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  • SPACECRAFT PROPULSION AND POWER
  • crystal structure
  • 1990-1994  (2)
  • 1935-1939
  • 1990  (2)
  • 1
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    Rocket engine failure detection using system identification techniques (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The theoretical foundation and application of two univariate failure detection algorithms to Space Shuttle Main Engine (SSME) test firing data is presented. Both algorithms were applied to data collected during steady state operation of the engine. One algorithm, the time series algorithm, is based on time series techniques and involves the computation of autoregressive models. Time series techniques have been previously applied to SSME data. The second algorithm is based on standard signal processing techniques. It consists of tracking the variations in the average signal power with time. The average signal power algorithm is a newly proposed SSME failure detection algorithm. Seven nominal test firings were used to develop failure indication thresholds for each algorithm. These thresholds were tested using four anomalous firings and one additional nominal firing. Both algorithms provided significantly earlier failure indication times than did the current redline limit system. Neither algorithm gave false failure indications for the nominal firing. The strengths and weaknesses of the two algorithms are discussed and compared. The average signal algorithm was found to have several advantages over the time series algorithm.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-1993
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight motor set 360L002 (STS-27R). Volume 5: Nozzle component (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A review of the performance and post-flight condition of the STS-27 Redesigned Solid Rocket Motor (RSRM) nozzles is presented. Thermal/Structural instrumentation data is reviewed, and applicable Discrepancy Reports (DRs) and Process Departures (PDs) are presented. The Nozzle Component Program Team (NCPT) performance evaluation and the Redesign Program Review Board (RPRB) assessment is included. The STS-27 nozzle assemblies were flown on the RSRM Second Flight (Space Shuttle Atlantis) on 2 December 1988. The nozzles were a partially submerged convergent and/or divergent movable design with an aft pivot point flexible bearing. The nozzle assemblies incorporated the following features: RSRM forward exit cone with snubber assembly, RSRM fixed housing, Structural backup Outer Boot Ring (OBR), RSRM cowl ring, RSRM nose inlet assembly, RSRM throat assembly, RSRM aft exit cone assembly with Linear-Shaped Charge (LSC), RTV backfill in Joints 1, 3, and 4, Use of EA913 NA adhesive in place of EA913 adhesive, Redesigned nozzle plug, and Carbon Cloth Phenolic (CCP) with 750 ppm sodium content. The CCP material usage for the STS-27 forward nozzle and aft exit cone assemblies is shown.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183945 , NAS 1.26:183945 , TWR-17541-5
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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