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Lathing method of skirt bases of thin-walled high-strength steel rocket hull

A technology of high-strength steel and rocket shell, applied in metal processing equipment, metal processing mechanical parts, turning equipment, etc., can solve the problems of high shell strength, large deformation, cutting deformation, etc., and achieve the effect of high processing accuracy

Inactive Publication Date: 2012-05-02
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

However, the processing of existing high-strength thin-walled parts is relatively difficult, and it is very easy to produce clamping deformation and cutting deformation during processing, and it is difficult to ensure the processing quality of parts.
For example, the above-mentioned rocket shell, due to the high strength of the shell, requires a large clamping force to ensure normal cutting. The front and rear skirts are deformed greatly due to the elastic recovery of the clamping deformation after machining: The design requirement for the diameter size deviation is not greater than ±0.1mm, but actually exceeds ±0.3mm; the design requirement for the coaxiality error of the reference outer circle of both ends of the skirt is not greater than 0.25mm, but the actual value exceeds 0.35mm, and the manufactured product can only be used for Ground test, cannot be used for flight test and delivery to users

Method used

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  • Lathing method of skirt bases of thin-walled high-strength steel rocket hull
  • Lathing method of skirt bases of thin-walled high-strength steel rocket hull
  • Lathing method of skirt bases of thin-walled high-strength steel rocket hull

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0024] For an ultra-high-strength steel rocket combustion chamber shell with a size parameter of Φ600mm×3500mm and a wall thickness of 3mm on an aircraft, the process control process of the skirt reference is as follows:

[0025] 1) Shell clamping and alignment position identification and measurement: Taking a point on the outer circle of the front skirt 2.2 of the rocket combustion chamber shell 2 as a reference, divide the outer circle of the front skirt 2.2 and the front joint 2.1 into four equal parts , the outer circle of the rear skirt 2.3 and the rear joint 2.4 are equally divided into eight equal parts, and a linear mark with a length of 10mm is made at each equal part; the four diameters at the eighth equal parts of the outer circle of the rear skirt 2.3 are measured and marked as Record;

[0026] 2) Installation of special braces: Install the special braces 3 into the inner hole of the rear joint 2.4 at one end of the rear skirt 2.3 and tighten them. The special brac...

Embodiment 2

[0031] For an ultra-high-strength steel rocket combustion chamber shell with a size parameter of Φ1200mm×5600mm and a wall thickness of 4mm on an aircraft, the process control process of the skirt reference is as follows:

[0032]1) Shell clamping and alignment position identification and measurement: Taking a point on the outer circle of the front skirt 2.2 of the rocket combustion chamber shell 2 as a reference, divide the outer circle of the front skirt 2.2 and the front joint 2.1 into four equal parts , the outer circle of the rear skirt 2.3 and the rear joint 2.4 are equally divided into eight equal parts, and a linear mark with a length of 15mm is made at each equal part; the four diameters at the eighth equal parts of the outer circle of the rear skirt 2.3 are measured and marked as Record;

[0033] 2) Installation of special braces: Install the special braces 3 into the inner hole of the rear joint 2.4 at one end of the rear skirt 2.3 and tighten them. The special brac...

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Abstract

The invention discloses a lathing method of skirt bases of a thin-walled high-strength steel rocket hull. The lathing method comprises the following steps of: 1, clamping a hull and identifying and measuring an alignment part; 2, installing a special support tool; 3, installing, aligning and clamping the hull; and 4, processing the hull: lathing excircles, end faces and inner holes of a front shirt base and a rear shirt base of a rocket combustion chamber hull. By adopting the special support tool and the special clamping and aligning method, the shirt bases of the thin-walled high-strength steel rocket combustion chamber hull are processed with high processing precision, thus requirements of product design precision are completely met. A product made by using the method provided by the invention can be used in a ground test, and can also be used in a flight test and can be delivered to a user for use. The lathing method provided by the invention can be used for processing the shirt bases of the thin-walled high-strength steel rocket hull, and can also be used for processing control of other similar products.

Description

technical field [0001] The invention relates to the processing technology of rocket combustion chamber casings, in particular to a lathe processing method of thin-walled high-strength steel rocket casing skirt reference. Background technique [0002] The solid rocket motor is the power device of the aerospace vehicle, which is composed of combustion chamber, propellant grain, nozzle, igniter and other main parts. Among them, the combustion chamber casing is a key part of the solid rocket motor system, which provides power for the aircraft through the combustion of propellant. The front skirt and the rear skirt of the combustion chamber shell are the installation benchmarks of the projectile structure. The front skirt is connected to the re-entry body of the aircraft through explosive bolts, and the rear skirt is connected to the rear transition cabin. When the aircraft arrives at the predetermined position, the computer on the bomb sends out a detonation command, the thrust...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23B5/00B23B25/06B23Q3/00
Inventor 韩庆波王华东余天雄
Owner 湖北三江航天江北机械工程有限公司
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