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  • 1
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    The development and application of aerodynamic uncertainties: And flight test verification for the space shuttle orbiter (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The approach used in establishing the predicted aerodynamic uncertainties and the process used in applying these uncertainties during the design of the Orbiter flight control system and the entry trajectories are presented. The flight test program that was designed to verify the stability and control derivatives with a minimum of test flights is presented and a comparison of preflight predictions with preliminary flight test results is made. It is concluded that the approach used for the Orbiter is applicable to future programs where testing is limited due to time constraints or funding.
    Keywords: SPACE TRANSPORTATION
    Type: Space Shuttle Tech. Conf., Pt. 1; p 264-294
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The aerodynamic challenges of the design and development of the space shuttle orbiter (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The major aerodynamic design challenge at the beginning of the United States Space Transportation System (STS) research and development phase was to design a vehicle that would fly as a spacecraft during early entry and as an aircraft during the final phase of entry. The design was further complicated because the envisioned vehicle was statically unstable during a portion of the aircraft mode of operation. The second challenge was the development of preflight aerodynamic predictions with an accuracy consistent with conducting a manned flight on the initial orbital flight. A brief history of the early contractual studies is presented highlighting the technical results and management decisions influencing the aerodynamic challenges. The configuration evolution and the development of preflight aerodynamic predictions will be reviewed. The results from the first four test flights shows excellent agreement with the preflight aerodynamic predictions over the majority of the flight regimes. The only regimes showing significant disagreement is confined primarily to early entry, where prediction of the basic vehicle trim and the influence of the reaction control system jets on the flow field were found to be deficient. Postflight results are analyzed to explain these prediction deficiencies.
    Keywords: SPACE TRANSPORTATION
    Type: Space Shuttle Tech. Conf., Pt. 1; p 209-263
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    The development of aerodynamic uncertainties for the space shuttle orbiter (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Shuttle Program development schedule and the management decision to perform an orbital, manned mission on the first launch resulted in a requirement to develop realistic aerodynamic uncertainties for the preflight aerodynamic predictions. This paper addresses the methodology in developing two types of aerodynamic uncertainties. One involves the ability to reproduce aerodynamic results between various wind tunnel tests. The second addresses the difference between preflight aerodynamic predictions and flight results derived from analysis of past aircraft programs. Both types of uncertainties for pitching moment, lateral-directional stability, rudder power, and aileron power are presented. In addition, the application of uncertainties to flight control design and fight test planning is briefly reviewed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 2; p 1169-1186
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A preliminary correlation of the orbiter stability and control aerodynamics from the first two Space Shuttle flights /STS-1 & 2/ with preflight predictions (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A correlation of the stability and control derivatives from flight (STS-1 & 2) with preflight predictions is presented across the Mach range from 0.9 to 25. Flight data obtained from specially designed flight test maneuvers as well as from conventional bank maneuvers generally indicate good agreement with predicted data. However, the vehicle appears to be lateral-directionally more stable than predicted in the transonic regime. Aerodynamic 'reasonableness tests' are employed to test for validity of flight data. The importance of testing multiple models in multiple wind tunnels at the same test conditions is demonstrated.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-0564 , In: Aerodynamic Testing Conference; Mar 22, 1982 - Mar 24, 1982; Williamsburg, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The Space Shuttle Orbiter approach and landing tests - A correlation of flight and predicted performance data (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper represents the results of a program in which a flight test vehicle was flown for a limited number of flights. The vehicle was the Space Shuttle Orbiter. The total free flight time for the entire flight test program was less than half an hour. The flight regime tested represented only the approach and landing phase of the vehicle's planned flight capability. The program relied heavily on an extensive wind tunnel test program to predict the aerodynamic performance data over the complete flight range, as well as to predict data tolerances. During the flight test program, short maneuvers performed were to provide flight motion data. A data extraction program was developed to produce flight derived aerodynamic performance data in coefficient form from the motion data. The resultant flight test data was correlated with the predicted data and fell within the predicted data tolerances for all phases of the subsonic flight test regime, including ground effects.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 78-793 , Aerodynamic Testing Conference; Apr 19, 1978 - Apr 21, 1978; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
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