Ceramic matrix composite and method for changing the dielectric properties of a ceramic matrix composite

Abstract: A method for changing the dielectric properties of a polymer impregnated and pyrolyzed ceramic matrix composite is disclosed. The polymer impregnated and pyrolyzed ceramic matrix composite can be used in aircraft and turbine engines. The polymer impregnated and pyrolyzed ceramic matrix composite comprises a ceramic matrix, a reinforcing fiber and at least 1 additive used to change dielectric properties (dielectric constant and loss factor). The additive can be a low dielectric constant material having a dielectric constant in the range of 1 to 7.5. The low dielectric constant material can be an oxide such as silica or aluminosilicate or a non-oxide such as silicon nitride, boron nitride or silicon carbide. The low dielectric constant material can be incorporated in the ceramic matrix as a filler. The low dielectric constant material may be incorporated in a uniform array of holes fabricated in the polymer impregnated and pyrolyzed ceramic matrix composite.

Description: This invention is a method for changing the dielectric properties of a polymer impregnated and pyrolyzed ceramic matrix composite (CMC). More particularly, this invention relates to a CMC with improved chemical, electrical and mechanical properties and a method for its fabrication. The CMC can be fabricated with a dielectric constant and loss factor that permits it to be used in aircraft and turbine engines. U.S. Patent 4,983,422 discloses a ceramic composite with a low dielectric constant and high mechanical strength. The composite is made from a liquid aluminum oxide precursor and a reinforcement fabric. The method for producing the ceramic composite comprises introducing the precursor into a reinforcement fabric, curing the precursor to set the desired geometry and converting the cured precursor to an aluminum oxide ceramic by pyrolysis. U.S. Patent 5,198,302 teaches a fiber reinforced ceramic matrix composite formed from a preform comprising silicon nitride fibers coated with boron nitride and alumina and a matrix material. When the preform is heated in an oxidizing atmosphere essentially free of water vapor, a composite with low dielectric loss and high strength is produced. U.S. Patent 5,318,930 discloses a fiber reinforced silicon carboxide composite with adjustable dielectric properties. The dielectric constants of the composites are adjusted by varying the reinforcing fibers and the carbon content of the black glass matrix. U.S. Patent 5,601,674 describes a method for making a fiber reinforced ceramic matrix composite that is oxidation stable. The method comprises heating a matrix mixture slurry interspersed about reinforcing fiber in an oxidizing atmosphere to yield a crystalline ceramic phase. However, the above composites contain oxide matrix materials which suffer from insufficient capability to retain mechanical strength at high process temperatures. One object of this invention is to provide a ceramic matrix composite that will withstand repeated exposure to high process temperatures (greater than 1,000°C.). A further object of this invention is to provide a ceramic matrix composite with low dielectric constant and loss factor, high mechanical strength, and low oxidation potential at high working temperatures in air. This invention relates to a polymer impregnated and pyrolyzed ceramic matrix composite (CMC) having improved dielectric properties and a method for its fabrication. The CMC comprises (a) reinforcing fibers capable of retaining their mechanical strength after processing at temperatures greater than 1,000°C; (b) a ceramic matrix derivable from a curable preceramic polymer; and (c) at least one additive to change the dielectric properties and loss factor of the ceramic matrix composite. This invention further relates to a method of changing the dielectric properties of said CMC. The dielectric properties can be changed by incorporating at least one additive having dielectric properties different from the original ceramic matrix and reinforcing fiber. The additive can be incorporated in the CMC by fabricating a uniform array of holes in the CMC, during or after the process of fabricating the CMC, and filling the holes with the additive. It is also within the scope of the present invention to both