Method of making a fiber reinforced ceramic glass composites having tailored coefficient of thermal expansion
AssigneeHughes Aircraft Company
InventorsRobert W. Seibold, Bruce W. Buller, James O. Gibson
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Abstract
Improved fiber reinforced composites having near zero coefficients of thermal expansion are described. The improved composites include reinforcing fibers and matrix material in which gap structures which exist within the composite are filled with a bonding agent. The reinforcing fibers can be unidirectionally, bidirectionally or multidirectionally oriented within the matrix material and articles fabricated from the improved composite have reduced coefficients of thermal expansion in directions transverse to the orientations of the fibers. This improvement makes these improved composites useful for fabricating high energy laser mirror substrates.
Claims7
A method for preparing improved fiber reinforced composites having a tailored coefficient of thermal expansion, said method comprising the steps of:
- (a) forming a preform comprising a matrix material in a fugitive binder and selected fibers;
- (b) partially consolidating said preform by exposure to an elevated temperature having a maximum of 1523.degree. K. (1250.degree. C.) and an elevated pressure having a maximum of 13.1 MPa (1900 psig) to remove said fugitive binder and form a partially consolidated preform;
- (c) completing consolidation of said partially consolidated preform by exposure to an elevated temperature having a maximum of 1713.degree. K. (1440.degree. C.) and an elevated pressure having a maximum of 103 MPa (15,000 psig) to form a consolidated composite;
- (d) cooling said consolidated composite whereby gap structures of about 300 to 1,000 angstroms in size form in said composite between said matrix material and said fibers, and within said fibers;
- (e) impregnating said composite having said gap structures with a bonding agent, said bonding agent comprising about 0.5 to 5 volume percent of said composite;
- (f) treating said impregnated composite to cure said bonding agent and bond said fibers and said matrix material.
A method for preparing an improved fiber reinforced composite having a tailored coefficient of thermal expansion, said method comprising the steps of:
- (a) forming a slurry of a precursor of a matrix material in a fugitive binder;
- (b) coating said slurry on selected fibers to form prepreg tapes;
- (c) drying said prepreg tapes;
- (d) forming said dried prepreg tapes into a desired shape, to form shaped prepregs;
- (e) stacking said shaped prepregs to form a billet preform;
- (f) partially consolidating said billet preform by application of pressure of up to a maximum of 13.1 Mp (1900 psig) and heat at temperatures of up to a maximum of 1523.degree. K. (1250.degree. C.) to remove said fugitive binder and form a partially consolidated billet preform;
- (g) completing consolidation of said partially consolidated billet preform by application of pressure of up to a maximum of 103 Mp (15,000 psig) and temperatures of up to a maximum of 1713.degree. K. (1440.degree. C.) to form a consolidated composite;
- (h) cooling said consolidated composite whereby gap structures having a size of about 300-1,000 angstroms form in said composite between said matrix material and said fibers, and within said fibers;
- (i) impregnating said composite having said gap structures with a bonding agent comprising about 0.5-5 volume percent of said composite;
- and
- (j) treating said impregnated composite to bond said fibers and said matrix material.
Dependencies are inferred from the claim text.