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Split type composite material core mold for winding solid rocket engine shell

A composite material core and engine casing technology, applied in applications, household components, household appliances, etc., can solve the problems of self-heavy core mold, poor shell profile accuracy after molding, and high assembly difficulty, reducing weight and ensuring size. The effect of stability and improving disassembly efficiency

Active Publication Date: 2021-11-16
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the shortcomings of existing mandrels that are too heavy and difficult to assemble, which will lead to poor surface accuracy of the shell after molding, and provide a split-type composite core for solid rocket motor shell winding mold

Method used

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  • Split type composite material core mold for winding solid rocket engine shell
  • Split type composite material core mold for winding solid rocket engine shell
  • Split type composite material core mold for winding solid rocket engine shell

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Experimental program
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Effect test

Embodiment Construction

[0079] Below in conjunction with accompanying drawing and specific embodiment content of the present invention is described in further detail:

[0080] Such as Figure 1-16 As shown, a split-type composite material mandrel for solid rocket motor casing winding, including coaxially installed large-end head 1, barrel section 2, small-end head 3, connecting structure 4 and mandrel shaft system 5 .

[0081] The big-end head 1, the cylinder section 2 and the small-end head 3 are all made of resin-based composite material, and are respectively divided into 11 split molds along the ring direction. The big-end head 1 is divided into eight first big-end split molds 25-32, one second big-end split mold 33, one third big-end split mold 34 and one fourth big-end split mold along the ring direction. The end split mold 35; the cylinder section 2 is divided into eight first cylinder section split molds 36-43, one second cylinder section split mold 44, one third cylinder section split mold ...

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Abstract

The invention discloses a split type composite material core mold for winding a solid rocket engine shell, and overcomes the defects that an existing core mold is too large in dead weight and high in assembly difficulty, and the molded surface precision of the formed shell is poor. The composite material is adopted as the main part of the overall structure of the large split type core mold, the split mold bodies of the large split type core mold are manufactured in the mode that the hot press forming technology and machining are combined, the weight of the large split type core mold is reduced, and the manufacturing efficiency and profile precision of the large solid rocket engine shell are improved.

Description

technical field [0001] The invention relates to the field of manufacturing solid rocket motor casings, in particular to a split-type composite material mandrel for winding solid rocket motor casings. Background technique [0002] The winding mandrel is a mold for the winding and forming of the rocket engine shell, and the shell mandrel technology is a key technology to support the manufacture of large solid rocket motor composite shells. In the face of the new generation of aerospace vehicles in the future, the diameter of the engine casing will reach several meters, and the existing core mold technology cannot meet the requirements. [0003] The existing mandrel structures mainly include all-gypsum mandrel and sand mandrel, assembled gypsum mandrel and sand mandrel, metal skeleton assembled gypsum mandrel and sand mandrel, and all-metal mandrel. [0004] However, gypsum core molds and sand core molds are low in strength and heavy in weight, and are easily deformed and crac...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C33/30B29C33/48B29L31/30
CPCB29C33/305B29C33/485B29L2031/3097
Inventor 校金友周汉雄文立华王时玉徐涛
Owner NORTHWESTERN POLYTECHNICAL UNIV
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