incorporate the additive into the ceramic matrix and to fill it into the uniform array of holes wherein the used additives are the same or different materials. The additive that is incorporated in the ceramic matrix is preferably a ceramic powder. U.S. Patent 5,707,471 discloses suitable reinforcing fibers, ceramic matrices, and methods for their preparation to be employed in this invention and need not be further repeated herein. The reinforcing fibers that may be used herein are high tensile modulus fibers that are compatible with the interfacial coatings and ceramic matrices described herein. These fibers must retain their mechanical strength after repeated process steps at temperatures of at least 1,000°C., preferably at least 1,300°C. Suitable fibers are known in the art, are commercially available, and more fully disclosed in U.S. Patents 5,707,471 and 5,279,780. Examples of suitable fibers include silicon carbide, silicon nitride, silicon carbide deposited on a carbon core, aluminum borate, aluminum oxide, silicon oxide, silicon carbide containing titanium, silicon oxycarbides, silicon oxycarbonitrides and carbon. Silicon carbide fibers are preferred because they can withstand processing temperatures of 1,300°C. or greater. Generally, these fibers have a modulus greater than 100 GPa, preferably greater than 150 GPa. The fibers may contain any number of filaments per tow and typically have a diameter in the range of 5 to 500 micrometers. Examples of specific fibers include NICALON® and HI-NICALON® fibers, which are silicon oxycarbide fibers with diameter of 10 to 20 micrometers manufactured by Nippon Carbon; SCS-6® fibers comprising silicon carbide deposited on a carbon core with diameter of about 143 micrometers, which are manufactured by Textron; NEXTEL® 312, NEXTEL® 440, NEXTEL® 480, NEXTEL® 610 and NEXTEL® 720 fibers, which are fibers containing oxides of aluminum, boron, and silicon with diameters of 10 to 12 micrometers manufactured by 3M; SiO 2 fibers with diameter of 8 to 10 micrometers manufactured by J.P. Stevens; Al 2 O 3 -SiO 2 fibers with diameter of 9 to 17 micrometers manufactured by Sumitomo, TYRRANO® fibers, which are silicon carbide fibers containing titanium with diameter of 8 to 10 micrometers manufactured by Ube; and silicon carbide fibers with diameter of 6 - 10 micrometers manufactured by Textron. The fibers can also have interfacial coatings. Suitable interfacial coatings are also disclosed in U.S. Patent 5,707,471. Examples of interfacial coatings include carbon, boron nitride, a two-layer coating comprising silicon nitride on top of boron nitride, silicon carbide, silicon nitride, aluminum nitride and combinations thereof. These interfacial coatings are typically 0.05 to 1.0 micrometers thick. The above fibers may be used in nearly any length or arrangement in the ceramic matrix in nearly any manner desired to reinforce the CMC. Fiber reinforcement can take various forms, such as continuous or discontinuous. The continuous fibers may be woven into a 2-dimensional fabric or cloth using different weaves such as plain, satin, leno and crowfoot. These fibers may also be shaped as a 3-dimensional pre-form. Other forms of continuous fiber reinforcement are exemplified by braids, stitched fabrics and unidirectional tapes or fabrics. Discontinuous fibers suitable for this invention include milled fibers, whiskers, chopped fibers and chopped fiber mats. A combination of continuous and discontinuous fibers may also be used in the CMC. The ceramic matrix of the CMC is derived from a curable preceramic polymer. "Curable" means that the polymer can be deep section infusibilized (cured) in the composite under moderate conditions by means such as mild heat, radiation, curing catalysts or curing agents or combinations thereof. Curability inhibits the composite from delaminating in subsequent process steps. Curable preceramic polymers are known in the art and can be manufactured by known techniques such as those disclosed in U.S. Patent 5,707,471. Examples of suitable preceramic polymers include polysilazanes, polycarbosilanes, polysiloxanes, polysilanes and polymetallosiloxanes. Polysilazanes are preferred. Suitable polysilazanes include hydridopolysilazanes, vinyl-modified polysilazanes, silacyclobutasilazane, vinyl-modified poly(disilyl)silazanes and borosilazanes. Preferred polysilazanes include