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Robotized spiral drilling method and system for laminated structure of airframe

A technology of laminated structure and aircraft fuselage, which is applied in the direction of manufacturing tools, details of milling machine equipment, metal processing equipment, etc., can solve the problems of difficult to use, unfavorable terminal hole-making actuator attachment, low efficiency in processing laminated structure, etc. Achieve the effect of suppressing the exciting force, improving the hole-making efficiency, and reducing the tool wear

Active Publication Date: 2016-07-06
NANJING COLLEGE OF INFORMATION TECH
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0005] The technical problem to be solved by the present invention is that it is difficult to use traditional drilling to make holes in the large-diameter connecting holes of the laminated assembly of the aircraft fuselage structure, and the existing small-pitch feed has low efficiency in processing laminated structures and unfavorable terminal hole-making execution. Problems such as the installation of the device and the robot platform

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  • Robotized spiral drilling method and system for laminated structure of airframe
  • Robotized spiral drilling method and system for laminated structure of airframe
  • Robotized spiral drilling method and system for laminated structure of airframe

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Embodiment Construction

[0023] Such as figure 1 As shown, a method for robotized spiral hole making for aircraft fuselage stacked structure, which is applied to a robotized screw hole making system, includes the following steps:

[0024] (1) According to the diameter of the tool and the diameter of the hole to be made on the laminated structure of the fuselage, adjust the tool revolution radius e to the required setting value;

[0025] (2) Tool 8 to match the high rotation speed n of the top layer component material s1 , low revolution speed n ω1 and large feed pitch P 1 , performing spiral drilling on the top layer member 101;

[0026] (3) At the interface 103 of the stacked structure of the fuselage, the high rotation speed, low revolution speed, and large feed pitch of the tool are adjusted by n s1 , n ω1 ,P 1 tuned to match the n of the underlying component material s2 , n ω2 ,P 2 ;

[0027] (4) Tool to match the high rotation speed n of the underlying component material s2 , low revol...

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Abstract

The invention discloses a robotized spiral drilling method and system for a laminated structure of an airframe. The robotized spiral drilling method comprises the steps of firstly, pressing a drilling region of the laminated layer of the airframe by using a pressing mechanism; then, spirally drilling a top-layer structural member at the high autoroatation speed ns1, low revolution speed nomega1 and large feeding pitch P1, matched with a top-layer structural member material, of a cutter; next, regulating the high autoroatation speed, low revolution speed and large feeding pitch of the cutter from ns1, nomega1 and P1 to ns2, nomega2 and P2 matched with a bottom-layer structural member material at an interface of the laminated layer; and finally, spirally drilling a bottom-layer structural member at ns2, nomega2 and P2. The system mainly comprises an industrial robot and a spiral drilling actuator, wherein the industrial robot is provided with a seventh shaft. The robotized spiral drilling method and system are beneficial to the reliable installation and connection of the spiral drilling actuator and a robot platform and can be used for remarkably increasing the spiral drilling efficiency and quality of the laminated structure.

Description

technical field [0001] The invention belongs to the field of automatic hole-making in aircraft digital assembly, and in particular relates to a method and system for robotized spiral hole-making in laminated structures of aircraft fuselages. Background technique [0002] CFRP and aluminum alloy, titanium alloy and other lightweight alloy laminated components are widely used in aircraft wings, central wing boxes, fuselage and other components due to their excellent comprehensive properties such as light weight, high strength, and corrosion resistance. While this kind of laminated component brings new opportunities to the development of the aviation industry, its processing difficulties and related research have also attracted great attention from scholars at home and abroad. Relevant research results show that how to reduce the axial force of drilling, reasonably control the drilling temperature, and realize the efficient drilling of CFRP / light alloy laminated components with...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23C3/16
CPCB23C3/16B23C2215/04B23C2265/40
Inventor 单以才章婷颜玮郭丽
Owner NANJING COLLEGE OF INFORMATION TECH
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