Variable parameter control holing method for laminated structure of aircraft

A technology of laminated structure and variable parameters, used in automatic control devices, manufacturing tools, metal processing machinery parts, etc., can solve problems such as uncontrollable product processing quality, improve hole-making efficiency, avoid tool replacement, and ensure continuity. Effect

Inactive Publication Date: 2014-07-02
ZHEJIANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, this patent document uses the traditional drilling technology, and it is difficult to avoid the phenom

Method used

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  • Variable parameter control holing method for laminated structure of aircraft
  • Variable parameter control holing method for laminated structure of aircraft
  • Variable parameter control holing method for laminated structure of aircraft

Examples

Experimental program
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Embodiment Construction

[0038] Such as figure 1 As shown, a screw hole-making end effector is fixed on a CNC machine tool, and is driven to a designated position by the CNC machine tool to make holes on the workpiece. It includes a base 1, a straight line set on the base Guide rail 6, a ram slidingly matched with the rail 6, an eccentric sleeve 2 and a revolution servo motor 3 fixed on the ram for cooperation through a synchronous belt 7, a mutually cooperating motor and electric spindle arranged in the eccentric sleeve 4, installation A cutter 8 on the electric spindle 4 and a presser foot 5 slidingly engaged with the base.

[0039] The drive motor and the ball screw pair matched with the drive motor are fixed on the base. The ball screw pair includes a screw and a nut, and the nut is fixed with the ram. Drive the ram to move on the track, that is, the tool moves on the track.

[0040] A cylinder is also fixed on the base, and the piston rod of the cylinder is fixed to the presser foot 5, which dr...

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Abstract

The invention discloses a variable parameter control holing method for a laminated structure of an aircraft. The laminated structure comprises a carbon fiber composite material layer and a titanium alloy layer. The method comprises the following steps: (1) pre-pressing a to-be-holed area of a workpiece; (2) controlling a tool to hole the carbon fiber composite material layer in a helical milling manner until the distance between a tool nose and a material interface is a preset value; (3) changing a rotation angle accelerated speed, a revolution angle accelerated speed and a feeding accelerated speed of the tool, and controlling the tool to continuously hole until the tool nose reaches the material interface; (4) keeping the rotation angle accelerated speed, the revolution angle accelerated speed and the feeding accelerated speed of the tool unchanged, and controlling the tool to hole the titanium alloy layer in the helical milling manner. According to the method, by dynamically adjusting parameters of the tool, requirements on cutting parameters of different material layers of the laminated structure are met, and the holing quality and the holing efficiency are ensured; the parameters of the tool are converted between 0.2mm and 0.3mm, the machining quality can be ensured, and the parameters can be switched within enough time; holing is carried out in the helical milling manner, so that the holing efficiency is improved.

Description

technical field [0001] The invention belongs to the field of automatic hole making for digital assembly of aircraft, and in particular relates to a hole making method controlled by variable parameters of an aircraft laminated structure. Background technique [0002] With the rapid development of the aviation industry, in order to effectively improve the structural strength of the aircraft, reduce the weight of the aircraft structure, and reduce the energy consumption of the aircraft, a large number of laminated structures composed of aluminum alloys, titanium alloys, and carbon fiber composite materials (CFRP) are used on aircraft. This kind of laminated structure is widely used especially in aircraft wings. The wing panels are made of composite materials, and the skeleton is made of aluminum and titanium alloys. The traditional drilling technology can no longer meet the product requirements. For titanium alloys, the traditional drilling technology is difficult to solve tec...

Claims

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Application Information

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IPC IPC(8): B23C3/00B23Q15/013B23Q15/08
Inventor 毕运波李江雄柯映林
Owner ZHEJIANG UNIV
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