Regeneratively cooled rocket combustion chamber and thrust novel assembly

Claim 1

An elongated and hollow rocket combustion chamber or thrust nozzle assembly, comprising: a first electroformed layer having a substantially uniform thickness and means defining a plurality of continuous and uninterrupted longitudinally extending alternating ribs and recesses on an inner surface thereof extending continuously along said assembly parallel to a longitudinal axis thereof, the outer surface of said first layer having continuously longitudinally extending alternating ribs and recesses thereon corresponding to the locations of said ribs and recesses on said inner surface thereof, said ribs on said inNer surface corresponding in location to the location of said recesses on said outer surface and said recesses in said inner surface corresponding in location to the location of said ribs on said outer surface; and a second layer of substantially uniform thickness on said outer surface of said first layer and being bonded to said first layer, said bond of said second layer to said first layer being at the peak of said ribs on said outer surface of said first layer to thereby define a plurality of continuous and uninterrupted longitudinally extending passageways extending parallel to said longitudinal axis of said assembly and separate from the interior of said assembly.