boro-modified polysilazanes and vinyl-modified polysilazanes. Other curable silicon-containing preceramic polymers can also be used in this invention. One skilled in the art knows how to readily select suitable curable preceramic polymers and methods for their preparation from the above disclosure. Curable preceramic polymers having a ceramic char containing at least 50 wt% silicon are preferred for the present invention. To determine the weight percent of silicon in the char, the curable preceramic polymer is heated in an inert atmosphere to a temperature of 1,200°C. The resulting char is next analyzed to determine the quantity of elements present and the weight percent of silicon is determined therefrom. The additive used to change dielectric properties herein is a ceramic material, preferably a ceramic powder; air; or a material of any other convenient form, depending on whether it is incorporated into the ceramic matrix or incorporated in the CMC by fabricating a uniform array of holes in the CMC and then filling the holes with the material. Ceramic powders can be used in combination with other additives, for example a material that can be filled into the uniform array of holes. The additive can be a high dielectric constant material, a low dielectric constant material, or a combination thereof. High dielectric constant materials typically have dielectric constants greater than 7.5. For example, silicon carbide is a suitable high dielectric constant material having a dielectric constant of 10. The low dielectric constant material used herein usually has a dielectric constant in the range of 1 to 7.5. This material is selected from the group consisting of air (which has a dielectric constant of about 1), oxides, and non-oxides. Suitable oxides typically have a dielectric constant in the range of 3.6 to 6.6 and include silica, which has dielectric constant of 3.6 to 3.8, and aluminosilicates, such as mullite which has dielectric constant of about 6.6. The low dielectric constant material is preferably a non-oxide having a dielectric constant in the range of 4.0 to 7.5. Suitable non-oxides include silicon nitride, which has a dielectric constant of 6.5 to 7.5, and boron nitride, which has a dielectric constant of about 4.0. Low dielectric constant materials used herein preferably have dielectric constants in the range of 5.5 to 7.5. Examples of preferred additives include silicon nitride, silicon carbide and boron nitride. Silicon nitride is most preferred. Usually, the additive comprises up to 70 wt% of the ceramic matrix, preferably 20 to 70 wt%, and more preferably 25 to 40 wt%. If the amount of additive in the ceramic matrix is less than 20 wt%, the ceramic matrix will be highly cracked on processing. If the amount of additive in the ceramic matrix is more than 70 wt%, it will be difficult to consolidate the CMC due to an inadequate preceramic polymer content. This invention further relates to a method for fabricating the CMC. The method comprises fabricating a CMC comprising reinforcing fibers and a ceramic matrix. The uniform array of holes may then be fabricated in the CMC. At least one additive used to change the dielectric properties in the CMC is included. However, the ceramic matrix of the CMC must have open porosity of from 2 to 20 vol%. The CMC herein can be generally fabricated by the method disclosed in U.S. Patent 5,707,471. In a preferred embodiment, our composite is fabricated by impregnating the reinforcing fiber with a matrix mixture comprising a curable preceramic polymer and optionally an additive to form a pre-preg; and by then pyrolyzing this pre-preg to form a CMC optionally having at least one additive incorporated herein to modify dielectric properties. The method of the present invention is performed under an inert atmosphere, where "inert" means containing less than 500 ppm oxygen. A suitable inert atmosphere comprises nitrogen, argon, helium, and combinations thereof. The inert atmosphere prevents formation of oxides from the curable preceramic polymer during processing. Impregnating the reinforcing fiber(s) with the matrix mixture can be performed, for example, by a solution route or a melt route. In the solution route, the matrix mixture is formed by mixing the curable preceramic polymer and any additives in an organic solvent. The solvent preferably has a vaporization