CN111940802A

CN111940802A - Milling tool for margin of aluminum alloy skin of airplane

Info

Publication number: CN111940802A
Application number: CN202010823098.6A
Authority: CN
Inventors: 刘晓东; 王宏锋; 王辉
Original assignee: Shenyang Aircraft Industry Group Co Ltd
Current assignee: Shenyang Aircraft Industry Group Co Ltd
Priority date: 2020-08-17
Filing date: 2020-08-17
Publication date: 2020-11-17
Anticipated expiration: 2040-08-17
Also published as: CN111940802B

Abstract

Aircraft aluminum alloy skin edge allowance milling tool belongs to aircraft assembly technical field. The tool comprises an air inlet nozzle, a starting switch, a turbine motor, a 90-degree angle head, a fastening nut, a limiting tail end main body, a jackscrew, a screw, a spring limiting piece, a cutter, a limiting block, an inner rolling bearing, a half-thread headless nail, an inner bearing blanking cover, a limiting block fastening knob, a distance adjusting telescopic device, an outer bearing blanking cover, an outer rolling bearing and a bearing. By using the tool, the control requirement of the aluminum alloy skin gap can be guaranteed with high precision, the control range of the skin gap is increased by the graded adjustment of the limiting slide block, misoperation in the working process is avoided by placing the spring piece, the friction force is reduced and the stability of operation is guaranteed because the tool and the skin binding surface adopt a rolling contact mode. The gap precision value can reach 0.1mm, and the accurate milling efficiency of the 600mm long skin edge is improved by 60 times.

Description

Milling tool for margin of aluminum alloy skin of airplane

Technical Field

The invention aims at the requirement of accurately controlling the margin of the aluminum alloy skin edge in the process of airplane assembly, is used for guaranteeing the requirement of the skin gap after assembly and connection, and carries out milling finish machining on the margin of the aluminum alloy skin; belongs to the technical field of airplane assembly.

Technical Field

In the process of airplane assembly, allowance is left before all components and parts are combined, manufacturing and assembly errors are eliminated through an actual milling finish machining mode, the main mode of edge milling of the aluminum alloy skin at present is marking by manual marking, the allowance is repeatedly removed by holding a pneumatic milling wheel and a grinding wheel through the experience and the technical proficiency of workers, the method is difficult to meet the requirement of the skin clearance of the 0.3mm outer surface of the new generation airplane at present, wherein, the pencil marking fineness has larger error, the milling and polishing amount is difficult to control, the skin clearance uniformity is poorer, the labor intensity of workers is large, repeated comparison measurement and multiple milling and polishing are needed, the accurate milling and polishing of the edge of the skin with the length of 600mm can be completed within about one hour, and the quality is difficult to guarantee, so that the searching for an accurate, efficient and low-labor-intensity milling tool for the edge allowance of the aluminum alloy skin is very necessary.

Disclosure of Invention

The invention adopts the design concept of clean edge auxiliary positioning (copying milling), namely, the finished aluminum alloy skin butt joint surface is used as the positioning reference of an edge milling tool, and the aluminum alloy skin butt joint surface on the other side is milled by the movement of the edge milling tool on the butt joint surface.

Aircraft aluminum alloy skin edge allowance milling instrument includes suction nozzle 1, starting switch 2, turbo motor 3, 90 angle head 4, fastening nut 5, spacing end main part 6, jackscrew 7, screw 8, spring spacing piece 9, cutter 10, stopper 11, inboard antifriction bearing 12, half thread headless nail 13, inboard bearing blanking cover 14, stopper fastening knob 15, roll adjustment telescoping device 16, outside bearing blanking cover 17, outside antifriction bearing 18 and bearing 19.

One end of the air inlet nozzle 1 is connected with an air source, and the other end of the air inlet nozzle is connected with the turbine motor 3 in a threaded connection mode; one end of 90 angle head 4 is connected with turbo motor 3, and 90 angle is to corner end connection fastening nut 5 of head 4, and 90 angle head 4 is connected with spacing terminal main part 6 interference fit simultaneously, fixes through two jackscrews 7 between 90 angle head 4 and the spacing terminal main part 6 to the connection stability of guarantee instrument, both ends are equipped with the spacing piece of spring 9 around spacing terminal main part 6, and carry out fastening connection by screw 8. The position of a tool can be fixed by the aid of a protruding part of the spring limiting piece 9, the tool can be conveniently manually pushed to mill, the fastening nut 5 is connected with the cutter 10, the cutter 10 is in a 24-blade truncated cone shape, a skin falls when an inclined cutting edge enters the cutter to cut, and a vertical cutting edge pushes the tool to cut. The bottom of the cutter bar of the cutter 10 is connected with a bearing 19 in an interference fit manner, the bearing 19 is positioned in a cylindrical groove of the limiting tail end main body 6, and the connection form is in interference fit connection; the limiting block 11 is positioned in a trapezoidal groove of the limiting tail end main body 6, the outer leakage shape is a rounded rectangular parallelepiped, the limiting block 11 is a positioning reference of milling, and the inner side face of the limiting block is attached to the vertical face of the processed clean edge skin; the number of the inner side rolling bearings 12 is 8, the inner side rolling bearings are connected with the limiting tail end main body 6 and the inner side bearing blocking cover 14 through half-thread headless nails 13, and the limiting block fastening knob 15 is cylindrical and is in threaded connection with the limiting tail end main body 6; the distance-adjusting telescopic device 16 is in a pitch adjusting form, the pitch is 1mm, the adjusting distance of each gear is 0.1mm, 5 adjusting gears are provided, the number of the outer rolling bearings is 4, and the outer rolling bearings are connected with the limiting tail end main body 6 and the outer bearing blocking cover 17 through the half-thread headless nails 13.

