Dismounting device and method for heat insulation forming ring of solid rocket engine

A solid rocket and dismantling device technology, applied in the manufacture of tools, hand-held tools, etc., can solve the problems of difficult disassembly, time-consuming and labor-intensive, damage to the shell and heat insulation layer, and achieve the effect of reducing labor intensity and improving disassembly efficiency

Pending Publication Date: 2022-07-15
HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, during the vulcanization process of the heat insulation material, it will be closely matched with the steps of the heat insulation forming ring, making it difficult to disassemble
[0003] Generally, two methods are used to disassemble the forming ring. One is to use a copper hammer to extend into the inner side of the forming ring from the rear opening, and disassemble the forming ring by knocking. Hidden danger
Another kind of dismantling and ejecting ring is matched with the design, but if there is no suitable screw hole on the open end of the shell, this method cannot be used

Method used

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  • Dismounting device and method for heat insulation forming ring of solid rocket engine
  • Dismounting device and method for heat insulation forming ring of solid rocket engine
  • Dismounting device and method for heat insulation forming ring of solid rocket engine

Examples

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Embodiment Construction

[0025] like Figure 1~2 As shown, a dismantling device for a solid rocket motor thermal insulation forming ring comprises a frame 1, a mounting seat 2 is arranged on the frame 1, a mounting frame 3 is arranged on the mounting seat 2, and a telescopic mechanism 4 is arranged on the mounting frame 3, In this embodiment, the telescopic mechanism 4 is a hydraulic cylinder, and the hydraulic cylinder can also be replaced by an air cylinder or the like. The telescopic end of the telescopic mechanism 4 is provided with a claw removal bracket 5, and the claw removal bracket 5 is provided with a claw removal bracket 6. In this embodiment, the number of the removal claws 6 is three, and the tail end of the removal claw 6 is provided with a claw removal bracket. 5. The sliding ring 601 is matched with the sliding ring 601. The sliding ring 601 moves along the claw removal bracket 5, and the position of the claw removal 6 can be adjusted. From 602 , a plurality of jacking rods 7 are arra...

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PUM

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Abstract

The invention provides a solid rocket engine heat insulation forming ring dismounting device and a dismounting method.The dismounting device comprises a rack, a mounting base is arranged on the rack, a mounting frame is arranged on the mounting base, a telescopic mechanism is arranged on the mounting frame, a dismounting claw support is arranged at the telescopic end of the telescopic mechanism, and dismounting claws are arranged on the dismounting claw support; a sliding ring matched with the dismounting claw support is arranged at the tail end of the dismounting claw, the sliding ring is fixed to the dismounting claw support through a puller bolt, a clamping protrusion is arranged at the front end of the dismounting claw, and a plurality of puller rods are arranged on the mounting frame. According to the dismounting device and the dismounting method, the solid rocket engine curing forming ring can be quickly dismounted, the labor intensity of operators is reduced, and the dismounting efficiency is improved.

Description

technical field [0001] The invention belongs to the technical field of manufacturing a solid rocket motor thermal insulation layer, in particular to a disassembly device and a disassembly method for a solid rocket motor thermal insulation forming ring. Background technique [0002] When assembling the solid rocket motor casing and the nozzle, it is necessary to ensure that the size of the insulation layer steps in the opening of the casing meets the design requirements. When forming the inner insulation step of the solid rocket motor, the generally used process is to design a matching metal step forming ring. During the pressurization of the insulation layer, the inner insulation material flows along the size of the forming ring, and forms a suitable size after vulcanization. In the vulcanization process of the thermal insulation material, it will be closely matched with the steps of the thermal insulation forming ring, and it is difficult to disassemble. [0003] There are...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B25B27/00
CPCB25B27/00
Inventor 韩娇程小凯李砚徽周安江鄂鹏飞唐文涛肖观福李凌峰王利明李换朝
Owner HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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