Health and Maintenance Status Determination and Predictive Fault Diagnosis System

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,986.00
Award Year:
2009
Program:
STTR
Phase:
Phase I
Contract:
NNX09CF81P
Agency Tracking Number:
080146
Solicitation Year:
2008
Solicitation Topic Code:
T10.01
Solicitation Number:
n/a
Small Business Information
American GNC Corporation
888 Easy Street, Simi Valley, CA, 93065-1812
Hubzone Owned:
N
Socially and Economically Disadvantaged:
Y
Woman Owned:
N
Duns:
611466855
Principal Investigator:
Ching-Fang Lin
Principal Investigator
() -
cflin@americangnc.com
Business Contact:
Lina Greenberg
Business Official
(805) 582-0582
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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