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Welding method for small airborne rocket case

A technology of a rocket shell and a welding method, applied in welding equipment, arc welding equipment, manufacturing tools, etc., can solve the problems of high processing efficiency, the excess height cannot be greater than 0.3mm, and the manufacturing cost is low, and achieves fast and accurate installation and positioning. Effect

Active Publication Date: 2019-07-30
湖北三江航天江北机械工程有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional butt welding method of medium and large solid rocket combustion chamber shells is difficult to meet the new requirements of large number of airborne small rocket shells, high processing efficiency and low manufacturing cost
[0004] For small rocket shells with a diameter of less than 260mm and materials made of 30CrMnSiA low-alloy high-strength steel, class I butt welds are required, the tensile strength of welded joints σb welding ≥ 972MPa, the bending angle of joints α ≥ 40°, and no dents are allowed on the back of the weld , and the weld reinforcement shall not be greater than 0.3mm, and the total time for assembly, welding, disassembly, and grinding shall not exceed 20 minutes, and the traditional butt welding method cannot meet the requirements

Method used

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  • Welding method for small airborne rocket case
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  • Welding method for small airborne rocket case

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0060] For a certain type of 30CrMnSiA low-alloy high-strength steel small shell, its external diameter D3 is 140mm, shell length L0 is 550mm, and wall thickness t is 2mm. The airborne small rocket shell welding method of the present invention is as follows:

[0061] 1) Processing of the front head shell and the rear joint shell of the cylinder

[0062] The raw material of the cylinder is roughly machined into the front head shell, the front end of the front head shell is provided with a finishing chuck, and the rear end of the front head shell is provided with a front circle which is butt-welded with the rear joint shell of the cylinder. and the rear end of the inner wall of the front cylinder section is provided with a front positioning annular notch, the rear end face of the front cylinder section is provided with a front bevel, and the inner edge of the front bevel is perpendicular to the surface between the end faces of the front positioning annular notch. The front butt ...

Embodiment 2

[0080] For a certain type of 30CrMnSiA low-alloy high-strength steel small shell, its external diameter D3 is 180mm, shell length L0 is 850mm, and wall thickness t is 2.5mm. The airborne small rocket shell welding method of the present invention is as follows:

[0081] 1) Processing of the front head shell and the rear joint shell of the cylinder

[0082] The raw material of the cylinder is roughly machined into the front head shell, the front end of the front head shell is provided with a finishing chuck, and the rear end of the front head shell is provided with a front circle which is butt-welded with the rear joint shell of the cylinder. and the rear end of the inner wall of the front cylinder section is provided with a front positioning annular notch, the rear end face of the front cylinder section is provided with a front bevel, and the inner edge of the front bevel is perpendicular to the surface between the end faces of the front positioning annular notch. The front but...

Embodiment 3

[0100] For a certain model 30CrMnSiA low-alloy high-strength steel small shell, its external diameter D3 is 220mm, the shell length L0 is 1150mm, and the wall thickness t is 3mm. The airborne small rocket shell welding method of the present invention is as follows:

[0101] 1) Processing of the front head shell and the rear joint shell of the cylinder

[0102] The raw material of the cylinder is roughly machined into the front head shell, the front end of the front head shell is provided with a finishing chuck, and the rear end of the front head shell is provided with a front circle which is butt-welded with the rear joint shell of the cylinder. and the rear end of the inner wall of the front cylinder section is provided with a front positioning annular notch, the rear end face of the front cylinder section is provided with a front bevel, and the inner edge of the front bevel is perpendicular to the surface between the end faces of the front positioning annular notch. The fron...

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Abstract

The invention discloses a welding method for a small airborne rocket shell. The welding method for the small airborne rocket case comprises the steps of machining of a front sealing head shell and a rear cylindrical connector shell, machining of a left section and a right section of a butt-welding sample, assembling and positioned welding, but welding of a prefabricated shell part and a prefabricated welding sample part, radiographic inspection of a weld joint, repair welding, radiographic inspection, and stress relief annealing. According to the welding method for the small airborne rocket shell, a butt-joint circumferential weld positioning structure is adopted, so that butt-welding mounting and positioning of the case are rapid and accurate and can be completed in two minutes, while themounting and positioning time of a traditional method is over 15 minutes; and a welding mandrel does not need to be dismantled, while the time for dismantling the welding mandrel of the traditional method is over 10 minutes. The welding method not only can be used for efficient welding of the small airborne rocket shell, but also can be used for efficient welding of other similar product parts.

Description

technical field [0001] The invention relates to the technical field of solid rocket combustion chamber shell welding, in particular to a welding method for an airborne small rocket shell. Background technique [0002] With the rapid development of technologies such as drones and helicopters, more and more airborne defense products and environmental detection products powered by solid rockets are used, which are characterized by large quantities, high processing efficiency, and low manufacturing costs. [0003] Medium and large solid rocket motors are used as launch power devices for strategic missiles, tactical missiles, and military and civilian satellites. The product value of the solid rocket combustion chamber shell is high and the processing cycle is long. Its traditional butt welding adopts copper lining inner support to adjust the circle and support welding. After welding, after taking out the copper lining inner support, the operator drills into the shell and grinds ...

Claims

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Application Information

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IPC IPC(8): B23K9/028B23K9/16
CPCB23K9/0035B23K9/0282B23K9/16
Inventor 韩庆波李章马旷门广伟吴钦
Owner 湖北三江航天江北机械工程有限公司
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