Feeding drill applicable to quick change arrangement of joint of robot

Abstract

The invention discloses a feeding drill applicable to the quick change arrangement of a joint of a robot, which comprises a quick change flange, a laser target flange, an automatic feeding mechanism, a power head, a pre-pressing mechanism, a cutting fluid pipe and a chip breaking processing mechanism, wherein one end of the quick change flange is positioned on an industrial robot flange, and the other end of the quick change flange is connected with one end of the laser target flange; the other end of the laser target flange is connected with a bottom plate of a platform of the automatic feeding mechanism; the power head is arranged on a guide rail of the automatic feeding mechanism; the pre-pressing mechanism is arranged at the front end of the automatic feeding mechanism; and the cutting fluid pipe and the chip breaking processing mechanism are arranged on a presser foot head of the pre-pressing mechanism. The feeding drill has the advantages of (1) realizing automatic drilling, achieving high machining efficiency and reducing the labor intensity of workers, (2) performing pre-pressing before machining and adjusting a cutter to make the cutter vertical to the surface of a work piece so as to improve the drilling efficiency, and (3) avoiding broken chip residues and conveniently keeping clean and tidy the work piece.

Description

technical field [0001] The invention relates to a feed drill, in particular to a feed drill suitable for quick-change installation of robot joints. Background technique [0002] In the total number of total failures of the aircraft, the number of failures due to structural damage generally accounts for 12% to 13%. However, because the airborne finished product can be replaced by a new one after failure, the life of the aircraft structural component determines the life of the aircraft. total lifespan. At present, the main connection method used in aircraft structural parts is still mechanical connection, and there are about 1.5 to 2 million connection parts on a large aircraft. The total life of the aircraft is mainly determined by the life of the airframe. Fatigue damage is the root cause of the aircraft's inability to work. According to statistics, 75% to 80% of the fatigue damage occurs on the connection parts of the airframe structure. It can be seen that the quality of ...

AI Technical Summary

Problems solved by technology

The usual disadvantages of traditional manual hole making are: (1) easy to form defects; (2) poor hole position accuracy; (3) many steps in hole making; (4) secondary assembly is required; (5) the influence of human factors cannot be avoided

[0004] my country's automatic hole-making technology started late, and there is no mature automatic hole-making technology and system

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