Technique for integrally and quickly forming special shaped rudder shaft of aircraft

A process method and aircraft technology, applied to the improvement of process efficiency, additive processing, metal processing equipment, etc., can solve the problems of complex manufacturing process, low pass rate, and difficult forming of rudder shaft segments, and meet the requirements of research and development. Effects of reduced processing costs and improved material utilization

Active Publication Date: 2018-06-08
BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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Problems solved by technology

[0007] The purpose of the present invention is to provide a process for the overall rapid prototyping of special-shaped rudder shafts of aircraft, through a reasonable process support structure, to realize t...

Method used

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  • Technique for integrally and quickly forming special shaped rudder shaft of aircraft
  • Technique for integrally and quickly forming special shaped rudder shaft of aircraft
  • Technique for integrally and quickly forming special shaped rudder shaft of aircraft

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Experimental program
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Embodiment 1

[0049] The material used in this embodiment is GH4169 alloy. Such as Figure 5 shown in the following steps:

[0050] The first step, model preparation

[0051] The three-dimensional model of the rudder shaft is processed, and the three segments are summed as a whole, and a margin of 2 mm is added to the outer surface of the long end and short end of the rudder shaft, and a margin of 0.5 mm is added to all inner profiles. Add a 0.1mm deep "U"-shaped reference line around the surface of the rudder shaft as a line drawing reference for finishing. According to the structural characteristics and forming direction of the rudder shaft, a solid process support is added at the bottom of the long end of the rudder shaft. The thickness of the solid body is 20mm. Multiple diamond-shaped hollow supports are added to the solid body to improve the forming efficiency and powder utilization rate.

[0052] The second step, slice file preparation

[0053] Import the processed part model int...

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Abstract

The invention belongs to the field of superalloy additive manufacturing, and particularly relates to a technique for integrally and quickly forming an special-shaped rudder shaft of an aircraft. An overall special-shaped rudder shaft structure formed by selective laser melting fully utilizes the characteristics of high flexibility and rapid response of an additive manufacturing technology. By means of a reasonable process supporting structure and a placement position, the integrated forming of the special-shaped rudder shaft is achieved. A selective laser melting forming process is rapid in solidification, grains of an alloy structure are refined, and the strength and plasticity of parts far exceed a traditional manufacturing process; secondly, the rapid forming method simplifies production process and improves production efficiency. Compared with the traditional manufacturing process, production cycle for rapid forming of the single-piece rudder shaft is shortened by 50%, the utilization rate of materials is increased by 30%, the processing cost is reduced by 30%, and model development demands are effectively ensured.

Description

technical field [0001] The invention belongs to the field of additive manufacturing of high-temperature alloys, and in particular relates to a process method for integral rapid forming of aircraft special-shaped rudder shafts. Background technique [0002] The service conditions of the new generation of fighter jets, unmanned combat platforms and aerospace defense products are becoming increasingly harsh, the flight speed of weapons is gradually increasing, and they experience harsh mechanical and thermal environments during flight. The low-cost manufacturing requirements of modernization and quick response. [0003] The overall shape of the high-temperature alloy rudder shaft of the aircraft is an "L"-shaped turning special-shaped structure, which is composed of two broken-line variable-section hollow structures and an intermediate connection structure. The maximum direction size of the parts is 460mm, and the maximum outer diameter is 69mm. The traditional process splits ...

Claims

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Application Information

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IPC IPC(8): B22F3/105B22F1/00B33Y10/00B33Y70/00
CPCB33Y10/00B33Y70/00B22F10/00B22F1/14B22F10/66B22F10/34B22F10/28B22F10/64B22F10/68Y02P10/25
Inventor 刘莹莹李明亮钱远宏
Owner BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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