Composite material, useful for production of thermal protective coatings of propellants, where composite material is made of cross-linked thermosetting composition, which comprises organic thermosetting matrix and fibrous reinforcements

摘要

The composite material formed from a cross-linked thermosetting composition at temperature, is claimed. The composition comprises an organic thermosetting matrix consisting of silicone resin mixed with refractory fillers, and fibrous reinforcements formed by mineral or ceramic fibers. The silicone resin is two-component silicone resin comprising a polymer and crosslinking agent, and is cross-linked through a polyaddition process. A weight proportion of the silicon resin and the refractory fillers in the thermosetting organic matrix is 80-82% for resin and 20-18% for refractory fillers. The composite material formed from a cross-linked thermosetting composition at temperature, is claimed. The composition comprises an organic thermosetting matrix consisting of silicone resin mixed with refractory fillers, and fibrous reinforcements formed by mineral or ceramic fibers. The silicone resin is two-component silicone resin comprising a polymer and crosslinking agent, and is cross-linked through a polyaddition process. A weight proportion of the silicon resin and the refractory fillers in the thermosetting organic matrix is 80-82% for resin and 20-18% for refractory fillers. A weight proportion of the refractory fillers and the fibrous reinforcements is, after curing the composition, 66-70% for refractory fillers and 34-30% for fibrous reinforcements. The refractory fillers of the organic matrix are constituted by a mixture of a reinforcement material in powder form. The fibrous reinforcements of the composition are made of short fibers of silicon carbide that form two groups, where a first group of fibers has an average length of 6 mm and a second group of fibers has an average length of 1 mm. An independent claim is included for a process for forming a composite material.