Process for the production of regeneratively cooled rocket combustionchambers and thrust nozzle assemblies
Abstract
Abstract A PROCESS FOR THE PRODUCTION OF ROCKET COMBUSTION CHAMBERS AND THRUST NOZZLE ASSEMBLIEES HAVING LENGTHWISE COOLING CHANNELS. THE PROCESS CONSISTS OF THE FOLLOWING STEPS: (1) CUTTING THE NEGAATIVE FORM OF THE COOLING CHANNELS INTO THE SURFACE OF A SUITABLE CORE, (2) GALVANICALLY DEPOSITING A FIRST LAYER ON THE CORE SURFACE TO PROVIDE THE INNER WALL OF THE ROCKET COMBUSTION CHAMBER AND THRUST NOZZLE ASSEMBLY SAID INNER WALL ALSO DEFINING SAID COOLING CHANNELS, (3) FILLING THE COOLING CHANNELS EXTERNALLY WITH AN ELECTRICALLY CONDUCTIVE FILL MATERIAL, AND (4) GALVANICALLY DEPOSITING A SECOND LAYER ON SAID FIRST LAYER AND THE FILL MATERIAL TO PROVIDE A SMOOTH EXTERNAL WALL FOR THE ROCKET COMBUSTION CHAMBER AND THRUST NOZALE ASSEMBLIES.
Inventors
- 👤 K Butter
- 👤 K Knauer
Bibliographic Details
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