High temperature titanium hybrid composite laminates are promising candidates for aerospace applications. They consist of thin sheets of titanium adhesively bonded together with a high temperature polymer resin that contains high or intermediate modulus fibers. This structure is capable of extended use at elevated temperature while exhibiting improved damage resistance. In this work the effect of several different combinations of constituents is examined analytically. Two titanium alloys are used, Timetal 21S and Ti-15-3, both of them are metastable beta alloys. Polymer resins LARC-IA and LARC-IAX are used as matrix material filled either with boron or carbon fibers (Carbon HM, Carbon IM) at a fraction of 20vol% to 70 vol%. It is shown that the higher the fiber volume fraction is the greater is the moduli and the strength. Both boron and intermediate modulus carbon fibers look promising. The combination of fibers and fiber volume fraction must be such that the polymer matrix composite has a higher modulus than that of the titanium in order to improve the benefits of HTCL (Hybrid titanium composite laminates). The relative stiffness and strengths of unidirectional and cross-plied HTCL with fiber volume fraction in the PMC of 50 % have been measured. Alternating 0 and 90 PMC layers between the metallic sheets lead to a more isotropic mechanical behavior of the composite. The titanium layers make the HTCL much more isotropic than it would otherwise be using just an unidirectional PMC. The HTCL is nearly as stiff in the longitudinal direction as the PMC but is over 10 times stiffer in the transverse direction. off-axis plies
High temperature hybrid titanium composite laminates: An early analytical assessment
Hochtemperaturfeste hybride Titanverbundlaminate: Eine frühzeitige analytische Einschätzung
Applied Composite Materials ; 3 , 6 ; 379-390
1996
12 Seiten, 8 Bilder, 3 Tabellen, 15 Quellen
Article (Journal)
English
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