point lower than 125°C. at ambient pressure and preferably also contains less than 1 wt% water. Examples of suitable organic solvents include aliphatic hydrocarbons, such as hexane and heptane, and aromatic hydrocarbons, such as toluene and benzene. The concentration of curable preceramic polymer in the solution is preferably 30 to 60 wt%. In the melt route, the matrix mixture is formed by heating the curable preceramic polymer to a temperature above its melting point but below the temperature required to cure said polymer. Additives may also be mixed into the molten polymer. The reinforcing fibers are then impregnated with the matrix mixture by any convenient means. For example, the reinforcing fibers can be immersed in the matrix mixture, sprayed with the matrix mixture, held under a stream of the matrix mixture or vacuum infiltrated with the matrix mixture. Following impregnation, the excess matrix mixture is removed. If the solution route was used, the solvent is conveniently removed from the impregnated fibers. The solvent can be removed, for example, by allowing the solvent to evaporate in air under atmospheric conditions, by application of mild heat or by use of vacuum. The impregnated fibers after solvent removal are commonly called a "pre-preg". The pre-preg is then formed into any suitable composite shape. Thereafter, the composite shape is fully cured or partially cured before pyrolysis. Curing allows the pre-preg to hold its shape during subsequent processing steps. Curing the pre-preg is performed by methods known in the art, such as those disclosed in U.S. Patent 5,707,471. Curing, however, must be carried out at a temperature less than the temperature required for pyrolysis. Typically heating at 50 to 150°C. for 2 minutes to 4 hours is sufficient. The method used for heating is not critical. One skilled in the art knows how to cure a composite shape and the procedure need not be repeated herein. The holes may then be fabricated in the composite shape. Thereafter, the composite shape is pyrolyzed at a temperature between 1,000 and 1,300°C. to form a pyrolyzed composite. If the pyrolysis temperature is greater than 1,300°C., the fibers may not retain their mechanical strength during processing. If the temperature is less than 1,000°C., pyrolysis will not be complete. Generally, the composite initially formed by this method has open porosity of up to 30 vol%. "Open porosity" as used herein means void space inherent in the fabricated composite, but does not include the additional void space of any holes fabricated in the CMC. The pyrolyzed composite may be further reimpregnated with curable preceramic polymer and then pyrolyzed again to further reduce open porosity. This reimpregnation and pyrolysis process may be repeated up to 15 times to adequately densify the CMC, until open porosity decreases to 2 to 20 vol%, preferably 5 to 15 vol% of the composite. If open porosity is more than 20 vol%, then mechanical strength of the CMC will be insufficient for some applications. At higher levels of open porosity, the dielectric constant is lower because more air, which has a dielectric constant of approximately 1, is present in the composite. However, the mechanical strength of the CMC without holes fabricated therein will be optimal at about 15 vol% open porosity. Maximum densification is complete when open porosity is between 2 to 5 vol%. The dielectric properties of a composite that is thus densified are normally a dielectric constant of 8 to 12 and a loss factor of 2 to 4. The dielectric properties of the CMC are further changed by fabricating a uniform array of holes therein, and by filling the holes with an additive having dielectric properties different from the CMC as fabricated. By controlling the size, shape and proximity of the holes and the additives used in the CMC, it is possible to tailor various chemical, electrical and mechanical properties of the CMC, such as mechanical strength, dielectric properties and oxidation potential. The holes may be formed during or after fabrication of the CMC. These holes range in diameter from 0.0254 to 0.318 cm, preferably from 0.0508 to 0.254 cm. When the holes are produced during fabrication of our composite, the CMC will have the further advantage of greater structural capability and mechanical strength because the reinforcing fibers are not cut; they