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  • 1
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    Elimination of a discrete frequency acoustical phenomenon associated with the Space Shuttle main engine oxidizer valve-duct system (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: In the development of the Space Shuttle Main Engines, various unpredictable dynamical phenomena were experienced which resulted in engine shutdown or failures, e.g., fires. One such dynamical phenomenon consisted of an acoustical buzz at 7200 Hz in the vicinity of the main oxidizer valve. The method of isolating the buzz phenomenon, identifying the mechanism, and developing a fix to eliminate the buzz is presented together with supporting data. These data, i.e., fluctuating pressure and acceleration data, were obtained from hot firing engine tests and from liquid nitrogen flow simulation tests conducted at Marshall Space Flight Center.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Information Center The Shock and Vibration Bull., No. 50, Part 2; p 247-255
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Space Shuttle Main Engine (SSME) Pogo testing and results (1982)
    In:  CASI
    Details
    Publication Date: 2015-07-14
    Description: To effectively assess the Pogo stability of the space shuttle vehicle, it was necessary to characterize the structural, propellant, and propulsion dynamics subsystems. Extensive analyses and comprehensive testing programs were established early in the project as an implementation of management philosophy of Pogo prevention for space shuttle. The role of the space shuttle main engine (SSMF) in the Pogo prevention plans, the results obtained from engine ground testing with analysis, and measured data from STS-1 flight are discussed.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 1-20
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A comparison of measured and theoretical predictions for STS ascent and entry sonic booms (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Sonic boom measurements have been obtained during the flights of STS-1 through 5. During STS-1, 2, and 4, entry sonic boom measurements were obtained and ascent measurements were made on STS-5. The objectives of this measurement program were (1) to define the sonic boom characteristics of the Space Transportation System (STS), (2) provide a realistic assessment of the validity of xisting theoretical prediction techniques, and (3) establish a level of confidence for predicting future STS configuration sonic boom environments. Detail evaluation and reporting of the results of this program are in progress. This paper will address only the significant results, mainly those data obtained during the entry of STS-1 at Edwards Air Force Base (EAFB), and the ascent of STS-5 from Kennedy Space Center (KSC). The theoretical prediction technique employed in this analysis is the so called Thomas Program. This prediction technique is a semi-empirical method that required definition of the near field signatures, detailed trajectory characteristics, and the prevailing meteorological characteristics as an input. This analytical procedure then extrapolates the near field signatures from the flight altitude to an altitude consistent with each measurement location.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Pt. 2; p 1277-1301
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Propulsion system ignition overpressure for the Space Shuttle (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Liquid and solid rocket motor propulsion systems create an overpressure wave during ignition, caused by the accelerating gas particles pushing against or displacing the air contained in the launch pad or launch facility and by the afterburning of the fuel-rich gases. This wave behaves as a blast or shock wave characterized by a positive triangular-shaped first pulse and a negative half-sine wave second pulse. The pulse travels up the space vehicle and has the potential of either overloading individual elements or exciting overall vehicle dynamics. The latter effect results from the phasing difference of the wave from one side of the vehicle to the other. This overpressure phasing, or delta P environment, because of its frequency content as well as amplitude, becomes a design driver for certain panels (e.g., thermal shields) and payloads for the Space Shuttle. The history of overpressure effects on the Space Shuttle, the basic overpressure phenomenon, Space Shuttle overpressure environment, scale model overpressure testing, and techniques for suppressing the overpressure environments are considered.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-82458
    Format: application/pdf
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  • 5
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    OEX - Use of the Shuttle Orbiter as a research vehicle (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Orbiter Experiments Program to provide research instrumentation on the Shuttle Orbiter is discussed. Flight aerodynamic problems such as ground-based data limitations, rarefied flow effects, body flap and control surface effectiveness, and windward surface heat transfer are reviewed. Experiments currently under development are described, including experiments on tile gaps and wall catalytic effects which provide the opportunity to obtain data not available in ground facilities and apply the results to improvements in the Orbiter's thermal protection system. Such experiments combined with other instrumentation on the Orbiter should provide benchmark flight data which can make a significant impact on the design of future space transportation systems.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 81-2512 , Flight Testing Conference; Nov 11, 1981 - Nov 13, 1981; Las Vegas, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Shuttle Performance: Lessons Learned, Part 2 (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Several areas of Space Shuttle technology were addressed including aerothermal environment, thermal protection, measurement and analysis, Shuttle carrier aerodynamics, entry analysis of the STS-3, and an overview of each section.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CP-2283-PT-2 , L-15673-PT-2 , NAS 1.55:2283-PT-2 , Mar 08, 1983 - Mar 10, 1983; Hampton, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Shuttle Performance: Lessons Learned, part 1 (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Beginning with the first orbital flight of the Space Shuttle, a great wealth of flight data became available to the aerospace community. These data were immediately subjected to analyses by several different groups with different viewpoints and motivations. The results were collected and presented in several papers in the subject areas of ascent and entry aerodynaics; guidance, navigation, and control; aerothermal environment prediction; thermal protection systems; and measurement techniques.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CP-2283-PT-1 , L-15673-PT-1 , NAS 1.55:2283-PT-1 , Mar 08, 1983 - Mar 10, 1983; Hampton, VA; United States
    Format: application/pdf
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