There is need for smaller, faster, more frequent space science missions. Smaller spacecraft may enable such missions. Technology has been developed by the United States' Department of Defense and other government agencies that can enable smaller spacecraft. This author has developed a generic concept for utilizing advanced technology to create a microspacecraft. A microspacecraft would have a mass on the order of 10 kg. This paper will present this microspacecraft concept.

Jones, R. M.↗

NASA NTRS1988

Alfven propulsion at Jupiter

The operation of an electrodynamic tether at Jupiter is investigated. The pertinent Jupiter environments are investigated, and analytic expressions are derived for the induced electric field and the voltage, current, and force for an electrodynamic tether as a function of the radial distance from Jupiter. The formulas are combined with environmental models to arrive at quantitative values for the above parameters. The results are used to investigate propulsion applications.

Gabriel, S. B.↗

NASA NTRS1986

Reinforcement of composite laminate free edges with U-shaped caps

Generalized plane strain finite element analysis is used to predict reduction of interlaminar normal stresses when a U-shaped cap is bonded to the edge of a laminate. Three-dimensional composite material failure criteria are used in a progressive laminate failure analysis to predict failure loads of laminates with different edge cap designs. In an experimental program, symmetric 11-layer graphite-epoxy laminates with a one-layer cap of Kevlar-epoxy cloth are shown to be 130 to 140 percent stronger than uncapped laminates under static tensile and tension-tension fatigue loading. In addition, the coefficient of variation of the static tensile failure load decreases from 24 to 8 percent when edge caps are added. The predicted failure load calculated with the finite element results is 10 percent lower than the actual failure load. For both capped and uncapped laminates, actual failure loads are much lower than those predicted using classical lamination theory stresses and a two-dimensional failure criterion. Possible applications of the free edge reinforcement concept are described, and future research is suggested.

Howard, W. E.↗

NASA NTRS1985

Vertical reactor coolant pump instabilities

The investigation conducted at the Tennessee Valley Authority's Sequoyah Nuclear Power Plant to determine and correct increasing vibrations in the vertical reactor coolant pumps is described. Diagnostic procedures to determine the vibration causes and evaluate the corrective measures taken are also described.

Jones, R. M.↗

NASA NTRS1985

Power supplies for primary electric propulsion missions

Explore the source record for details and available documents.

Jones, R. M.↗

NASA NTRS1985

Composite laminate free edge reinforcement concepts

The presence of a free edge in a laminated composite structure can result in delamination of the composite under certain loading conditions. Linear finite element analysis predicts large or even singular interlaminar stresses near the free edge. Edge reinforcements which will reduce these interlaminar stresses, prevent or delay the onset of delaminations, and thereby increase the strength and life of the structure were studied. Finite element models are used to analyze reinforced laminates which were subsequently fabricated and loaded to failure in order to verify the analysis results.

Howard, W. E.↗

NASA NTRS1984

Nuclear electric propulsion missions

This paper reviews nuclear electric propulsion technology and missions. The science objectives and mission performance of the following five missions are presented: (1) Neptune orbiter, (2) Saturn ring rendezvous, (3) an asteroid sample return, (4) a comet sample return, and (5) an interstellar precursor mission. A short status of the reactor and thermal to electric conversion technologies is given as well as a brief discussion of ion thruster technology. A specific nuclear reactor power system concept is presented that produces 100 kWe and has a mass of about 2600 kg. Mission performance in terms of payload and flight time is presented for all five missions. Heliocentric trajectories are presented for the Neptune orbiter, Saturn ring rendezvous, and Comet Tempel 2 nucleus sample return missions.

Jones, R. M.↗

NASA NTRS1984

Comparison of potential electric propulsion systems for orbit transfer

Previously cited in issue 03, p. 283, Accession no. A83-14375

Jones, R. M.↗

NASA NTRS1984

Advanced solar electric propulsion (ASEP) for planetary missions

This paper defines an advanced SEP concept based upon demonstrated ion thruster technology improvements and projected improvements in solar array technology. The ASEP concept utilizes an 'integrated' rather than a 'stage' approach and assumes 30 cm Hg ion thrusters capable of operation near 7 kWe each. The mission performance using the ASEP system is presented for three missions: (1) Saturn orbiter, (2) comet rendezvous and (3) comet sample return. The ASEP system provides significant mission performance improvements. The simpler, fewer thruster ASEP system design may provide cost as well as performance benefits for the missions examined when compared to ballistic or SEP stage mission options.

Jones, R. M.↗

NASA NTRS1984

The status of power supplies for primary electric propulsion in the U.S.A.

This paper reviews the status of and requirements on solar electric and nuclear electric power supplies for primary electric propulsion missions. The power supply requirements of power level, specific mass (kg/kWe) and lifetime are defined as a function of the mission and electric propulsion system characteristics for planetary missions. The technology status of planar and concentrator arrays is discussed. Nuclear reactors and thermoelectric, thermionic, Brayton and Rankine conversion technologies are reviewed, as well as recent nuclear power system design concepts and program activity. Technology projections for power supplies applicable to primary electric propulsion missions are included.

Jones, R. M.↗

NASA NTRS1983

Should we make products on the moon?

It is pointed out that products from extraterrestrial materials can play a major role in future space operations within the useful lifetime of the first major space station, now in the planning stage. Possible economic advantages regarding the use of such products could be related to the recognition that it takes seven times more energy to get one kilogram from the earth's surface to low earth orbit (LEO) than it does to move one kilogram from the moon's surface to LEO. An analysis regarding the margin of advantage of extraterrestrial materials as been conducted, taking into account equipment and supplies which ust be launched from earth to make the acquisition of extraterrestrial products feasible. The present investigation is concerned with a study of engineering practicality. Attention is given to the transport of processing equipment from LEO to the lunar surface and of lunar products to LEO and the geosynchronous orbit. It is found that lunar oxygen and radiation shielding could possibly be utilized by the turn of the century.

Carroll, W. F.↗

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 NTRS1983

Space station orbit maintenance

The orbit maintenance problem is examined for two low-earth-orbiting space station concepts - the large, manned Space Operations Center (SOC) and the smaller, unmanned Science and Applications Space Platform (SASP). Atmospheric drag forces are calculated, and circular orbit altitudes are selected to assure a 90 day decay period in the event of catastrophic propulsion system failure. Several thrusting strategies for orbit maintenance are discussed. Various chemical and electric propulsion systems for orbit maintenance are compared on the basis of propellant resupply requirements, power requirements, Shuttle launch costs, and technology readiness.

Kaplan, D. I.↗

NASA NTRS1982

A comparison of potential electric propulsion systems for orbit transfer

Electric propulsion concepts are compared on the basis of trip time for the low earth orbit (LEO) to geosynchronous earth orbit (GEO) mission. Resistojet, arcjet, magnetoplasmadynamic (MPD), pulsed inductive, and ion engine thruster concepts are included. The optimum (minimum trip time) value of specific impulse is found to be dependent upon the specific mission and system being considered. As expected, the devices which can deliver good efficiency at low specific impulses promise the fastest trip times. The solution for trip time and propellant mass for the constant power, continuous low acceleration orbit transfer problem (one way and round trip) is presented in nomograph form. The influences of mission Delta V, thruster efficiency, specific impulse, power, power and propulsion system mass, and payload mass are clearly illustrated.

Jones, R. M.↗