are merely displaced. A method for forming holes filled with an additive during fabrication of our CMC comprises forming a pre-preg around the additive to make the desired composite shape. The composite shape is then cured and pyrolyzed as described above. For example, the additive is formed into a desired shape, such as rods, and thereafter placed in a die. The pre-preg is then formed around the additive in the die to facilitate hole formation. Alternatively, the holes can be produced after fabrication of the CMC by a method such as diamond machining, laser machining and ultrasonic machining. Producing the holes after fabrication allows for our CMC to be processed to a lower amount of open porosity than a CMC without holes, with no adverse impact on the dielectric constant. As the amount of open porosity decreases, the surface area of the composite that will be exposed to air decreases; and, therefore, the oxidation potential decreases. The CMC with holes formed after the CMC is fabricated also has the advantage of lower oxidation potential. Thereafter, the holes can be filled with an additive, as described previously, having a dielectric constant different from that of the fabricated CMC. The additive can be introduced into the holes by various methods, such as sol gel methods, slurry casting, glass frit melting, inserting solid rods of the additive material into the holes or polymer derived methods. The additive can then be heated to a temperature of 1,000 to 1,300°C. to form a stable ceramic material filling the holes in the CMC. If air is used as additive in the holes, filling is accomplished by exposing the ceramic matrix composite comprising the fabricated holes to the atmosphere. The method of fabricating the CMC may further comprise an oxidation step after pyrolysis is complete (i.e., when open porosity is 2 to 20 vol%). The oxidation step comprises heating the CMC to a temperature of 800 to 1,000°C. for 10 to 40 hours in an oxidizing atmosphere. This forms a layer of an oxide material on the surface of our CMC. This layer protects the CMC from further oxidation when used, for example, in an engine or turbine . Further, it also serves to reduce the dielectric constant and loss factor of the CMC by removal of residual carbon in the ceramic matrix. The following examples are intended to further illustrate the invention. Example 1 (not an example of the present invention) Four polymer impregnated and pyrolyzed ceramic matrix composite samples were fabricated using a borohydridopolysilazane resin as the matrix material and NICALON® fibers woven into a fabric. Said fibers were coated with a two-layer interfacial coating comprising silicon nitride on top of boron nitride. Samples 1-1 and 1-3 contained 40 wt% of a silicon nitride additive in the ceramic matrix. Samples 1-2 and 1-4 contained 40 wt% of a silicon carbide additive in the ceramic matrix. The method for preparing the samples was: prepregging, vacuum bagging and autoclave processing and cure followed by a pyrolysis process at elevated temperature. A matrix mixture was made by combining the resin, the additive and a solvent. The mixture was prepared by ball milling for 24 hours to provide adequate mixing and dispersion. The coated fabric was then impregnated with the matrix mixture. The fabric was thereafter air dried for 45 minutes to permit solvent evaporation. The fabric was next cut into the desired ply dimensions, stacked and placed on a flat plate. The stack of plies on said plate were subsequently subjected to a vacuum and placed in an autoclave for compaction and cure. This was carried out by heating to a maximum temperature of 232°C. for 6 hours. After autoclaving, the resulting cured panel was pyrolyzed in a high temperature furnace at a maximum temperature of 1200°C. in an argon atmosphere for 6 hours. After pyrolysis, the resulting CMC samples had open porosity greater than 20 vol%. This porosity was then reduced by carrying out a vacuum re-impregnation of the CMC with a solution of hydridopolysilazane resin in solvent. After re-impregnation, the CMC was pyrolyzed again in the high temperature furnace as described above. This process was repeated until an open porosity of from 2 to 20 vol% was attained. The dielectric constant and loss factor were measured at 10 GHz on the samples 1-1 and 1-2. Samples 1-3 and 1-4 were further heated