Skirt structure of solid rocket engine shell, skirt assembling tool and skirt installing method

Abstract

The invention relates to a skirt structure of a solid rocket engine shell, a skirt assembling tool and a skirt installing method. The skirt structure comprises at least two skirt petals, and the two circumferential side edges of each skirt petal are each provided with a circumferential connecting structure. The circumferential connecting structures of every two adjacent skirt petals are used in a matched mode and abut against each other in the circumferential direction, so that the multiple skirt petals are connected to form the annular skirt structure. The skirt assembling tool comprises a positioning flange and a plurality of tool assemblies evenly distributed around the center axis of the positioning flange. During installation, the skirt assembling tool and the skirt structure can be directly assembled around a mandrel without taking down a solid rocket engine shell prefabricated product from winding equipment, , and the skirt installing work is completed. The multiple skirt petals can be machined at the same time, the skirt installing work can be completed without transferring the solid rocket engine shell prefabricated product many times, the production and installation difficulty is small, and the efficiency is high; and compared with an existing integrally-formed annular skirt, the skirt structure formed by connecting the multiple skirt petals is better in rigidity.

Description

technical field [0001] The invention relates to the field of solid rocket motor manufacturing, in particular to a skirt structure of a solid rocket motor shell, a skirt assembly tool, and a skirt upper method. Background technique [0002] The skirt structure is an important structural part for the external connection of the solid rocket motor, which connects the solid rocket motor with the interstage section and the tail section as a whole. Generally, the skirt structure of the solid rocket motor is an integral ring structure with an "L"-shaped rotary section, which is inserted into the winding layer of the solid rocket motor casing by means of adhesive bonding. In order to facilitate the connection between the skirt structure and the solid rocket motor casing and to coordinate the deformation, the connection area between the skirt structure and the solid rocket motor casing is a variable thickness structure, and several strip-shaped through grooves are evenly distributed i...

AI Technical Summary

Problems solved by technology

[0003] With the improvement of rocket carrying capacity requirements, solid rocket motors are gradually becoming larger, and the existing technology has the following limitations in practical application: 1) The forming of large-scale overall skirts needs to rely on large-scale equipment, which is difficult, time-consuming and costly; 2) When installing a large overall skirt, the fiber-wound solid rocket motor shell preform that has been wound on the winding mandrel before being skirted must be removed from the winding equipment, placed on the winding mandrel assembly bracket for skirting, and then Place the winding mandrel after the upper skirt is completed on the winding equipment, continue to complete the skirt outer hoop layer winding, and then cure

This method needs to transfer the mandrel with large volume and weight many times, which is difficult and risky

Moreover, due to the limitation of space and the weight of the mandrel, it is necessary to install extension shafts and multiple conversion support points when winding the skirt on the mandrel assembly bracket. The process is complex and difficult; 3) The skirt bonding of the large solid rocket motor shell The size of the area is large, the matching with the shell is difficult to control, and the bonding quality is reduced

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