| 摘要 |
A carbon framework structure for the jet nozzle exhaust pipe (1) for a rocket engine is obtained by coiling, and a flange for fixing the exhaust pipe (1) to the end of the nozzle (2) from the combustion chamber is integrated with a continuous line of fibers of the framework of carbon fibers coiled up in the exhaust pipe (1) . Preferred Features: The flange can be in the form of a conical expansion of the exhaust pipe (1), or can be in the form of a conical extension of the exhaust pipe (1) which comprises an additional folded section for axially receiving screws that fix the flange to the combustion chamber. The jet nozzle exhaust pipe (1) comprises a fixed section and a deployable section (4). An interface connection is located between the sections of the exhaust pipe on a flange at the inlet of the deployable section (4) of the exhaust pipe (1), the flange being integrated with a continuous line of fibers of the framework of carbon fibers coiled up in the deployable section (4) of the jet nozzle. The interface connection comprises an interface ring made of carbon/silicon carbide (C/SiC) on the fixed section (3) of the exhaust pipe (1). Locking tabs distributed at the periphery of the interface connection, and made of C/SiC, are integrated by a machining cutting operation performed on the interface ring once it has hardened. The deployable section (4) of the exhaust pipe (1) comprises an upper segment (5) and a lower segment (6). An interface connection (9) is located between the segments of the jet nozzle at the inlet of the lower section of the jet nozzle having a flange, integrated with a continuous line of fibers in the framework of carbon fibers coiled up in the lower segment (6) of the jet nozzle. One or more of the coiled-up flanges are reinforced by a prefabricated carbon fiber lap. |
