Fiber-based ablative and high temperature pre-preg material
View Patent ↗A fabric-matrix composite structure [ 10] for making parts [ 13] suitable for use in hostile, high-temperature environments, such as rocket exhaust nozzles. The structure [ 10] includes a fabric [ 11] formed of polyacrylonitrile fiber, especially a polyacrylonitrile fiber that has been oxidized, and especially a combination of polyacrylonitrile fibers that have been oxidized to different degrees. The structure [ 10] also includes a binder [ 12] that impregnates the fabric [ 11] . The binder [ 12] might be a phenolic resin. The structure is formed [ 30] , partially cured [ 40] , formed into a product [ 50] , and finish cured [ 60].
1. A method of forming a product for use in ablative conditions, comprising the steps of:
a.) forming a composite structure comprised of a fabric formed of polyacrylonitrile fiber that has been oxidized and said fabric impregnated with a phenolic polymer,
b.) partially polymerizing the polymer to B stage wherein at said B stage, the polymer is physically stable but not fully cross-linked,
c.) forming the structure into the form of a rocket exhaust nozzle, and
d.) carbonizing the composite structure by exposing it to sufficient heat and nitrogen atmosphere.
2. A method of forming a product for use in ablative conditions, comprising the steps of:
a.) forming a pre-preg composite structure of a pre-preg formulation comprised of a fabric formed of polyacrylonitrile fiber that has been oxidized and said fabric impregnated with a phenolic polymer wherein the pre-preg formulation includes a fibrous material that is woven, non-woven, aligned unidirectional fibers, or discontinuous fibers wherein the fibrous material or discontinuous fibers consists of fibers of two different fiber materials consisting of carbon fiber based on polyacrylonitrile (PAN) at a carbon content of 95+/−3% and polyacrylonitrile (PAN) based pre-ox carbon fiber at a carbon content of 60+/−5%,
b.) partially polymerizing the polymer to B stage wherein at said B stage, the polymer is physically stable but not fully cross-linked,
c.) forming the structure into the form of the product,
d.) carbonizing the product,
e.) fully polymerizing the polymer, and
f.) exposing the product to ablative conditions.
3. A method as recited in claim 2 , wherein the fibrous materials or discontinuous fibers are blended into a yarn at a ratio such that the carbon content of the yarn is 82+/−10%.
4. A method as recited in claim 3 , wherein the yarn is manufactured into a substrate that is impregnated with a phenolic resin.
5. A method as recited in claim 4 , wherein the substrate can be woven, non-woven or aligned unidirectional fibers.
6. A method as recited in claim 2 , wherein the phenolic polymer contains particulate fillers, short fibers, plate shaped fillers and/or nanometer-sized fillers.
7. A method as recited in claim 2 , wherein the pre-preg composite structure can be used as broad goods, molding compound, straight tapes or biased tapes.
8. A method as recited in claim 2 , wherein the pre-preg composite structure can be processed into parts via compression molding, vacuum bag molding in oven, vacuum bag molding in autoclave or vacuum bag molding in a hydroclave.
9. A method as recited in claim 8 , wherein the pre-preg composite structure, after processing into parts via the use of compression molding, vacuum bag molding in oven, vacuum bag molding in autoclave or vacuum bag molding in a hydroclave, can be converted from a phenolic impregnated fabric molded structure to a carbon impregnated fabric molded structure (also known as carbon/carbon), via exposure to a minimum of 1200 F. in a nitrogen atmosphere.
10. A method as recited in claim 2 , wherein the phenolic polymer is capable of being formulated with appropriate solvents for impregnation into fibrous woven fabrics, fibrous nonwoven fabrics or aligned unidirectional fibers.
11. A method as recited in claim 2 , wherein the pre-preg composite structure can be molded to a desired thickness and then processed into parts via compression molding, vacuum bag molding in oven, vacuum bag molding in autoclave or vacuum bag molding in a hydroclave.
12. A method as recited in claim 11 , wherein multiple layers of the pre-preg composite structure can be used to achieve the desired thickness.