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  • 1
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    Simulation study of a method for analyzing wide field of view radiometer measurements from satellites and some analysis of ESSA 7 data (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Method of relating wide field of view radiometer measurements from satellites to the Earth longwave flux field is simulated and is used to obtain zonal and global averages of longwave (LW) flux for ESSA 7.
    Keywords: METEOROLOGY AND CLIMATOLOGY
    Type: NASA. Goddard Space Flight Center 3d NASA Weather and Climate Program Sci. Rev.; p 305-309
    Format: text
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  • 2
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    Mars sample return through parking orbit (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A Mars surface sample return mission using Mars direct entry and Mars parking orbit return is described. The mission is designed for a minimum energy requirement and is relatively simple in comparison to the alternative Mars orbital rendezvous mode. The design calls for minimal science, and uses a single Titan IIIE/Centaur launch vehicle. The primary science areas included are biology, biochemistry, geochemistry, and petrology, for detecting life, age dating, and determining chemical compositions and rock types. The total minimum sample requirement would be 30 g. Sampling conditions and recommended measurements are discussed. Maximum use of hardware and experience from the Mariner, Pioneer, and Viking missions is contemplated. The profile for a 1979 conjunction-class mission would include a total time of 1025 days, including one year in Mars parking orbit after sampling. The lander structure, components, and recovery alternatives are explained.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Astronautics and Aeronautics; 13; Jan. 197
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  • 3
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    Multiple-orifice liquid injection into hypersonic air streams. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Review of oblique water and fluorocarbon injection test results obtained in experimental studies of the effects of multiple-orifice liquid injection into hypersonic air streams. The results include the finding that maximum lateral penetration from such injections increases linearly with the square root of the jet-to-freestream dynamic-pressure ratio and is proportional to an equivalent orifice diameter.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Dec. 197
    Format: text
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  • 4
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    Mars surface-to-orbit vehicles for sample return missions (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Review of the results of a Mars surface-to-orbit launch vehicle study using an upgraded atmospheric density profile and an ascent trajectory optimization program. Orbit insertion was achieved with velocity losses less than those found in an earlier study. Values of thrust-to-mass ratio which minimize velocity losses for dual-burn vehicles were found to be significantly greater than the values of thrust-to-launch-mass ratio for the minimum-velocity-loss continuous-burn vehicle. The use of a two-stage solid-propellant vehicle employing a spin-stabilized second stage offers an attractive design option for a Mars surface-to-orbit launch vehicle.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 11; June 197
    Format: text
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  • 5
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    Simulation study of geometric shape factor approach to estimating earth emitted flux densities from wide field-of-view radiation measurements (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A study was performed on the use of geometric shape factors to estimate earth-emitted flux densities from radiation measurements with wide field-of-view flat-plate radiometers on satellites. Sets of simulated irradiance measurements were computed for unrestricted and restricted field-of-view detectors. In these simulations, the earth radiation field was modeled using data from Nimbus 2 and 3. Geometric shape factors were derived and applied to these data to estimate flux densities on global and zonal scales. For measurements at a satellite altitude of 600 km, estimates of zonal flux density were in error 1.0 to 1.2%, and global flux density errors were less than 0.2%. Estimates with unrestricted field-of-view detectors were about the same for Lambertian and non-Lambertian radiation models, but were affected by satellite altitude. The opposite was found for the restricted field-of-view detectors.
