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Reusable rocket engine turbopump health monitoring system, part 3Degradation mechanisms and sensor identification/selection resulted in a list of degradation modes and a list of sensors that are utilized in the diagnosis of these degradation modes. The sensor list is divided into primary and secondary indicators of the corresponding degradation modes. The signal conditioning requirements are discussed, describing the methods of producing the Space Shuttle Main Engine (SSME) post-hot-fire test data to be utilized by the Health Monitoring System. Development of the diagnostic logic and algorithms is also presented. The knowledge engineering approach, as utilized, includes the knowledge acquisition effort, characterization of the expert's problem solving strategy, conceptually defining the form of the applicable knowledge base, and rule base, and identifying an appropriate inferencing mechanism for the problem domain. The resulting logic flow graphs detail the diagnosis/prognosis procedure as followed by the experts. The nature and content of required support data and databases is also presented. The distinction between deep and shallow types of knowledge is identified. Computer coding of the Health Monitoring System is shown to follow the logical inferencing of the logic flow graphs/algorithms.
Document ID
19900017004
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Perry, John G. (Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 6, 2013
Publication Date
March 14, 1989
Subject Category
Mechanical Engineering
Report/Patent Number
RI/RD89-171-PT-3
NASA-CR-182294
NAS 1.26:182294
Accession Number
90N26320
Funding Number(s)
CONTRACT_GRANT: NAS3-25279
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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