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  • 1
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    A Knowledge-Based System Developer for aerospace applications (1993)
    In:  Other Sources
    Details
    Publication Date: 2013-08-29
    Description: A prototype Knowledge-Based System Developer (KBSD) has been developed for aerospace applications by utilizing artificial intelligence technology. The KBSD directly acquires knowledge from domain experts through a graphical interface then builds expert systems from that knowledge. This raises the state of the art of knowledge acquisition/expert system technology to a new level by lessening the need for skilled knowledge engineers. The feasibility, applicability , and efficiency of the proposed concept was established, making a continuation which would develop the prototype to a full-scale general-purpose knowledge-based system developer justifiable. The KBSD has great commercial potential. It will provide a marketable software shell which alleviates the need for knowledge engineers and increase productivity in the workplace. The KBSD will therefore make knowledge-based systems available to a large portion of industry.
    Keywords: DOCUMENTATION AND INFORMATION SCIENCE
    Type: Center for Space Transportation and Applied Research Fifth Annual Technical Symposium Proceedings; 00006 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Neural networks analysis on SSME vibration simulation data (1993)
    In:  Other Sources
    Details
    Publication Date: 2013-08-29
    Description: The neural networks method is applied to investigate the feasibility in detecting anomalies in turbopump vibration of SSME to supplement the statistical method utilized in the prototype system. The investigation of neural networks analysis is conducted using SSME vibration data from a NASA developed numerical simulator. The limited application of neural networks to the HPFTP has also shown the effectiveness in diagnosing the anomalies of turbopump vibrations.
    Keywords: CYBERNETICS
    Type: Center for Space Transportation and Applied Research Fifth Annual Technical Symposium Proceedings; 00016 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Automatic detection of anomalies in Space Shuttle Main Engine turbopumps (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A prototype expert system for detecting anomalies in turbopump vibration data has been tested with data from ground tests 902-473, 902-501 902-519, and 904-097 of the Space Shuttle Main Engine!nc (SSME). The expert system has been utilized to analyze vibration ion data from each of the following SSME components: pressure oxidizer turbopump, high-pressure fuel turbo pump, low-pressure fuel turbopump, and preburner boost pump. The expert system locates and classifies peaks in the power spectral density of each 0.4 s window of steady-state data. Peaks representing the fundamental and harmonic frequencies of both shaft rotation and bearing cage rotation are identified by the expert system. Anomalies are then detected on the basis of of two thresholds set individually for the amplitude of each of these peaks: a prior threshold used during the first few windows of data in a test, and a posterior threshold used thereafter. In most cases the anomalies detected by the expert system agree with those reported by NASA. The two cases where there is significant disagreement will be further studied and the system design refined accordingly.
    Keywords: Mechanical Engineering
    Type: CSTAR 3rd Annual Technical Symposium Proceedings; 122-131; NASA-CR-199702
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Neural network based expert system for compressor stall monitoring (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This research is designed to apply a new information processing technology, artificial neural networks, to monitoring compressor stall. The outputs of neural networks support the dynamic knowledge data base of an expert system. This is the open-loop mode to avoid compressor stall. The integration of a control system with neural networks is the closed-loop mode in stall avoidance. The feasibility of the concept has been demonstrated for the compressor of 16-foot transonic/supersonic propulsion wind tunnels. The construction of a prototpye expert system has been initiated.
    Keywords: CYBERNETICS
    Type: AIAA PAPER 91-2500
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Development of an intelligent hypertext system for wind tunnel testing (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper summarizes the results of a system utilizing artificial intelligence technology to improve the productivity of project engineers who conduct wind tunnel tests. The objective was to create an intelligent hypertext system which integrates a hypertext manual and expert system that stores experts' knowledge and experience. The preliminary (Phase I) effort implemented a prototype IHS module encompassing a portion of the manuals and knowledge used for wind tunnel testing. The effort successfully demonstrated the feasibility of the intelligent hypertext system concept. A module for the internal strain gage balance, implemented on both IBM-PC and Macintosh computers, is presented. A description of the Phase II effort is included.