    Keywords: GEOPHYSICS
    Type: Remote Sensing of Environment; 9; May 1980
    Format: text
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  • 6
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    Failure of the ERBE scanner instrument aboard NOAA 10 spacecraft and results of failure analysis (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Earth Radiation Budget Experiment (ERBE) scanner instrument on the NOAA 10 spacecraft malfunctioned on May 22, 1989, after more than 4 years of in-flight operation. After the failure, all instrument operational mode commands were tested and the resulting data analyzed. Details of the tests and analysis of output data are discussed therein. The radiometric and housekeeping data appear to be valid. However, the instrument will not correctly execute operational scan mode commands or the preprogrammed calibration sequences. The data indicate the problem is the result of a failure in the internal address decoding circuity in one of the ROM (read only memory) chips of the instrument computer.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-102661 , NAS 1.15:102661
    Format: application/pdf
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  • 7
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    Simulation study of a geometric shape factor technique for estimating earth-emitted radiant flux densities from wide-field-of-view radiation measurements (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Geometric shape factors were computed and applied to satellite simulated irradiance measurements to estimate Earth emitted flux densities for global and zonal scales and for areas smaller than the detector field of view (FOV). Wide field of view flat plate detectors were emphasized, but spherical detectors were also studied. The radiation field was modeled after data from the Nimbus 2 and 3 satellites. At a satellite altitude of 600 km, zonal estimates were in error 1.0 to 1.2 percent and global estimates were in error less than 0.2 percent. Estimates with unrestricted field of view (UFOV) detectors were about the same for Lambertian and limb darkening radiation models. The opposite was found for restricted field of view detectors. The UFOV detectors are found to be poor estimators of flux density from the total FOV and are shown to be much better as estimators of flux density from a circle centered at the FOV with an area significantly smaller than that for the total FOV.
    Keywords: METEOROLOGY AND CLIMATOLOGY
    Type: NASA-TP-1629 , L-13373
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  • 8
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    Entry trajectory, entry environment, and analysis of spacecraft motion for the RAM C-3 flight experiment (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The RAM C-3 flight experiment was launched to study the problem of radiofrequency blackout at an entry velocity of 24,300 ft/sec. The flight is described, and data for the entry trajectory and environment, which include the effects of actual temperature measured the day of launch, are presented. An analysis of entry spacecraft motions was performed. This analysis included the determination of wind angles from measured accelerations and estimates of wind angles at high altitudes from gyro-measured rotation rates. The maximum wind angles were found to be less than 5 deg to the point of pitch-roll resonance where the total wind angle increased to 8.5 deg and the roll rate started decreasing. A plausible cause for the decrease in roll rate was shown to be a combination of trim angle and an offset center of gravity.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-2562 , L-8181
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  • 9
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    Automated Mars surface sample return mission concepts for achievement of essential scientific objectives (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Mission concepts were investigated for automated return to Earth of a Mars surface sample adequate for detailed analyses in scientific laboratories. The minimum sample mass sufficient to meet scientific requirements was determined. Types of materials and supporting measurements for essential analyses are reported. A baseline trajectory profile was selected for its low energy requirements and relatively simple implementation, and trajectory profile design data were developed for 1979 and 1981 launch opportunities. Efficient spacecraft systems were conceived by utilizing existing technology where possible. Systems concepts emphasized the 1979 launch opportunity, and the applicability of results to other opportunities was assessed. It was shown that the baseline missions (return through Mars parking orbit) and some comparison missions (return after sample transfer in Mars orbit) can be accomplished by using a single Titan III E/Centaur as the launch vehicle. All missions investigated can be accomplished by use of Space Shuttle/Centaur vehicles.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TM-X-3184 , L-9847
    Format: application/pdf
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  • 10
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    Multiple-orifice liquid injection into hypersonic airstreams and applications to ram C-3 flight (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental data are presented for the oblique injection of water and three electrophilic liquids (fluorocarbon compounds) through multiple-orifice nozzles from a flat plate and the sides of a hemisphere-cone (0.375 scale of RAM C spacecraft) into hypersonic airstreams. The nozzle patterns included single and multiple orifices, single rows of nozzles, and duplicates of the RAM C-III nozzles. The flat-plate tests were made at Mach 8. Total pressure was varied from 3.45 MN/m2 to 10.34 MN/m2, Reynolds number was varied form 9,840,000 per meter to 19,700,000 per meter, and liquid injection pressure was varied from 0.69 MN/m2 to 3.5 MN/m2. The hemisphere-cone tests were made at Mach 7.3. Total pressure was varied from 1.38 MN/m2, to 6.89 MN/m2, Reynolds number was varied from 3,540,000 per meter to 17,700,000 per meter, and liquid-injection pressure was varied from 0.34 MN/m2 to 4.14 MN/m2. Photographs of the tests and plots of liquid-penetration and spray cross-section area are presented. Maximum penetration was found to vary as the square root of the dynamic-pressure ratio and the square root of the total injection nozzle area. Spray cross-section area was linear with maximum penetration. The test results are used to compute injection parameters for the RAM C-3 flight injection experiment.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2486 , L-8023
    Format: application/pdf
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