for an additional 40 hours at 1,000°C. in air to oxidize said samples. Then, the dielectric constant and loss factor were measured with the results reported in Table 1. Dielectric Properties Measured on Samples with Different Additives Non-oxidized After Oxidation Sample # 1-1 1-2 1-3 1-4 Additve Silicon Nitride Silicon Carbide Silicon Nitride Silicon Carbide Dielectric Constant 8.7 12.0 7.1 9.37 Loss Factor 2.02 4.00 3.21 2.55 Example 2 Three CMC samples were fabricated using borohydridopolysilazane resin and silicon carbide additive as the matrix material and silicon carbide fibers (NICALON®). The fibers were coated with a boron nitride interfacial coating. Samples 2-1 and 2-3 had no holes. Sample 2-2 was fabricated with 20% holes. The method for preparing these samples was the same as that used in Example 1. Samples 2-1 and 2-2 were impregnated, cured and pyrolyzed 15 times each. Thereafter, holes were drilled in sample 2-2 by ultrasonic machining (20 vol%). The holes had a diameter of 0.18 cm. Sample 2-3 was impregnated, cured and pyrolyzed only 4 times. Density, open porosity, dielectric constant and loss factor were measured for these samples. For sample 2-2, open porosity refers to the 7.21% open porosity for the CMC, not including the additional porosity provided by fabrication of 20 vol% holes therein. The results are listed in Table 2. Density is reported in units of g/cm 3 . Comparison of Samples with and without Holes Sample # Density Open porosity (vol%) Dielectric Constant Loss Factor 2-1 (no holes) 2.209 6.279 10.43 7.296 2-2 (holes) 2.190 7.21 6.211 2.961 2-3 (no holes) 2.015 15.789 8.896 1.829 Example 3 Sample 3 was prepared by the same method for sample 2-2 in Example 2, except that after pyrolysis was complete and holes were machined, the holes in sample 3 were filled with glass. Dielectric constant and loss factor were measured as in Example 1. Sample 3 was then oxidized by heating to 1,000°C. for 10 hours in air. Dielectric constant and loss factor were measured as in Example 1. Dielectric constant and loss factor were also measured on the glass used to fill the holes. The results are provided in Table 3. Comparison of Samples with Unfilled Holes and Holes Filled with Glass Sample Density (g/cm 3 ) Open Porosity (vol%) Dielectric Constant Loss Factor Glass 2.384 0.393 5.0 0.063 3 (before oxidation) 2.212 7.059 12.0 13.0 3 (after oxidation) 2.178 6.481 10.7 10.9

Claims: A polymer impregnated and pyrolyzed ceramic matrix composite comprising: (a) reinforcing fibers capable of retaining their mechanical strength after processing at temperatures greater than 1.000°C; (b) a ceramic matrix derivable from a curable preceramic polymer; and (c) at least one additive to change the dielectric properties and loss factor of the ceramic matrix composite wherein the additive is (i) filled in a uniform array of holes having a diameter from 0.0254 to 0.318 cm fabricated in the ceramic matrix, or (ii) both incorporated in the ceramic matrix and filled in a uniform array of holes having a diameter from 0.0254 to 0.318 cm fabricated in the ceramic matrix, the additives incorporated in the ceramic matrix and filled in the holes are the same or different materials. The ceramic matrix composite according to claim 1 wherein the additive is selected from the group consisting of low dielectric constant materials having dielectric constants ranging from 1.0 to 7.5, high dielectric constant materials having dielectric constants greater than 7.5, and combinations thereof. The ceramic matrix composite according to claim 2 wherein the additive is air filled in the uniform array of holes. The ceramic matrix composite according to claim 2 wherein the additive is a ceramic material. The ceramic matrix composite according to claim 4 wherein the additive is silicon carbide. The ceramic matrix composite according to claim 4 wherein the additive is a low dielectric constant material selected from oxide and non-oxide materials. The ceramic matrix composite according to claim 6 wherein the additive is an oxide material selected from silica and aluminosilicates. The ceramic matrix composite according to claim 6 wherein the additive is a non-oxide material selected from silicon nitride and boron nitride. A method for fabricating a polymer impregnated and pyrolyzed ceramic matrix composite, wherein the method comprises: (i) impregnating reinforcing fibers capable of retaining their mechanical strength after processing at temperatures greater than 1,000°C with a matrix mixture comprising a curable preceramic polymer and at least one additive to change the dielectric properties and loss factor of said composite to form a pre-preg, (ii) forming a composite shape from said pre-preg, (iii) curing the composite shape, (iv) pyrolyzing the composite shape in an inert atmosphere at a temperature of at least 1,000°C. to form a pyrolyzed composite comprising a reinforcing fiber, a ceramic matrix, and an additive incorporated in the ceramic matrix, (v) impregnating the pyrolyzed composite with the curable preceramic polymer, (vi) pyrolyzing the pyrolyzed composite and curable preceramic polymer from step (v), (vii) repeating steps (v) and (vi) until open porosity of the composite decreases to 2 to 20 vol% to form a polymer impregnated and pyrolyzed ceramic matrix composite; and (viii) fabricating a uniform array of holes having a diameter from 0.0254 to 0.318 cm in the polymer impregnated and pyrolyzed ceramic matrix composite. The method according to claim 9 wherein the array of holes is fabricated by a method selected from diamond machining, laser machining, and ultrasonic machining. The method according to claim 10 wherein the holes are then filled with an additive to change the dielectric properties and loss factor of said composite; the additive being the same or a different additive as incorporated in the ceramic matrix. The method according to claim 11 wherein the additive is incorporated into the holes by a method selected from sol gel methods, slurry casting, glass frit melting, inserting solid rods of the additive into the holes and polymer derived methods. The method according to claim 12 further comprising forming a stable ceramic material filling the holes by heating the composite to a temperature of 1,000 to 1,300°C. after the holes are filled. A method for fabricating a polymer impregnated and pyrolyzed ceramic matrix composite, wherein the method comprises: (i) impregnating reinforcing fibers capable of retaining their mechanical strength after processing at temperatures greater than 1,000°C with a matrix mixture comprising a curable preceramic polymer to form a pre-preg, (ii) forming a composite shape from said pre-preg, (iii) curing the composite shape, (iv) pyrolyzing the composite shape in an inert atmosphere at a temperature of at least 1,000°C. to form a pyrolyzed composite comprising a reinforcing fiber and a ceramic matrix, and (v) impregnating the pyrolyzed composite with the curable preceramic polymer, (vi) pyrolyzing the pyrolyzed composite and curable preceramic polymer from step (v). (vii) repeating steps (v) and (vi) until open porosity of the composite decreases to 2 to 20 vol% to form a polymer impregnated and pyrolyzed ceramic matrix composite; wherein a uniform array of holes having a diameter from 0.0254 to 0.318 cm filled with an additive to change the dielectric properties and loss factor of the ceramic matrix composite is formed during fabrication of the ceramic matrix composite by first forming the additive into a desired shape; placing the shaped additive in a die, and thereafter forming the pre-preg of step (i) around the additive. The method of any of claims 9 to 14 further comprising heating the ceramic matrix composite after step (vii) to a temperature of 800 to 1,000°C. in an oxidizing atmosphere. A method for changing the dielectric properties of a polymer impregnated and pyrolyzed ceramic matrix composite, wherein the method comprises fabricating a uniform array of holes having a diameter from 0.0254 to 0.318 cm in the polymer impregnated and pyrolyzed ceramic matrix composite, which comprises a reinforcing fiber and a ceramic matrix. A method for changing the dielectric properties of a polymer impregnated and pyrolyzed ceramic matrix composite, wherein the method comprises fabricating a uniform array of holes in the polymer impregnated and pyrolyzed ceramic matrix composite, which comprises a reinforcing fiber and a ceramic matrix.

Inventors: BRIDGEWATER TODD JEFFREY, PETRAK DANIEL RALPH, SZWEDA ANDREW, BRIDGEWATER, TODD JEFFREY, PETRAK, DANIEL RALPH, SZWEDA, ANDREW
Applicants: DOW CORNING, DOW CORNING CORPORATION
Application year: 1999
Main classification: C04B35
IPC codes: C04B35, C04B38