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  • Other Sources  (294)
  • FLUID MECHANICS AND HEAT TRANSFER  (130)
  • SPACE TRANSPORTATION  (83)
  • Life and Medical Sciences
  • STRUCTURAL MECHANICS
  • 1990-1994
  • 1980-1984  (294)
  • 1940-1944
  • 1935-1939
  • 1880-1889
  • 1984  (144)
  • 1983  (150)
  • 1939
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  • 1990-1994
  • 1980-1984  (294)
  • 1940-1944
  • 1935-1939
  • 1880-1889
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  • 1
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    Transportation - Space Station interfaces (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A study aimed at identifying conceptual mechanisms for the transfer and manipulation of various masses in the vicinity of or on the Space Station is presented. These transfers encompass mass transfers involved in the arrivals or departures of various vehicles including the Shuttle, Orbital Manuever Vehicles (OMVs), and Orbital Transfer Vehicles (OTVs); point-to-point mass transfer of a nonroutine nature around the Space Station; and routine transfer of cargo and spacecraft around the Space Station, including the mating and processing of OMVs, OTVs, propellants, and payloads.
    Keywords: SPACE TRANSPORTATION
    Type: ; 31 p.|NASA, Rendezvous and Proximity Operations Workshop, Houston; Feb 19, 1984 - Feb 20, 1984; Houston, TX; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Mean flowfields in axisymmetric combustor geometries with swirl (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: (Previously cited in issue 06, p. 860, Accession no. A82-17824)
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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    NASA TECHNICAL REPORTS
  • 3
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    Approach to establishing the effect of aeroelasticity on aerodynamic characteristics of the space shuttle orbiter (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The static aeroelastic effects on the longitudinal stability and elevon/aileron effectiveness of the space transportation system (STS) Space Shuttle orbiter were estimated by a simplified approach called the elevon torsional stiffness (ETS) method. This method employs rigid model wind tunnel test results to predict aeroelastic effects. Lateral/directional stability and rudder effectiveness were based on results of a wind tunnel test in which a flexible tail model was used. Comparisons with selective flight data are made in this paper. Results of correlations with flight data (although limited at the present time) verify the predicted aeroelastic effects for the orbiter. The orbiter's structural characteristics are such that the effects of aeroelasticity, whether estimated using analytical techniques or simplified methods, do not appear to affect the vehicle performance to any great extent. The large amount of scatter in the flight-extracted data made verification of the aeroelastic corrections very difficult. Generally, the simplified elevon torsional stiffness method provided better correlation with flight test results than he analytical method and reduced the verification effort and cost.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 413-446
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    NASA TECHNICAL REPORTS
  • 4
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    Assessing the orbiter thermal environment using flight data (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 534-541
    Format: text
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  • 5
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    Designing for a new era of launch vehicle operational efficiency (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: It is pointed out that early recognition of operational requirements and assessment of their effects provides the best chance of designing an economically viable future space transportation system (FSTS). Operational factors which may influence configuration design include fleet size, operation mode, refurbishment, and the resource requirements. FTST has a simplified operational role compared to the Space Shuttle, which, in addition to transportation, must perform experiments, support payloads, and stay long on orbit. In the future a space station will perform many of these tasks. The FSTS comprises a two-stage fully reusable launch vehicle designed to carry 150,000 lb to a space station, off-load, and return. It would always be launched fully loaded, and its cargo would be processed and redistributed at the space station. Attention is given to ground servicing, flight operations, rendezvous-compatible orbits, launch windows, standard trajectories, entry windows, operational costs, the mission model, and resource requirements.
