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  • Articles
  • Other Sources  (49)
  • NASA Technical Reports  (49)
  • SPACE TRANSPORTATION  (49)
  • 1980-1984  (49)
  • 1965-1969
  • 1983  (49)
  • 1
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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
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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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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    NASA TECHNICAL REPORTS
  • 3
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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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  • 4
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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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  • 5
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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
    Format: application/pdf
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  • 6
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    An assessment of the Space Shuttle Orbiter thermal environment using flight data (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A unified analysis of the Shuttle Orbiter aerothermodynamic environment and thermal protection system performance is presented using the Space Transportation System development flight data. Comparisons of predicted and measured temperatures and heating rates along the Orbiter lower windward fuselage centerline and lower wing 50 percent and 80 percent semi-spans are discussed. The results of this study indicate lower than predicted heating on windward fuselage surface but higher heating on the nose cap and 50 percent semi-span wing panels.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 83-1488
    Format: text
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  • 7
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    Operations simulation for the design of a future space transportation system (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A high, level discrete simulation model has been developed to study the operational requirements of future space transportation systems. To illustrate the capabilities of this model, the result of a study for a future fully reusable, two-stage launch vehicle concept which delivers men and material to a space station and returns are presented. Orbital transfer vehicles, based at the space station, are also included for delivery to other orbits. Results are presented which indicate that the model can be a helpful tool in evaluating the transportation system's operational needs and its ability to meet the desired mission requirements.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 83-0140 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
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  • 8
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    Loads environment for payload/cargo integration (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Space Shuttle users are required to design their payload to the Shuttle loads environment. This loads environment covers mission phases from prelaunch to landing. Transient response loads analyses are required for lift-off and landing events. Other mission events are analyzed statically because they result in payload loads that either change slowly or are lower than lift-off and landing loads. Response data from flight instrumentation located on the orbiter and payloads have been compared to preflight design conditions and to nominal predictions. The results have verified that the design loads envelop flight responses.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 83-0328 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
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  • 9
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    Space shuttle descent flight control design requirements and experiments Learned, Pt. 1 p 617-628 (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Some of the lessons learned during the development of the Space Shuttle descent flight control system (FCS) are reviewed. Examples confirm the importance for requirements definition, systems level analyses, and testing. In sounding these experiences may have implication for future designs or suggest the discipline required in this engineering art.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons (SEE N84-10115 01-16)
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  • 10
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    The application of aerodynamic uncertainties in the design of the entry trajectory and flight control system of the space shuttle orbiter (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The process used in the application of aerodynamic uncertainties for the design and verification of the Space Shuttle Orbiter Entry Flight Control System is presented. The uncertainties were used to help set center of gravity, angle of attack and dynamic pressure lateral control divergence parameter as well as C sub n sub beta dynamic were instrumental in setting these placards.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 1; p 595-616
    Format: text
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