Hybrid Structures for Improved Damage Tolerance of Unitized Structures

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9550-09-C-0177
Agency Tracking Number: F08B-T07-0168
Amount: $99,998.00
Phase: Phase I
Program: STTR
Awards Year: 2009
Solitcitation Year: 2008
Solitcitation Topic Code: AF08-BT07
Solitcitation Number: 2008.B
Small Business Information
ALPHA STAR
5199 E. PACIFIC COAST HWY, SUITE # 410, LONG BEACH, CA, 90804
Duns: 603371238
Hubzone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 FRANK ABDI
 CTO
 (562) 985-1100
 FABDI@ALPHASTARCORP.COM
Business Contact
 KAY MATIN
Title: PRESIDENT
Phone: (562) 985-1100
Email: KMATIN@ALPHASTARCORP.COM
Research Institution
 SOUTH WEST RESEARCH INSTITUTE
 Dale Cope
 6220 Culebra Road
P.O.Drawer 28150
SAN ANTONIO, TX, 78228
 (210) 522-2415
 Domestic nonprofit research organization
Abstract
Recent developments of advanced hybrid metallic structural concepts have been extremely promising for durable light-weight and ultra-long fatigue life large transport aircraft.  The Alpha STAR team (Alcoa, SWRI, and Virginia Tech) proposes to extend the validated Fiber Metal Laminate (FML) high fidelity analytical capability from GLARE to CentrAl  FML concepts, as well as develop the necessary robust design optimization techniques.  Candidate ultra-long life approaches will be conceptualized and demonstrated on aerospace structural components. A building block verification strategy will be conducted. Observed test data will be compared with analytical predictions for unnotched/notched coupons under service loading conditions; static, fatigue crack initiation/propagation/residual strength, and thermal fatigue.  In Phase I, the team will validate the analytical tools with 5 stringer panel fuselage/lower wing test data under static and fatigue spectrum loadings. Our effort will lead to a robust design development and demonstration in Phase II of a unique FML stiffened panel concept to reduce weight and eliminate delamination.   This effort will expand the current GLARE applications from biaxial loading conditions, such as the Airbus-380 upper-fuselage, to CentrAl applications for a wider range of aircraft components, such as the lower wing cover. BENEFIT: Recent developments of advanced hybrid metallic structural concepts have been extremely promising for durable light-weight and ultra-long fatigue life large transport aircraft.  The Alpha STAR team (Alcoa, SWRI, and Virginia Tech) proposes to extend the validated Fiber Metal Laminate (FML) high fidelity analytical capability from GLARE to CentrAl  FML concepts, as well as develop the necessary robust design optimization techniques.  Candidate ultra-long life approaches will be conceptualized and demonstrated on aerospace structural components. A building block verification strategy will be conducted. Observed test data will be compared with analytical predictions for unnotched/notched coupons under service loading conditions; static, fatigue crack initiation/propagation/residual strength, and thermal fatigue.  In Phase I, the team will validate the analytical tools with 5 stringer panel fuselage/lower wing test data under static and fatigue spectrum loadings. Our effort will lead to a robust design development and demonstration in Phase II of a unique FML stiffened panel concept to reduce weight and eliminate delamination.   This effort will expand the current GLARE applications from biaxial loading conditions, such as the Airbus-380 upper-fuselage, to CentrAl applications for a wider range of aircraft components, such as the lower wing cover.)

* information listed above is at the time of submission.

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