Health and Maintenance Status Determination and Predictive Fault Diagnosis System

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX09CF81P
Agency Tracking Number: 080146
Amount: $99,986.00
Phase: Phase I
Program: STTR
Awards Year: 2009
Solicitation Year: 2008
Solicitation Topic Code: T10.01
Solicitation Number: N/A
Small Business Information
888 Easy Street, Simi Valley, CA, 93065-1812
DUNS: 611466855
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: Y
Principal Investigator
 Ching-Fang Lin
 Principal Investigator
 () -
 cflin@americangnc.com
Business Contact
 Lina Greenberg
Title: Business Official
Phone: (805) 582-0582
Email: lgreenberg@americangnc.com
Research Institution
 The University of Kansas Center for Research, Inc.
 Not Available
 2385 Irving Hill Road
Lawrence, KS, 66045
 (785) 864-3441
 Domestic nonprofit research organization
Abstract
The objective of this project is to demonstrate intelligent health and maintenance status determination and predictive fault diagnosis techniques for NASA rocket engines under online and offline conditions from either on-board or maintenance, test and analytic data. AGNC proposes a Health and Maintenance Status Determination and Predictive Fault Diagnosis System (HMSD/PFDS). The fuzzy qualitative model for model-based residual generation and the rule-based evaluation of residuals using neural-fuzzy combination are defined. Intelligent data fusion strategies for health and maintenance determination and predictive fault diagnosis are developed for rocket engine systems/subsystems. The goal is to ensure safety, cost reduction, graceful degradation and re-optimization in the case of failures, malfunctions and damages. Kalman filter based and rule based evaluation of residuals using neural-fuzzy combination are developed. The use of fuzzy qualitative models takes into account the uncertainties associated with behavior descriptions and incorporates available expert failure symptom knowledge to recognize the particular failure features. Actual or simulated rocket engine sensed or derived data are utilized to evaluate the effectiveness of the health and maintenance determination and fault prognosis approaches for NASA platforms. Phase I is devoted to the HMSD/PFDS design and simulation. Phase II will result in development of a functional prototype.

* Information listed above is at the time of submission. *

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