Physics Based Gear Health Prognosis via Modeling Coupled with Component Level Tests

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$69,999.00
Award Year:
2007
Program:
STTR
Phase:
Phase I
Contract:
N00014-07-M-0444
Agency Tracking Number:
N074-010-0349
Solicitation Year:
2007
Solicitation Topic Code:
N07-T010
Solicitation Number:
n/a
Small Business Information
VEXTEC CORP.
750 Old Hickory Blvd, Building 2, Suite 270, Brentwood, TN, 37027
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
128193997
Principal Investigator:
Richard Holmes
Director M&S
(615) 372-0299
Rholmes@vextec.com
Business Contact:
Loren Nasser
President/CEO
(615) 372-0299
Lnasser@vextec.com
Research Institution:
PURDUE UNIV.
Thomas Farris
315 North Grant Street
West Lafayette, IN, 47907-2023
(765) 494-5118
Nonprofit college or university
Abstract
PHM investments can successfully diagnose up to 70% of damage fault indications. The cost of empirically-based testing is very high and must be reworked for every gear system design change. Physics-based FEA combined with long crack modeling can be self-adapting and overcome the high cost of pure statistical approaches but still unable to diagnose the remaining 30% failures because onset of damage is too small and happens too quickly. VEXTEC has already developed techniques for modeling damage at the fundamental microstructural level which will uniquely be applied to gear system PHM under this STTR. The modeling properties include geometry, composition, material characteristics, case hardness, core hardness, case depth, design ratios of case to tooth thickness, surface finish, and machining are directly and explicitly addressed in the formulation of the micromechanical material model. The objective of this STTR is to develop physics-based failure models to allow for explicit prognosis of air vehicle gear components and systems. This project provides for successful modeling of the effects of tooth bending, spalling, and pitting to advance the understanding of these failure modes as a critical and new approach to aerospace application prognosis.

* information listed above is at the time of submission.

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