    Keywords: CYBERNETICS
    Type: AIAA PAPER 91-0654
    Format: text
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  • 6
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    Intelligent hypertext systems for aerospace engineering applications (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper is a progress report on the utilization of AI technology for assisting users locating and understanding technical information in manuals used for planning and conducting wind tunnel test. The specific goal is to create an Intelligent Hypertext System (IHS) for wind tunnel testing which combines the computerized manual in the form of hypertext and an advisory system that stores experts' knowledge and experiences. A prototype IHS for conducting transonic wind tunnel testing has been constructed with limited knowledge base. The prototype is being evaluated by potential users.
    Keywords: DOCUMENTATION AND INFORMATION SCIENCE
    Type: TABES PAPER 89-1906
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Development of an Intelligent Hypertext Manual for the Space Shuttle Hazardous Gas Detection System (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Intelligent Hypertext Manual (IHM) for the Hazardous Gas Detection System (HGDS) of the Space Shuttle is described as an example of an integrated knowledge system. The IHM is described in terms of its design as a system for facilitating the interpretation of real-time data regarding hazardous gases and their successful and timely detection. Hypermedia technology is employed that incorporates text, video, and sound, and the architecture of the IHM integrated knowledge system is based on knowledge elements, a basic user interface, and integrated application software. Knowledge organization enhances the retrieval of documents for launch commit criteria, operations and maintenance requirements, flight-measurement location, and hypermedia incorporation. The integration of computer and AI technologies for the HGDS IHM demonstrates the potential for enhancing efficiency in aerospace operations with aerospace data that are easy to retrieve.
    Keywords: CYBERNETICS
    Type: AIAA PAPER 92-3580
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Automatic detection of anomalies in Space Shuttle Main Engine turbopumps (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A prototype expert system (developed on both PC and Symbolics 3670 lisp machine) for detecting anomalies in turbopump vibration data has been tested with data from ground tests 902-473, 902-501, 902-519, and 904-097 of the Space Shuttle Main Engine (SSME). The expert system has been utilized to analyze vibration data from each of the following SSME components: high-pressure oxidizer turbopump, high-pressure fuel turbopump, low-pressure fuel turbopump, and preburner boost pump. The expert system locates and classifies peaks in the power spectral density of each 0.4-sec window of steady-state data. Peaks representing the fundamental and harmonic frequencies of both shaft rotation and bearing cage rotation are identified by the expert system. Anomalies are then detected on the basis of sequential criteria and two threshold criteria set individually for the amplitude of each of these peaks: a prior threshold used during the first few windows of data in a test, and a posterior threshold used thereafter. In most cases the anomalies detected by the expert system agree with those reported by NASA. The two cases where there is significant disagreement will be further studied and the system design refined accordingly.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3329
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Application of intelligent systems to wind tunnel test facilities (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An approach to the application of intelligent-systems technology to the wind tunnel facilities at NASA Ames Research Center is outlined. To help fulfill the long-range goals of improving data quality and increasing personnel efficiency and management effectiveness, three major areas of intelligent systems application are recommended. The available state-of-the-art technology for developing the proposed systems is reviewed including the application of commercial software packages. The initial tasks and effort to develop these systems are recommended. A prototype expert system for selection of internal strain-gage balances has been built and is presented herein as an example model for the future systems.
    Keywords: SYSTEMS ANALYSIS
    Type: AIAA PAPER 88-0193
    Format: text
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  • 10
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    Supersonic laminar flow control research (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The objective of the research is to understand supersonic laminar flow stability, transition, and active control. Some prediction techniques will be developed or modified to analyze laminar flow stability. The effects of supersonic laminar flow with distributed heating and cooling on active control will be studied. The primary tasks of the research applying to the NASA/Ames Proof of Concept (POC) Supersonic Wind Tunnel and Laminar Flow Supersonic Wind Tunnel (LFSWT) nozzle design with laminar flow control are as follows: (1) predictions of supersonic laminar boundary layer stability and transition, (2) effects of wall heating and cooling for supersonic laminar flow control, and (3) performance evaluation of POC and LFSWT nozzles design with wall heating and cooling effects applying at different locations and various length.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-196049 , NAS 1.26:196049
    Format: application/pdf
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