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Aviation lamination material variable-parameter adaptive hole drilling system and method

A technology of laminated materials and adaptive controllers, applied in the direction of automatic control devices, manufacturing tools, boring/drilling, etc., to achieve the effects of ensuring continuity, saving time, avoiding delamination defects and large exit burrs

Active Publication Date: 2015-07-08
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Application Information

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Problems solved by technology

[0007] The invention provides an adaptive hole-making method of variable parameters for aviation laminated materials, which can monitor the processing state and processing quality of the material in real time during the drilling process, and perform real-time variable parameter adaptive control for abnormal conditions, thereby fundamentally Solve the problems encountered in the drilling of laminated materials and realize the integrated efficient and high-quality hole making of different materials

Method used

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  • Aviation lamination material variable-parameter adaptive hole drilling system and method
  • Aviation lamination material variable-parameter adaptive hole drilling system and method
  • Aviation lamination material variable-parameter adaptive hole drilling system and method

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Embodiment Construction

[0033] The present invention is described in further detail in conjunction with the accompanying drawings, taking the carbon fiber composite material 2 as the upper layer material, and the metal material 3 as the lower layer material as an example, as figure 1 The schematic diagram of the hole making is shown.

[0034] figure 2 , 3 The shown end effector is mounted on an industrial robot and is mainly used for hole making in robot automation assembly. figure 2The load cell 4 has the function of the tool handle 11, the drilling tool 1 is clamped on the load cell 4, the load cell 4 is installed on the electric spindle 6, the spindle sleeve 5 is set on the electric spindle 6, and the electric spindle The main shaft 6 is driven by a driving motor 8, and there are two vertical linear guide rails 10 under the base 9, through which the electric main shaft 6 can move freely in the plane of the base 9 through the linear guide rails 10. The encoder of the drive motor 8 can also mon...

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Abstract

An aviation lamination material variable-parameter adaptive hole drilling system is characterized by comprising a, an end executor; b, a force sensor or a current detector; c, an adaptive controller; d, a control unit. An electric spindle transducer of the end executor controls the rotation of an electric spindle. The force sensor or the current detector is arranged on the electric spindle to be used for detecting the axial force or the current of the electric spindle. The adaptive controller communicates with the force sensor or the current detector and the control unit to be used for receiving feedback signals of the force sensor or the current detector to send instructions to the control unit, and the control unit controls the end executor to perform corresponding actions. A drive motor of the end executor comprises an encoder to be used for recognizing and feeding back tool feeding positions, and the adaptive controller communicates with the encoder and the control unit to be used for receiving the feedback signals of the encoder to send instructions to the control unit which controls the end executor to perform corresponding actions.

Description

technical field [0001] The invention is applied to the field of hole making for automatic assembly of aircraft components, and in particular relates to a variable parameter self-adaptive lamination hole making system and method for carbon fiber composite materials and metal materials. Background technique [0002] With the advancement of material science and processing technology, and in order to meet the lightweight and high fatigue life performance requirements of the new generation of advanced aircraft and large civil aircraft structural parts, carbon fiber composites are used as a material with excellent performance in such as aircraft panels, It is widely used in the manufacture of aerospace products such as fuselage sections of large passenger aircraft and engine casings. [0003] After the composite material component is formed, in a large number of occasions, it needs to be stacked with other metal structural parts to make holes to realize the assembly of aircraft co...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23B41/00B23Q15/013B23Q15/12
CPCB23B41/00B23B2215/04B23Q15/013B23Q15/12
Inventor 田威胡坚廖文和张霖布音
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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