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  • 1
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    The Apollo 15 deployable boom anomaly (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: During the Apollo 15 mission, a boom with an attached mass spectrometer was required to retract periodically so that the instrument would not be in the field of view of other experiments. The boom did not fully retract on five of 12 occasions. Data analysis indicated that the boom probably retracted to within approximately 2.54 centimeters (1 inch) of full retraction. The pertinent boom-design details, the events in the mission related to the anomaly, a discussion of the inflight and postflight investigation of the problem, a discussion of the design changes to the boom mechanism as a result of the investigation, and subsequent flight performance are presented.
    Keywords: SPACE VEHICLES
    Type: the 7th Aerospace Mech. Symp.; p 15-26
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Investigation of configuration effects on entry heating distributions at Mach no. equals 8.0 (OH41A) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented of aerodynamic heating investigations conducted on 0.006 scale models of three Rockwell International Space Shuttle Vehicles (SSV) orbiter configurations in the Mach 8 variable density tunnel. It was established that lower surface modifications to one of these configurations (Model SS-H-00326-4) would alleviate premature transition. Re-entry data were acquired on these models at angles of attack from 30 to 40 degrees for nominal Reynolds numbers per foot of 1.0, 3.0, 6.0 and 8.0 million utilizing the phase change paint technique. A total of 17 orbiter heating runs and 3 orbiter oil flow runs were completed.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128785 , DMS-DR-2076
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Investigation of configuration effects on entry heating distributions at Mach no. equal 8.0 (OH41) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aerodynamic heating data were obtained on 0.006 scale models of four Rockwell International SSV double delta wing Orbiters in the Mach 8 variable density tunnel. A model of two previously tested Rockwell International Orbiters which are identified in the Configuration Description of this report were also tested. Orbiter surfaces were thermally mapped from the laminar through turbulent flight regimes during re-entry. Various modifications were made to model lower surfaces to determine the cause of transition in the vicinity of 3.0 million Reynolds number per foot. Re-entry data were acquired for angles of attack from 25 through 35 degrees at nominal Reynolds numbers per foot of 1.0, 2.0, 2.3, 2.5, 3.0, 3.5, 4.5 and 6.0 million utilizing the phase change paint technique. Launch data were acquired on the model upper surfaces for angles of attack of 0 and -5 degrees at nominal Reynolds numbers per foot of 3.0 and 6.0 million. A total of 70 orbiter heating runs and 6 material sample sphere runs were completed.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128784 , DMS-DR-2075
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Preliminary analysis of the effects of pressure space correlations on the vibrations of Apollo flight structure (1966)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Vibration response of Apollo skin structure to convected boundary layer turbulence
    Keywords: SPACE VEHICLES
    Type: NASA-CR-65808 , WR-66-32
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Apollo experience report: Command module uprighting system (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A water-landing requirement and two stable flotation attitudes required that a system be developed to ensure that the Apollo command module would always assume an upright flotation attitude. The resolution to the flotation problem and the uprighting concepts, design selection, design changes, development program, qualification, and mission performance are discussed for the uprighting system, which is composed of inflatable bags, compressors, valves, and associated tubing.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7081 , MSC-S-338
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Candidate configuration trade study, Stellar-Inertial Measurement System (SIMS) for an Earth Observation Satellite (EOS), addendum (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are given of an investigation of the effects of spacecraft orbital ephemeris and attitude errors on the ability to determine the locations of unknown landmarks with respect to known landmarks in the payload sensor imagery.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134042 , R-741-ADD
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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