical trajectory characteristics are discussed. The low thrust characteristic velocity requirement for the basic mission is identified and used to generate parametric mission performance characteristics for one-way, round-trip, and multitrip missions. These data indicate the interrelations between gross weight, power rating, specific impulse, and total propulsion time and their effect on payload capabilities. The resulting data then are compared with the capabilities of comparable chemical and nuclear rocket-propelled vehicles. (auth)

• Research Organization: General Electric Co., Evendale, Ohio
• Sponsoring Organization: USDOE
• NSA Number: NSA-17-019692
• OSTI ID: 4704042
• Journal Information: AIAA (Am. Inst. Aeron. Astronaut.) J., Journal Name: AIAA (Am. Inst. Aeron. Astronaut.) J. Vol. Vol: 1
• Country of Publication: Country unknown/Code not available
• Language: English

Related Subjects

CHEMICALS
CONVERSION
ELECTRIC ARCS
ELECTRICITY
IONS
JETS
MAN
NESDPS Office of Nuclear Energy Space and Defense Power Systems
PAYLOAD
POWER
PROPULSION
REACTORS
ROCKETS
SPACE APPLICATIONS AND TECHNOLOGY
SPACE FLIGHT
VELOCITY
WEIGHT