MECHANISTIC MODELING PREDICTS NO SIGNIFICANT DOSE RATE EFFECT ON HEAVY-ION CARCINOGENESIS AT DOSE RATES RELEVANT FOR SPACE EXPLORATION
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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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NASA activities - Ranger VII moonflight, Apollo lunar landing and Nimbus weather satellite
Use of fission and isotopic fuels for nuclear advanced spacecraft propulsion
Contamination probability distribution models for spacecraft - microbiological assays and sterilization of spacecraft components
IR spectrometers, radiometers, horizon sensors, rotating-prism planet-seekers and detector cooling using solid cryogens, for use in high altitude rockets and Earth satellites
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Scientific objectives for Lunar Exploration Systems for Apollo, noting compatibility with geoscience operation and radiation investigation
Gravity gradient phenomena in orbiting vehicle to explore planetary gravity
Statistical models for spacecraft sterilization and microbial growths
Tracking and data acquisition system between spacecraft and ground station
Tracking and data acquisition systems for spacecraft and ground link through command, telemetry and tracking, noting data relay satellites, etc
Etiology, symptomatology, and treatment of motion sickness with respect to vestibular organ and related neurological functions
Optimized silicon solar cell development for spacecraft with near-sun missions
Statistical procedures for investigating decontamination of spacecraft and microbial assays
Pioneer 6-9 low magnetism spacecraft for interplanetary magnetic field observation
A program is described aimed at designing and fabricating improved silicon solar cells for a range of missions extending from 0.1 to 15 astronomical units (Mercury to Jupiter). For missions lying inside Earth radius (Mercury, Venus) the major cell property required was very low series resistance, allowing high curve fill factor to be maintained at the higher intensities. For the Mercury mission, the temperature of the cell had to be kept low. This was achieved by reflecting more of the incident sunlight by use of large area front contacts. For the outer missions (Mars, the Asteroid belts and Jupiter) the formation of a Schottky barrier at the back contact had to be avoided (by use of a P+ layer under the back contact) and the excess leakage current of the PN junction had to be reduced. Optimum grid patterns were also derived and used for these missions.
For abstract, see N74-20534. For complete abstract, see .