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Titanium-polymer hybrid laminates
| Details |
Inventors: Westre, Willard N.; Allen-Lilly, Heather C.; Ayers, Donald J.; Cregger, Samuel E.; Evans, David W.; Grande, Donald L.; Hoffman, Daniel J.; Rogalski, Mark E.; Rothschilds, Robert J.;
Assignee: The Boeing Company (Seattle, WA)
Primary Examiner: Zimmerman; John J.
Assistant Examiner: LaVilla; Michael
Attorney, Agent or Firm: Christensen, O'Connor, Johnson & Kindness PLLC
The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like. |
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DETAILED DESCRIPTION The invention provides hybrid laminates, including layers of titanium alloy foil alternating with layers of a polymeric matrix with reinforcing fibers embedded therein, that form the skin (e.
g.
, fuselage, wings, vertical and horizontal stabilizers, and strakes) of a supersonic civilian aircraft.
The laminates possess high strength-to-weight ratio, modulus, fatigue resistance, and have outstanding thermal-mechanical endurance properties.
Moreover, crack propagation is very slow, compared to monolithic titanium alloys, so that the life span of the aircraft is enhanced.
The laminates dent in a manner similar to metals allowing detection of damage before significant deterioration of physical properties occurs.
Moreover, since the outer surfaces of the hybrid laminates are of titanium alloy foil, the laminates are resistant to fuel and other solvents that may otherwise adversely affect a polymeric composite.
In addition, the polymeric composite layers of the hybrid laminates are protected from oxidation, water ingress, and the deleterious effects of ultraviolet light by the outer covering of titanium alloy foil.
The hybrid laminates of the invention preferably include a central layer of a core structure covered on both sides with layups that include layers of titanium alloy foil with at least a one-ply layer of a polymeric matrix composite interposed between each foil layer, to produce a symmetrical laminate.
The layers of metallic foil are preferably about 0.
01 to about 0.
003 inches thick, and made of a beta titanium that has been heat-treated to a yield strain of greater than about 1%.
The layers of polymeric composite are made up of one or more plies, each layer is about 0.
005 to about 0.
03 inches thick.
The preferred organic polymeric composite is formed from a prepreg in the form of a tape of continuous parallel reinforcing fibers coated with a resin to form a continuous strip.
Thus, when the prepreg is laid down to form a composite ply, each composite ply includes a matrix of a resin (that is resistant to the high temperatures encountered during supersonic flight) reinforced with parallel fibers
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