Multi-ring-groove explosive type mechanical forming core mold for solid rocket engine

Abstract

The invention provides a multi-ring-groove explosive type mechanical forming core mold for a solid rocket engine. According to the multi-ring-groove explosive type mechanical forming core mold, a plurality of through holes are annularly and evenly distributed in the side walls of cylinder section umbrella disc fixing actuator cylinders, bolts are arranged in the through holes, rotating shafts arearranged in the centers of the actuator cylinders and rotates to push the bolts out of the through holes to fix umbrella discs, a plurality of axial bulges which are annularly and uniformly distributed are additionally arranged at the positions, on the side walls of the cylinder section umbrella disc fixing actuator cylinders, of wing slot umbrella disc fixing actuator cylinders, a main core moldbody and the cylinder section umbrella disc fixing actuator cylinders are coaxially and alternately connected and then are connected to the wing slot umbrella disc fixing actuator cylinders, and the rotating shafts of the cylinder section umbrella disc fixing actuator cylinders are fixedly connected to the rotating shafts of the wing slot umbrella disc fixing actuator cylinders. According to the multi-ring-groove explosive type mechanical forming core mold, on the premise that the filling fraction is guaranteed, multi-ring-groove pre-embedded ablative device forming is realized, and thereforerepeated mounting and dismounting of a tool are reduced, and the working efficiency is improved.

Description

technical field [0001] The invention relates to solid rocket motor technology, in particular to a charge forming technology. Background technique [0002] The working environment of the solid rocket motor is relatively harsh, the temperature adaptability of the engine is relatively wide, and the performance requirements are relatively high. It requires a high-loading charge structure design. The high-loading charge structure generally has a relatively large stress. The stress relief structure becomes the key technology of the engine. The structure of the engine can be formed by adopting the radial groove charge structure. [0003] The application of radial annular groove charge structure abroad is earlier, and the corresponding technology is relatively mature. The engines that use stress relief groove charge abroad include American TU-780 engine, AIM-120 engine and RAM missile engine, and foreign radial annular groove The groove structure mainly adopts three methods: (1) m...

AI Technical Summary

Problems solved by technology

Disadvantages of each forming process: (1) The forming tool formed by mechanical processing has a complex structure and high failure rate, and during the propellant turning process, it is easy to cause the propellant to frictionally generate heat and ignite the propellant; (2) The pre-embedded ablation device The disadvantage is that it can only form a single-ring groove, and cannot form a multi-ring groove structure; (3) the molding tooling structure of the pre-embedded ablation disassembly device is complicated, and it is installed first each time, and the device is disassembled after the propellant solidifies, so the work efficiency is low; (4) ) uses a deformable structure to form a multi-ring groove structure, and the deformable structure uses a shape memory alloy material. The number of repeated operations depends on the performance of the shape memory alloy material, and the reliability is low, and the number of repeated uses is limited.

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