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Results for “Nuclear-electric propulsion”

Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 55 records · Page 3
All sourcesNASA NTRSDOE OSTI
NASA NTRS1965

Space nuclear propulsion mid-decade.

Space propulsion systems including solid core nuclear rockets, electric propulsion thrustors and nuclear electric generators

ELECTRIC PROPULSION↗
NASA NTRS1961

Control and Guidance of Electrically Propelled Spacecraft

Some of the conditions and methods of control and guidance for a nuclear-electric spacecraft are discussed in general terms. The type of spacecraft considered is propelled by an ion motor. The broad aspects of the flight trajectory peculiar to this type of propulsion are examined. Some equipment limitations are reviewed.

NUCLEAR-ELECTRIC PROPULSION↗
NASA NTRS1983

An analysis of propulsion options for transport of lunar materials to earth orbit

This paper describes the results of analyses of space-based transportation systems for the transport of extraterrestrial materials from their point of origin on the lunar surface to final delivery point in earth orbit and transport of equipment and supplies for extraterrestrial processing to the operational site. The emphasis has been on the use of near-term (pre-year 2000) propulsion systems, such as advanced chemical (H2, O2) and nuclear-electric systems. More exotic systems (mass drivers, nuclear-thermal rockets, etc.) were also considered to evaluate the potential to be gained by use of post-year 2000 technologies. Finally, the effects of using extraterrestrial propellants (e.g., H2 from lunar polar water-ice for chemical systems) were compared to those of propulsion systems deriving all or part of their propellants from the earth.

Frisbee, R. H.↗
NASA NTRS1988

Parametric studies of electric propulsion systems for orbit transfer vehicles

The present parametric tradeoff study for OTV electric propulsion systems encompasses ammonia and hydrogen arcjets as well as Xe-ion propulsion systems with performance characteristics currently being projected for 1993 operation. In all cases, the power source is a nuclear-electric system with 30 kg/kW(e) specific mass, and the mission involves the movement of payloads from lower orbits to GEO. Attention is given to payload capabilities and associated propellant requirements. Mission trip time is identified as the key parameter for selection; while arcjets are preferable for shorter trip times, ion propulsion is more advantageous for longer trip times due to reduced propellant mass fraction.

Manvi, R.↗
NASA NTRS1986

A review of the multimegawatt MPD thruster and current mission applications

The magnetoplasmadynamic (MPD) thruster is potentially capable of providing 20-200 N of steady-state thrust, at 1000-20,000 s specific impulse while consuming a variety of propellants and megawatts of DC power. The specific impulse and power capacity put the MPD thruster in a class separate from other electric propulsion engines. Several types of missions are enhanced by the unique capabilities of a nuclear-electric driven MPD thruster and these include earth-orbit raising, cis-lunar transportation, and planetary exploration. This paper describes current MPD thruster technology, and several missions typical of the above cited categories.

King, D. Q.↗
NASA NTRS1973

Preliminary cost and mission value comparisons for planetary probes delivered by advanced propulsion systems

The three advanced propulsion systems analyzed are an advanced chemical system, an improved solid-core nuclear rocket engine with a 25-kilowatt auxiliary powerplant, and a nuclear-electric system. The comparison of these systems is made on the basis of transportation cost divided by the expected value of the data returned to earth. The analysis shows that for the Mercury Orbiter mission and for missions to the outer planets with a high data requirement, the nuclear-electric system emerges as the best system. For the Venus Orbiter mission, the advanced chemical propulsion system is best.

Hrach, F. J.↗
NASA NTRS1972

Planetary exploration with electrically propelled vehicles.

The characteristics of propulsion systems required for carrying out flight missions within the solar system, as desired by planetary physicists and astronomers, are reviewed. It is shown that an encouraging answer to these requirements is available in the form of electrostatic or ion propulsion systems. The design and performance characteristics of an electrostatic thrustor employing an ion source, accelerating electrode, beam neutralizer, and power source are discussed, together with those of the Kaufmann engine (electrostatic thrustor employing bombardment type ionization). More demanding missions which will become feasible with the advent of nuclear-electric power sources (such as the incore thermionic reactor) may include close orbiters around all the planets, and asteroid and cometary missions.

Stuhlinger, E.↗
NASA NTRS1966

Electric propulsion in 1965.

Electric propulsion in 1965, discussing electron bombardment and contact ionization thrustors, nuclear and solar-electric power systems, etc

ELECTRON BOMBARDMENT↗