Unlock instant, AI-driven research and patent intelligence for your innovation.

Solid rocket engine composite skirt and shell integration formation method

A technology of solid rockets and molding methods, which is applied to other household appliances, household appliances, household components, etc., can solve the problems of large shell material waste, high equipment requirements, unsuitable fiber strength, etc., and achieve strong repeatability, Improve production efficiency, facilitate installation and disassembly

Active Publication Date: 2020-01-24
湖北三江航天江北机械工程有限公司
View PDF6 Cites 9 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The separate molding method is to make a cylinder first, then process the cylinder and the shell according to the requirements, and then use the bonding method to fit the skirt onto the shell; this method is very destructive to the integrity of the fiber and is not suitable for the fiber. strength play
One of the overall molding methods is to cover the dummy head after the shell is wrapped around the longitudinal layer. The dummy head has a cylindrical section, that is, the skirt, which is wound as a whole according to the process requirements of the skirt, and the head and the barrel are cut off after winding. A section of excess yarn tape, only retaining the skirt; this method wastes a lot of material for large shells
Another method of overall molding is the winding and layering scheme, that is, after the shell is wound with the longitudinal layer and part of the hoop layer, the composite skirt is made, and the skirt is formed by hoop winding and laying prepreg tape; the material of this method Small waste, good dimensional stability, but high requirements for equipment and complicated molding process

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Solid rocket engine composite skirt and shell integration formation method
  • Solid rocket engine composite skirt and shell integration formation method
  • Solid rocket engine composite skirt and shell integration formation method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0034] Such as figure 1 As shown, the present invention discloses a composite skirt mold, which includes a skirt tool base 3.1, a skirt combination mold 3.2, a skirt flange compression plate 3.3, a skirt tool compression nut 3.4, a bearing 3.5, a skirt tool positioning key 3.6, Skirt flange compression plate compression bolt 3.7, skirt combination mold positioning pin 3.8, skirt combination mold set screw 3.9; wherein, the skirt combination mold 3.2 includes more than one skirt combination module 3.21, and each adjacent skirt combination module 3.21 There is no gap between the sides and form a skirt combination mold 3.2, at the same time, combine figure 2 It can be seen that the skirt combination mold 3.2 is positioned and installed on the skirt tooling base 3.1 through the skirt combination mold positioning pin 3.8 and the skirt combination mold set screw 3.9 in sequence to form the skirt tooling. The skirt frock can be positioned and installed on the mandrel 1 through the ...

Embodiment 2

[0037] to combine image 3 As shown, the present invention also discloses a manufacturing method for integrally forming the solid rocket motor composite skirt and shell by using the above composite skirt mold, which includes winding the longitudinal layer and part of the circumferential layer along the mandrel 2 to form the shell 4, and then The shell 4 is fitted with a detachable composite skirt mold 3 along the front and rear ends of the mandrel 1 to make a composite skirt 5, and the composite skirt 5 is directly paved with prepreg along the shell 4 and the detachable composite skirt mold 3. The material is made into a shape, which specifically includes the following steps:

[0038] 1) Complete the longitudinal layer and part of the hoop layer winding according to the designed casing winding level to make the casing; in this embodiment, 1 cycle of longitudinal winding + 1 to 2 layers of hoop winding + 1 cycle of longitudinal winding + 1 ~ The two layers of hoop winding are ...

Embodiment 3

[0047] The integrally formed composite skirt and shell prepared in the above examples are tested, such as hydrostatic inspection, non-destructive testing, etc. The hydraulic inspection pressure is usually 6MPa-12MPa without leakage, and then the skirt and its connection with the shell are subjected to ultrasonic testing. C-scan or X-ray inspection requires that the inside of the skirt and its bonding surface have no defects such as debonding and delamination.

[0048] It can be seen from the above examples that the process designed by the present invention has strong operability and greatly improves production efficiency, and at the same time, the qualified rate of products obtained through the process is high and meets relevant standards.

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention discloses a solid rocket engine composite skirt and shell integration formation method and belongs to the technical field of mechanical assembly technologies. The method comprises the steps that a vertical layer and a partial annular layer are wound along a core mold to form a shell, a detachable composite skirt mold sleeves the shell along the front and rear ends of a core shaft tomake a composite skirt, the composite skirt is made and formed in the mode that a prepreg is directly laid on the detachable composite skirt mold along the shell, and the detachable composite skirt mold comprises a skirt tool base, a skirt combination mold and a skirt flange compression disc. According to the formation method, by using the characteristic that the composite skirt mold is convenientto install and detach, the production efficiency is improved.

Description

technical field [0001] The invention relates to a molding process of a rocket motor casing, which belongs to the technical field of mechanical assembly technology, in particular to an integrated molding method of a solid rocket motor composite skirt and casing. Background technique [0002] The shell connecting skirt of the solid rocket motor is an integral extension of the shell, which is used to realize the connection between the shell stages or with other components, and it must withstand various loads such as axial pressure, bending moment, shear, and internal pressure, etc. The situation is more complicated. How to simplify the molding process and improve its performance without increasing the quality of the skirt is crucial to the improvement of the performance of the entire engine casing. With the development of material science, composite material connecting skirts have gradually replaced metal connecting skirts because of their high mass ratio, high reliability, sho...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
IPC IPC(8): B29C70/34B29C70/54B29L31/30
CPCB29C70/34B29C70/54B29L2031/3097
Inventor 黄泽勇李一洋王连伟魏虹
Owner 湖北三江航天江北机械工程有限公司