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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (340)
  • INSTRUMENTATION AND PHOTOGRAPHY  (313)
  • 2025-2025
  • 2015-2019
  • 1975-1979  (653)
  • 1975  (653)
Collection
Keywords
Years
  • 2025-2025
  • 2015-2019
  • 1975-1979  (653)
Year
  • 1
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    Analytical and test equipment: A compilation (1975)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A compilation is presented of innovations in testing and measuring technology for both the laboratory and industry. Topics discussed include spectrometers, radiometers, and descriptions of analytical and test equipment in several areas including thermodynamics, fluid flow, electronics, and materials testing.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-SP-5972(03)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The LAGEOS system (1975)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The LAGEOS system is defined and its rationale is developed. Key features of the baseline system specified included a circular orbit at 5900 km altitude and an inclination of 110 deg, and a satellite 60 cm in diameter weighing some 385 kg and mounting 440 retroreflectors, each having a diameter of 3.8 cm, leaving 30% of the spherical surface available for reflecting sunlight diffusely to facilitate tracking by Baker-Nunn cameras. The satellite weight was increased to 411 kg in the actual design through the addition of a 4th-stage apogee-kick motor. The number and diameter of the retroreflectors are now 426 and 3.81 cm, respectively. The net effect of these partially compensating changes is not significant. The diffusely reflecting area was increased to 47% of the satellite surface.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-73072
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Applications of Microwaves to Remote Sensing of Terrain (1975)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A survey and study was conducted to define the role that microwaves may play in the measurement of a variety of terrain-related parameters. The survey consisted of discussions with many users and researchers in the field of remote sensing. In addition, a survey questionnaire was prepared and replies were solicited from these and other users and researchers. The results of the survey, and associated bibliography, were studied and conclusions were drawn as to the usefulness of radiometric systems for remote sensing of terrain.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-2581
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Engineering principles to assure compatible docking between future spacecraft of USA and USSR (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: Working jointly the USA and the USSR have selected an androgynous, peripheral type docking mechanism concept. The mechanical principles inherent to the concept, the rationale supporting its selection, and the probable nature of future designs stemming from the concept, are described. Operational situations just prior to docking, impact conditions, energy absorption, and the structural joining of the spacecraft, are specified. Docking procedures for the Apollo-Soyuz missions are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of the Astronautical Sciences; 23; Jan
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Spacecraft charging at high altitudes - The SCATHA satellite program (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: Satellites at synchronous altitude exhibit unexplained behavior in the operation of electronic circuits and in the performance of thermal controls. A possible explanation for this behavior is the fact that satellites can be charged to large negative voltages by energetic electrons in the space environment. A space measurements program entitled SCATHA has been formulated to determine the characteristics of the charging process, to measure the response of the satellite when charging occurs, and to evaluate the utility of various corrective techniques which can minimize differential charging on the satellite. The instrumentation will measure charging levels and rates of twenty samples of satellite materials, some of which will be modified to prevent buildup of electrostatic charge. The electromagnetic interference background on the satellite will be measured for comparison with MIL STD 461, Electromagnetic Interference Characteristics Requirements for Equipment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-92 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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  • 6
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    A fast sampling device for the mass spectrometric analysis of liquid rocket engine exhaust (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The design of a device to obtain compositional data on rocket exhaust by direct sampling of reactive flow exhausts into a mass spectrometer is presented. Sampling at three stages differing in pressure and orifice angle and diameter is possible. Results of calibration with pure gases and gas mixtures are erratic and of unknown accuracy for H2, limiting the usefulness of the apparatus for determining oxidizer/fuel ratios from combustion product analysis. Deposition effects are discussed, and data obtained from rocket exhaust spectra are analyzed to give O/F ratios and mixture ratio distribution. The O/F ratio determined spectrometrically is insufficiently accurate for quantitative comparison with cold flow data. However, a criterion for operating conditions with improved mixing of fuel and oxidizer which is consistent with cold flow results may be obtained by inspection of contour plots. A chemical inefficiency in the combustion process when oxidizer is in excess is observed from reactive flow measurements. Present results were obtained with N2O4/N2H4 propellants.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 75-1270
