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  • SPACE RADIATION  (97)
  • SPACE VEHICLES  (86)
  • 1970-1974  (178)
  • 1960-1964  (5)
  • 1972  (178)
  • 1961  (3)
  • 1960  (2)
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  • 1970-1974  (178)
  • 1960-1964  (5)
Year
  • 11
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    Search for antimatter in primary cosmic rays. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Data from two flights of a new superconducting magnetic spectrometer are reported. This instrument was capable of a direct matter-antimatter separation in the cosmic rays. Antimatter events would appear in the spectrometer as trajectories which curve in the opposite direction to common matter, because of their negative charge. A brief description of the equipment and of the characteristics of the instrument is presented, along with the data processing techniques used. A new upper limit on the amount of antimatter in primary cosmic rays has been established. The limits are considerably lower than those for any previous experiment.
    Keywords: SPACE RADIATION
    Type: Nature; 236; Apr. 14
    Format: text
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    NASA TECHNICAL REPORTS
  • 12
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    Origin of 200-keV interplanetary electrons. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The suggestion by Lin et al. (1972) that a distinct spectral feature exists at about 200 keV, which could be due to a neutron-decay electron component of either solar or galactic origin, is examined. Alternative sources models, including production by nearby galactic objects or acceleration at the outer boundary of the solar system, are also considered.
    Keywords: SPACE RADIATION
    Type: Physical Review Letters; 29; Oct. 9
    Format: text
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  • 13
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    The cosmic gamma-ray spectrum between 0.3 and 27 MeV measured on the Apollo 15 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The spectrum of the total (diffuse and discrete sources) cosmic gamma-ray background over the 0.3 to 27 MeV range was measured with a 7.0 cm diameter x 7.0 cm long uncollimated NaI(Tl) scintillation counter located on a boom 7.6 m from the Apollo 15 service module. Data on cosmic gamma-rays were taken during transearth coast at various boom extensions, detector gains, and with the plastic anticoincidence scintillator enabled and disabled.
    Keywords: SPACE RADIATION
    Type: NASA-TM-X-66104 , X-641-72-421
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    Forebody and vertical stabilizer effects on directional stability of a reusable LOX/RP (061) booster AR 12161-2 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are presented of a wind tunnel test on the directional stability of space shuttle booster configurations. The test was conducted at the 14-inch trisonic tunnel starting 6 December 1971 and continued through 11 December 1971 for a total of 66 occupancy hours. Configurations tested included a cylindrical body with two axisymmetrical noses, one with and without canopy, one delta wing, located in two positions, five vertical tails (including a V tail), two having split rudders, ventral fins, two sets of chines, three airbreathing engine pods, and rocket engine shrouds. The model scale was 0.003366.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120027 , DMS-DR-1209
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    Soft X-rays from the vicinity of the North Polar Spur. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Soft X rays in the energy regions below 284 eV and between 500 and 1000 eV have been detected on the vicinity of the North Polar Spur. The region of enhanced X-ray emission reported was observed from an Aerobee 150 rocket launched on May 29, 1970, from Woomera, Australia.
    Keywords: SPACE RADIATION
    Type: Astrophysical Journal; 172; Mar. 1
    Format: text
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  • 16
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    Solar-wind structure determined by corotating coronal inhomogeneities. II - Arbitrary perturbations. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The problem of the solar-wind structure resulting from long-lived inhomogeneities in the solar corona has been extended within the framework of a linearized hydrodynamic approach to allow for arbitrary perturbations in the plasma parameters, namely, velocity, density, and temperature. By using a Parker model for the zero-order flow speed, solutions are given for perturbations imposed at the zero-order critical point. Using the restriction that the solutions must be regular at the critical point, it is possible to express all situations as a linear sum of the solutions for pure velocity, density, and temperature perturbations at the critical point. The results of the integrations for three inner-boundary conditions can be used as the elements of matrices that map arbitrary perturbations at one heliocentric distance to any other distance. One interesting feature of the solutions is that the amplitudes at earth for the pure initial temperature situation are larger than for the other two situations.
    Keywords: SPACE RADIATION
    Type: Journal of Geophysical Research; 77; Jan. 1
    Format: text
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  • 17
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    Aerodynamic stability and control characteristics of TBC shuttle booster AR-11981-3 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A scale model of the Boeing Company space shuttle booster configuration 3 was tested in the MSFC 14-inch trisonic wind tunnel. This test was proposed to fill-in the original test run schedule as well as to investigate the aerodynamic stability and control characteristics of the booster with three wing configurations not previously tested. The configurations tested included: (1) a cylindrical booster body with an axisymmetric nose, (2) clipped delta canards that had variable incidence from 0 deg to -60 deg, (3) different aft body mounted wing configurations, (4) two vertical fin configurations, and (5) a Grumman G-3 orbiter configuration. Tests were conducted over a Mach range from 0.6 to 5.0.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120003 , DMS-DR-1160
    Format: application/pdf
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  • 18
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    Space shuttle: Aerodynamic characteristics of a composite booster/040A orbiter launch configuration with fin and booster body configuration effect contribution (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made of the fin configuration and booster body configuration effects on a composite booster/040A orbiter launch configuration. Aerodynamic performance and stability characteristics in pitch and yaw were obtained. Configurations tested included two stepped cylindrical bodies of different lengths with a conical nose, four fin shapes of various sizes and aspect ratios mounted in different positions around the base of the bodies, two base flare angles and three 040A orbiter configurations. The orbiter variations included a tailless configuration and two tail sizes. A tailless booster launch configuration with deflected petals (expanded flare sectors) was also tested. The model scale was 0.003366. Data were converted to coefficient form in near real time, punched on cards, and tabulated. The cards used in conjunction with a Benson-Lehner plotter were used to provide plotted data. At the end of the test, tabulated input forms were completed for the SADSAC computer program to aid in publishing the final test data report.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120039 , DMS-DR-1227
    Format: application/pdf
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  • 19
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    Thermal-structural combined loads design criteria study (1972)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A study was conducted to determine methodology for combining thermal structural loads and assessing the effects of the combined loads on the design of a thermal protection system and a hot structure of a high cross range delta wing space shuttle orbiter vehicle. The study presents guidelines for establishing a basis for predicting thermal and pressure environments and for determining limit and ultimate design loads on the vehicle during reentry. Limit trajectories were determined by using dispersions on a representative nominal mission and system parameters expected during the life of the vehicle. Nine chosen locations on the vehicle surface having TPS or hot structures were examined, and weight sensitivity analyses were performed for each location.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-2102 , D180-14647-1
    Format: application/pdf
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  • 20
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    Experimental evaluation of the Skylab orbital workshop ventilation system concept (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Extensive testing was conducted to evaluate the Orbital Workshop ventilation concept. Component tests were utilized to determine the relationship between operating characteristics at 1 and 0.34 atm. System tests were conducted at 1 atm within the Orbital Workshop full-scale mockup to assess delivered volumetric flow rate and compartment air velocities. Component tests with the Anemostat circular diffusers (plenum- and duct-mounted) demonstrated that the diffuser produced essentially equivalent airflow patterns and velocities in 1- and 0.34-atm environments. The tests also showed that the pressure drop across the diffuser could be scaled from 1 to 0.34 atm using the atmosphere pressure ratio. Fan tests indicated that the performance of a multiple, parallel-mounted fan cluster could be predicted by summing the single-fan flow rates at a given delta P.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64700
    Format: application/pdf
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