    Keywords: SPACE TRANSPORTATION
    Type: Astronautics and Aeronautics (ISSN 0004-6213); 21; June 198
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  • 6
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    Control techniques to improve Space Shuttle solid rocket booster separation (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The present Space Shuttle's control system does not prevent the Orbiter's main engines from being in gimbal positions that are adverse to solid rocket booster separation. By eliminating the attitude error and attitude rate feedback just prior to solid rocket booster separation, the detrimental effects of the Orbiter's main engines can be reduced. In addition, if angular acceleration feedback is applied, the gimbal torques produced by the Orbiter's engines can reduce the detrimental effects of the aerodynamic torques. This paper develops these control techniques and compares the separation capability of the developed control systems. Currently with the worst case initial conditions and each Shuttle system dispersion aligned in the worst direction (which is more conservative than will be experienced in flight), the solid rocket booster has an interference with the Shuttle's external tank of 30 in. Elimination of the attitude error and attitude rate feedback reduces that interference to 19 in. Substitution of angular acceleration feedback reduces the interference to 6 in. The two latter interferences can be eliminated by atess conservative analysis techniques, that is, by using a root sum square of the system dispersions.
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 6; May-June
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  • 7
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    Space shuttle orbiter leading-edge flight performance compared to design goals (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Thermo-structural performance of the Space Shuttle orbiter Columbia's leading-edge structural subsystem for the first five (5) flights is compared with the design goals. Lessons learned from thse initial flights of the first reusable manned spacecraft are discussed in order to assess design maturity, deficiencies, and modifications required to rectify the design deficiencies. Flight data and post-flight inspections support the conclusion that the leading-edge structural subsystem hardware performance was outstanding for the initial five (5) flights.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 2; p 1065-1082
    Format: application/pdf
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  • 8
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    Filler bar heating due to stepped tiles in the shuttle orbiter thermal protection system (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An analytical study was performed to investigate the excessive heating in the tile to tile gaps of the Shuttle Orbiter Thermal Protection System due to stepped tiles. The excessive heating was evidence by visible discoloration and charring of the filler bar and strain isolation pad that is used in the attachment of tiles to the aluminum substrate. Two tile locations on the Shuttle orbiter were considered, one on the lower surface of the fuselage and one on the lower surface of the wing. The gap heating analysis involved the calculation of external and internal gas pressures and temperatures, internal mass flow rates, and the transient thermal response of the thermal protection system. The results of the analysis are presented for the fuselage and wing location for several step heights. The results of a study to determine the effectiveness of a half height ceramic fiber gap filler in preventing hot gas flow in the tile gaps are also presented.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Pt. 2; p 891-912
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  • 9
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    Turbulence characteristics of an axisymmetric reacting flow (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Turbulent sudden expansion flows are of significant theoretical and practical importance. Such flows have been the subject of extensive analytical and experimental study for decades, but many issues are still unresolved. Detailed information on reacting sudden expansion flows is very limited, since suitable measurement techniques have only been available in recent years. The present study of reacting flow in an axisymmetric sudden expansion was initiated under NASA support in December 1983. It is an extension of a reacting flow program which has been carried out with Air Force support under Contract F33615-81-K-2003. Since the present effort has just begun, results are not yet available. Therefore a brief overview of results from the Air Force program will be presented to indicate the basis for the work to be carried out.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Lewis Research Center Combust. Fundamentals Res.; p 189-198
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  • 10
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    Transient vibration test criteria for spacecraft hardware (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: Transient vibration test criteria, developed for spacecraft hardware, provide a test rationale to verify the capability of the hardware to withstand the low and mid frequency transient vibration environments induced by launch vehicle events. A test method, consisting of a series of discrete frequency, limited cycle, modulated sine wave pulses, was developed to avoid the slow swept sine drawbacks, yet provide a repeatable test that would excite all frequencies. The shape of the waveform is that of the classic response of the mass of a one degree of freedom system when it is base-excited by an exponentially decayed sine wave transient. Criteria were developed to define pulse amplitudes, shapes, and center frequencies from spacecraft loads analyses. Test tolerance criteria were also developed and specified. The transient vibration test criteria were implemented on spacecraft flight hardware and provided a more realistic test simulation (i.e., less conservative) for qualification of spacecraft hardware without risk of undertest.
    Keywords: STRUCTURAL MECHANICS
    Type: Shock and Vibration Information Center The Shock and Vibration Bull. 54, Pt. 3; p 99-110
    Format: text
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