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  • Other Sources  (13)
  • SPACE SCIENCES  (7)
  • SPACE VEHICLES  (6)
  • Life and Medical Sciences
  • 1980-1984
  • 1970-1974  (13)
  • 1
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    Surface electrical properties experiment (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The surface electrical properties (SEP) experiment was used to explore the subsurface material of the Apollo 17 landing site by means of electromagnetic radiation. The experiment was designed to detect electrical layering, discrete scattering bodies, and the possible presence of water. From the analysis of the data, it was expected that values of the electrical properties (dielectric constant and loss tangent) of lunar material in situ would be obtained. The basic principle of the SEP experiment is interferometry. This principle involves only the interference of two or more waves to produce an interference pattern. The inversion of the interference pattern in terms of the spatial distribution of the electrical properties is the basic aim of the experiment (fig. 15-1). The experiment is most easily understood in terms of a single dipole antenna for radiating electromagnetic energy and a loop receiver for measuring the magnitudes of the fields.
    Keywords: SPACE SCIENCES
    Type: NASA. Johnson Space Center Apollo 17 Prelim. Sci. Rept.; 14 p
    Format: text
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  • 2
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    Abort separation of the shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A sensitivity analysis of the factors which affect a successful abort maneuver following a space shuttle launching is presented. Wind tunnel tests were conducted using optimum simulation techniques and data acquisition procedures. Static stability, dynamic stability, and local loads were investigated. It is concluded that parallel abort separation of the space shuttle components is possible at both high and low dynamic pressures. Successful separation is dependent upon configuration, Mach number, rocket exhaust impingement and relative position and attitude of the stages.
    Keywords: SPACE SCIENCES
    Type: Space Shuttle Aerothermodyn. Tech. Conf., vol. 4 p1105-1164 (SEE N72-20880 11-31)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Heat transfer distributions on the LMSC 040C and 040A-L4 delta wing orbiters (M equals 8)7 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a wind tunnel investigation are presented for measuring aerodynamic heat transfer distributions on the 040C and 040A-L4 space shuttle orbiter configurations. Heat transfer rates were determined by the phase change coating technique, using 0.012-scale Stycast models coated with Tempilaq. Data were obtained at a nominal free stream Mach number of 8, Reynolds numbers from 1.0 to 3.8 million per foot, and angles of attack from 20 to 60 deg.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120072 , DMS-DR-1266
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aerodynamic stability and drag characteristics of the MSFC pressure fed booster configurations at Mach numbers from 0.9 to5.0 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted in the NASA/MSFC 14 x 14 Inch Trisonic Wind Tunnel during January 1972 on 0.003366 and 0.00419 scale models of the MSFC space shuttle pressure fed booster configurations. The configurations tested were a 40 deg cone/cylinder/13 deg flare with and without fins, a 40 deg cone/cylinder/13 deg flare/9 deg flare with and without fins, a 35 deg cone/cylinder with and without fins, a 35 deg cone/cylinder/7 deg flare and a 35 deg cone/cylinder with straight extension. Six component aerodynamic force and moment data were recorded over a Mach number range of 0.9 to 5.0. Model angle of attack range was -10 to +10 deg and +20 to 80 at 0 deg sideslip. Model sideslip range was -10 to +10 deg at nominal angles of attack of 0, 30 and 51 deg
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120038 , DMS-DR-1226
    Format: application/pdf
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  • 5
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    Calibration of propulsion simulation nozzles for space shuttle booster and orbiter models for the abort/separation staging experimental program (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental program to determine the power-on aerodynamic flight characteristics of the booster and orbiter vehicles during the abort separation maneuver is reported. An essential contribution to such a test program is the gas dynamic simulation of the size and shape of the plumes emitting from the full-scale orbiter and booster main propulsion systems. The two major effects of the plume which must be simulated are: the interaction of the plume with the external flow field, and the direct impingement of the plumes on surfaces which are enveloped by the plume. To accomplish the objective of correct plume simulation, the similarity parameters developed by Herron and the requirement to match momentum flux per unit area between the model and the full-scale systems, were applied to the orbiter and booster propulsion systems.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-124217 , TM-54/20-320 , LMSC/HREC-D225144
    Format: application/pdf
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  • 6
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    Research related to measurements of atomic species in the earth's upper atmosphere Final report (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Interaction kinetics of atomic oxygen and hydrogen on metal surfaces of satellite-borne mass spectrometers
    Keywords: SPACE SCIENCES
    Type: NASA-CR-111117
    Format: application/pdf
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  • 7
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    Aerodynamic characteristics of the MSFC pressure fed boosters at high angles of attack (M equals 0.6 to 5.0) (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted in the 14 x 14 inch trisonic wind tunnel during early December 1971 on 0.003366 scale models of the space shuttle pressure fed booster configurations. The basic configurations tested were a 40 deg cone/cylinder/13 deg flare designated the pressure fed booster and a 35 deg cone/cylinder designated the pressure fed booster configuration x. Six component aerodynamic force and moment data were recorded over a Mach number range from 0.6 to 5.0 at angles of attack from +20 to +60 deg at 0 deg sideslip and over a sideslip range from -10 to +10 deg at 31 and 52 deg angles of attack. Primary configuration variables for the two basic pressure fed booster configurations were fin size and fin dihedral position.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120026 , DMS-DR-1208
    Format: application/pdf
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  • 8
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    Design of an inert fluid injection system, phase 3 Final report (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Research, development, and design of velocity trim system for third stage of Delta launch vehicle
    Keywords: SPACE VEHICLES
    Type: NASA-CR-118488 , LMSC/HREC-D162662 , HREC-1614-4
    Format: application/pdf
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  • 9
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    Simple method of using onboard optical measurements to predict the orbit established after the lunar-ascent-transfer orbit (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Onboard optical measurements of angles for orbit prediction established after lunar-ascent and transfer orbits
    Keywords: SPACE SCIENCES
    Type: NASA-TN-D-5618 , L-6680
    Format: application/pdf
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  • 10
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    The magnetosphere of Jupiter as observed with Pioneer 10. I - Instrument and principal findings (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Description of the first in situ observations of energetic electrons of energy greater than 0.06 MeV in the magnetosphere of Jupiter during November-December 1973. The outer magnetosphere has the form of a thin disklike quasi-trapping region extending from about 20 to over 100 Jovian radii. This magnetodisk is confined near the magnetic equatorial plane and has approximate axial symmetry about the magnetic axis of the planet. The observations inside a radial distance of 12 Jovian radii are well organized by a centered dipolar model of the planet's magnetic field with a tilt of 9.5 plus or minus 0.5 deg to the rotational axis and with pole at a system III longitude of 230 plus or minus 3 deg. Absolute omnidirectional intensities of electrons within the stable trapping region inside 20 Jovian radii are given for five energy ranges greater than 0.06, 0.55, 5.0, 21, and 31 MeV.
    Keywords: SPACE SCIENCES
    Type: AD-A000274 , Journal of Geophysical Research; 79; Sept. 1
    Format: text
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