Date of Award

12-2013

Document Type

Thesis - Open Access

Degree Name

Master of Science in Aerospace Engineering

Department

Aerospace Engineering

Committee Chair

David J. Sypeck, Ph.D.

First Committee Member

Frank Radosta, Ph.D.

Second Committee Member

Dae Won Kim, Ph.D.

Abstract

An investigational study was conducted into the tensile and impact behavior of Fiber Metal Laminates by combining 5052 alumintrm mesh or2024-T3 aluminum sheets,2.47 N (8.9 oz) or 6.67 N (24 az) ShieldStand® S fiberglass, and Hysol EA 9313 epoxy. Testing was performed under the guidelines of ASTM D3039-00 utilizing an lnstron 8802 Servohydraulic Materials Testing Instrument for tensile tests and ASTM D3763-06 utilizing an Inston 9250 HV Dynatup Impulse Impact Testing System for impact tests. Samples were strained at arate of 2 mrn/min for tensile tests and impacted with enetgies of 10 to 40 J in l0 J increments for impact tests. It was found that the 6.67 N Q4 oz) ShieldStand ® S with 2024-T3 aluminum alloy sheet samples perforrred best when compared to the other fabricated sarrples. When compared to GLARE 3 there was a 24.7o/o decrease in uttimate terrile steagth with 6.07% decrease in ultimate shain. 6.67 N Q4 oz) ShieldStand® S with 5052 aluminum mesh sarrples were extremely flexible, had the same density and stress-sfiain curve shape as the fiberglass/epoxy only samples, but behaved like a fiber metal taminate when impacted. Though not as strong wlrcn compared to GLARE 5, this material can be used advantageously to create complex shapes aod is more cost effective to manufacture.

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