Welding and forming method for shell of solid rocket engine

An engine casing and welding forming technology, applied in welding equipment, welding equipment, auxiliary welding equipment, etc., can solve problems such as large deformation of thin-walled barrel sections, engine casings that do not meet the overall index requirements, and difficulty in shape correction, etc., to achieve Avoid cold cracks, stable and reliable welded joint strength, small heat-affected zone effect

Active Publication Date: 2018-12-18
湖北三江航天江北机械工程有限公司
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Problems solved by technology

Since the thin-walled engine shell needs to undergo multiple high-temperature heat treatments, there is a large deformation in ...

Method used

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  • Welding and forming method for shell of solid rocket engine

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Embodiment

[0052] The welding method for the combustion chamber shell with a length of 1500mm and a barrel section wall thickness of 1.8mm is as follows:

[0053] 1) Determine the segmental welding structure of the shell

[0054] Divide the shell into front joint, cylinder and rear joint;

[0055] 2) Process front and rear joints

[0056] Forgings are used to process the front joint blank, and then the front joint blank is subjected to heat treatment to strengthen quenching and tempering after rough turning; after the front joint blank is heat treated, the outer diameter of the butt welding part with the cylinder is finished to ensure that the outer diameter of the butt welding part is consistent with the cylinder The outer diameter is consistent to form the front joint;

[0057] Among them, the heat treatment system is as follows: first, heat at 935°C for 45 minutes, then quench in oil, and then hold at 305°C for 3.5 hours, then air cool;

[0058] In the same way, forgings are used t...

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Abstract

The invention discloses a welding and forming method for a shell of a solid rocket engine. The shell is made of 30Cr3 ultrahigh-strength steel in material; a cylindrical section is tempered in advance, and then, a way of power-spinning cold hardening is employed to guarantee that the cylindrical section reaches 48 to 52 HRC (Rockwell hardness) and is not less than 1620 MPa in strength before beingwelded; a front joint and a rear joint are tempered after being roughly turned, and then a butting part and a butting part of the cylindrical section are turned, thus creating a good assembly environment for welding and forming a circumferential weld by an electron beam; the circumferential weld among the front joint, the rear joint and the cylindrical section is welded by adopting a vacuum electron beam, so that a heat affected zone is small, the weld width is narrow, the weld in a tempered state and an overheated zone can be respectively prevented from generating a cold crack and from beingembrittled and softened, and stable and reliable welded joint strength is guaranteed; and after the shell is welded by adopting the vacuum electron beam in the tempered state, structure property doesnot need to be improved through high-temperature quenching, and welding stress is removed only by low-temperature tempering, so that the shell is little in deformation and can be effectively guaranteed in geometric tolerance.

Description

technical field [0001] The invention relates to the technical field of processing and forming of small-diameter solid rocket motors, in particular to a method for welding and forming solid rocket motor shells. Background technique [0002] Air-to-air missiles are generally small-diameter solid rocket motors (including solid ramjet motors), which are hung on fighter-bombers and attack aircraft. Battlefield air interdiction, air strikes, and fixed-point clearance play an important role in combat missions. They are the core factor of the precision strike system in modern warfare and the decisive force that determines the outcome of a local war. [0003] Air-to-air missiles are different from ordinary surface-to-ground and surface-to-air missiles because of their own structure and close integration with aircraft. They are very strict on dimensions and tolerances. The size and diameter difference, straightness, roundness and other shape and position tolerances of the engine casi...

Claims

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Application Information

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IPC IPC(8): B23P15/00B23K15/06B23K37/00
CPCB23K15/06B23K37/00B23P15/00
Inventor 杨江波付德生和玉晓晏述亮曾永春
Owner 湖北三江航天江北机械工程有限公司
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