Patent ID: 7293403

Claim:
A process for manufacturing a combustion chamber for a rocket drive, comprising: producing a fibrous structure comprising layers of carbon-containing fibers which form a three-dimensional matrix; producing a ceramic matrix composite material by feeding silicon into said fibrous structure to form a silicon carbide matrix; and making at least one composite material jacket of said combustion chamber from said composite material; wherein, said producing step comprises forming first, second and third layers of fibers or bundles of fibers, wherein fibers of said first layer extend in a first direction in space; fibers of said second layer extend in a second direction in space; and fibers of said third layer extend in a third direction in space; and wherein said first, second, and third layers penetrate each other at least partially; and said forming of first, second and third layers includes separating said fibers or bundles of fibers of the respective layers from each other such that in each layer, fibers or bundles of fibers of another layer can be disposed in resulting spaces.