    Format: text
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  • 7
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    Test evaluation of potential heat shield contamination of an Outer Planet Probe's atmospheric sampling system (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: An Outer Planets Probe which retains the charred heatshield during atmospheric descent must deploy a sampling tube through the heatshield to extract atmospheric samples for analysis. Once the sampling tube is deployed, the atmospheric samples ingested must be free of contaminant gases generated by the heatshield. Outgassing products such as methane and water vapor are present in planetary atmospheres and hence, ingestion of such species would result in gas analyzer measurement uncertainties. This paper evaluates the potential for, and design impact of, the extracted atmospheric samples being contaminated by heatshield outgassing products. Flight trajectory data for Jupiter, Saturn and Uranus entries are analyzed to define the conditions resulting in the greatest potential for outgassing products being ingested into the probe's sampling system. An experimental program is defined and described which simulates the key flow field features for a planetary flight in a ground-based test facility. The primary parameters varied in the test include: sampling tube length, injectant mass flow rate and angle of attack. Measured contaminant levels predict the critical sampling tube length for contamination avoidance. Thus, the study demonstrates the compatibility of a retained heatshield concept and high quality atmospheric trace species measurements.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-1151 , American Institute of Aeronautics and Astronautics and American Geophysical Union, Conference on the Exploration of the Outer Planets; Sept. 17-19, 1975; St. Louis, MO
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Self sterilization of bodies during outer planet entry (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: As a body encounters the atmosphere of an outer planet, whether accidentally or by plan, it will be subjected to heat loads which could result in high temperature conditions that render terrestrial organisms on or within the body non-viable. To determine whether an irregularly shaped entering body, consisting of several different materials, would be sterilized during inadvertent entry at high velocity, the thermal response of a typical outer planet spacecraft instrument was studied. The results indicate that the Teflon-insulated cable and electronic circuit boards may not experience sterilizing temperatures during a Jupiter, Saturn, or Titan entry. Another conclusion of the study is that small plastic particles entering Saturn from outer space have wider survival corridors than do those at Jupiter.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Format: text
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  • 9
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    Improved planetary orbit mission capabilities in the Shuttle era by use of space-storable propulsion systems (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Planetary-orbit mission capabilities will be greatly improved by the advent of space-storable retropropulsion systems with liquid fluorine and hydrazine as bipropellants even when the Shuttle/Tug is used as launch vehicle. Having a specific impulse as large as 375 sec, a multimission propulsion module using space-storable propellants with Pioneer or Mariner spacecraft as payload can perform Mercury, Saturn, and Uranus orbiter missions, and even some comet rendezvous missions, more cost effectively and flexibly than one using earth-storable propellants. It also can reduce trip time to the outer planets significantly. This paper presents mission requirements, technology status, system design and performance, development schedules, and costs based on data derived in a recent design and feasibility study.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-1137 , American Institute of Aeronautics and Astronautics and American Geophysical Union, Conference on the Exploration of the Outer Planets; Sept. 17-19, 1975; St. Louis, MO
    Format: text
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  • 10
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    Reliability considerations in long-life outer planet spacecraft system design (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A Mariner Jupiter/Saturn mission has been planned for 1977. System reliability questions are discussed, taking into account the actual and design lifetime, causes of mission termination, in-flight failures and their consequences for the mission, and the use of redundancy to avoid failures. The design process employed optimizes the use of proven subsystem and system designs and then makes the necessary improvements to increase the lifetime as required.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IAF PAPER 75-077 , International Astronautical Federation, International Astronautical Congress; Sept. 21-27, 1975; Lisbon; Portugal
    Format: text
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