Manufacturing Method Of Rocket Engine Nozzle Bonding And Clamping Device

1. The present invention relates to the field of processing and manufacturing of aerospace equipment, in particular to a rocket engine nozzle bonding and clamping device.

Background technique:

2. The nozzle is the energy conversion device of the rocket engine. It effectively converts the gas energy generated by the combustion chamber into kinetic energy by controlling the expansion of the exhaust gas, thereby providing thrust. The nozzle is usually composed of the front section of the nozzle, the rear section of the nozzle, the throat lining, and the tail section. Metal lining (diffusion section), throat lining and front and rear sections are connected by bonding process. The adhesive used is a room temperature curing epoxy adhesive. There are two curing methods. The ambient temperature is not lower than 15°C for 7 days, or the oven is heated to 70-75°C for 2 hours. Usually, in order to improve efficiency and production capacity, an oven is used. The curing method, during the curing process, must maintain a certain bonding pressure, otherwise there may be local poor bonding or debonding.

3. The published patent (cn113799031a) discloses a combined clamping device for the bonding of shell linings. By applying pressure plates and pull rods at both ends of the shell, the non-metallic surface is squeezed by tensile force. pressure. This method is a commonly used process in traditional rocket nozzles, and can well solve the nozzle assembly process.

4. However, with the advancement of technology, the nozzle structure tends to be diverse. For complex and diverse structures, it is often necessary to perform secondary extrusion and fixed installation, but the current clamping device cannot meet the needs. The structure of the assembly often makes it impossible to accurately locate the assembly, and the assembly can move in a large range, which may lead to

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