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Drill-rivet method for semi-closed cage type thin-wall inter-box housing section

A semi-closed, birdcage technology, applied in the field of drilling and riveting, can solve the problems of incomplete application and poor opening, and achieve the effects of low riveting noise, improved drilling and riveting efficiency, and high one-time pass rate.

Active Publication Date: 2015-03-04
CAPITAL AEROSPACE MACHINERY +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the space between the launch vehicle case is a typical semi-enclosed birdcage-type thin-walled shell, which has poor opening performance, and the automatic drilling and riveting process for aviation panel products cannot be fully applied.

Method used

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  • Drill-rivet method for semi-closed cage type thin-wall inter-box housing section
  • Drill-rivet method for semi-closed cage type thin-wall inter-box housing section
  • Drill-rivet method for semi-closed cage type thin-wall inter-box housing section

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Embodiment Construction

[0023] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0024] A method for drilling and riveting shell segments between semi-enclosed birdcage-type thin-walled boxes, comprising the following steps:

[0025] Step 1: Take the center of the circle on the butt joint surface of the lower end frame of the inter-box section as the origin, establish the spatial x, y, z coordinate system of the inter-box section; and establish the rivet hole position coordinates in this coordinate system. Such as figure 1 shown;

[0026] Step 2: According to the rivet point data, plan the drilling and riveting program walking paths of the front and rear end frames, middle frames, and stringers according to the riveting sequence; for a single stringer, in order to ensure the release of riveting stress, the riveting path for hole making is along the stringer direction, the order is: 1-2, 3-4, 5-6, 7-8 such as f...

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Abstract

The invention belongs to the field of a drill-rivet method, specifically relates to a drill-rivet method for a semi-closed cage type thin-wall inter-box housing section, and aims at realizing the engineering application of the automatic drill-rivet technology on the inter-box section of a carrier rocket. The automatic drill-rivet technology is a novel technology developed for overcoming the shortage of manual drill rivet, and has the advantages of being high in production efficiency, high in quality reliability and small in production noise. The automatic drill-rivet technology enables automatic drilling, pin feeding, rivet performing, gumming, planing and other functions, and can be widely applied to a wing wallboard and body wallboard and the like with high openness in spacecraft instrumentation. With the adoption of the drill-rivet method, the drill-rivet efficiency is increased, the form and location tolerance of the product meets the design index requirement, the rivet noise is reduced, and the first pass yield of a rivet is increased.

Description

technical field [0001] The technology belongs to the field of drilling and riveting methods, and in particular relates to a drilling and riveting method for shell sections between semi-closed birdcage thin-walled boxes. Background technique [0002] The inter-section of the launch vehicle is located between the fuel tank and the oxidant storage tank. It is a typical semi-closed birdcage thin-walled riveted shell section. The inter-box section is mainly composed of the front and rear ends, the middle frame, stringers and skin. At present, the box section is produced by the traditional manual drilling and riveting process. First, use the existing riveted frame to position and pre-connect the front and rear end frames, the middle frame, and the stringers to form the birdcage structure of the tube section, and then lay the skin on the outside of the pre-connected structure to form the entire tube section shell, and then the front and rear end frames are aligned. , the middle fr...

Claims

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Application Information

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IPC IPC(8): B23P15/00
CPCB21J15/048
Inventor 王国庆丁鹏飞陶钢章茂云马兴海侯东旭金健孙立强臧建新庄树鹏
Owner CAPITAL AEROSPACE MACHINERY
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