The invention has the beneficial effects that: the tool changes the traditional process means and method for repairing the skin gap, the control requirement of the aluminum alloy skin gap can be guaranteed with high precision by using the tool, the control range of the skin gap is increased by the graded adjustment of the limiting slide block, misoperation in the working process is avoided by placing the spring piece, the tool and the skin binding surface adopt a rolling contact mode, the friction force is greatly reduced, the labor intensity of workers is reduced, and the stability of operation is guaranteed. The gap precision value can reach 0.1mm, the edge of the skin with the length of 600mm can be accurately milled for 1 minute, and the efficiency is improved by 60 times.

Drawings

FIG. 1 is a front view of an aircraft aluminum alloy skin edge allowance milling tool.

FIG. 2 is a bottom view of an aircraft aluminum alloy skin edge allowance milling tool.

FIG. 3 is a side view of an aircraft aluminum alloy skin edge allowance milling tool.

Wherein: 1. air inlet nozzle, 2, starting switch, 3, turbine motor, 4, 90 DEG angle are to the head, 5, fastening nut, 6, spacing terminal main part, 7, jackscrew, 8, screw, 9, the spacing piece of spring, 10, cutter, 11, stopper, 12, inboard antifriction bearing, 13, half-thread headless nail, 14, inside bearing blanking cover, 15, stopper fastening knob, 16, roll adjustment telescoping device, 17, outside bearing blanking cover, 18, outside antifriction bearing, 19, bearing.

Detailed Description

The milling tool for the margin of the edge of the aircraft aluminum alloy skin consists of the following components: the device comprises an air inlet nozzle 1, a starting switch 2, a turbo motor 3, a 90-degree angle head 4, a fastening nut 5, a limiting terminal main body 6, a jackscrew 7, a screw 8, a spring limiting piece 9, a cutter 10, a limiting block 11, an inner rolling bearing 12, a half-thread headless nail 13, an inner bearing blanking cover 14, a limiting block fastening knob 15, a distance adjusting telescopic device 16, an outer bearing blanking cover 17, an outer rolling bearing 18 and a bearing 19.

1 one end of suction nozzle links to each other with the wind regime, and the other end passes through the spiro union form to be connected with turbo motor 3, and 90 jiaos are connected fastening nut 5 to 4 turning ends of head, and 90 jiaos are connected with spacing end subject 6 and are interfered the fit simultaneously to fix through two jackscrews 7, with the connection stability of this guarantee instrument, both ends are equipped with spring spacing piece 9 around spacing end subject 6, and carry out fastening connection by screw 8. The protruding part of the tool can assist in fixing the position of the tool, the tool can be conveniently manually pushed to mill, the fastening nut 5 is connected with the cutter 10, the cutter is in a 24-edge truncated cone shape, the inclined cutting edge cuts in the process that a skin falls when entering the cutter, and the vertical cutting edge cuts in the process that the tool is pushed. The bottom of the cutter bar of the cutter 10 is connected with a bearing 19 in an interference fit manner, the bearing 19 is positioned in a cylindrical groove of the limiting tail end main body 6, the connection form is in the interference fit connection, a limiting block 11 is positioned in a trapezoidal groove of the limiting tail end main body 6, the outer leakage shape is a rounded cuboid, the limiting block is a positioning reference for milling, wherein the inner side surface is jointed with the vertical surface of the processed clean edge skin, the number of the inner rolling bearings 12 is 8, is connected with a limit tail end main body 6 and an inner side bearing blanking cover 14 through a half-thread headless nail 13, a limit block fastening knob 15 is cylindrical, is in threaded connection with the limiting tail end main body 6, the distance adjusting telescopic device 16 is in a thread pitch adjusting form, the thread pitch is 1mm, the adjusting distance of each gear is 0.1mm, 5 adjusting gears are provided, the number of the outer rolling bearings 18 is 4, connected with the limit end body 6 and the outer bearing block cover 17 through a half-thread headless nail 13.

The embodiment is the repair of an aluminum alloy skin with the thickness of 1.5mm in the assembly process of a certain assembly of an airplane, and the milling test length of the skin is 600 mm. Firstly, clamping and positioning an assembly, simulating milling of a tool under the condition that an air source is not connected, ensuring that the reference section of a clean-edge skin is smooth and unobstructed, limiting a spring piece, then connecting the air source, idle running the tool, checking the working integrity and usability of the tool, then tilting one end of the skin needing to be milled and repaired, positioning the tool, removing the allowance of the initial end, lowering the skin to the vertical blade of a cutter, and finally stably pushing the tool at a constant speed to mill the whole edge, wherein the tolerance of the gap between the butt seam and the seam after milling of the aluminum alloy skin is not more than 0.1mm through the implementation and application created by the invention; the end face milling surface roughness of the aluminum alloy skin is not less than 1.6 mu m, and the edge milling efficiency (the thickness is not more than 4mm) is not less than 500mm (length)/min.

Claims

1. The milling tool for the margin of the edge of the aluminum alloy skin of the airplane is characterized by comprising an air inlet nozzle (1), a starting switch (2), a turbine motor (3), a 90-degree angle head (4), a fastening nut (5), a limiting tail end main body (6), a jackscrew (7), a screw (8), a spring limiting sheet (9), a cutter (10), a limiting block (11), an inner side rolling bearing (12), a half-thread headless nail (13), an inner side bearing blanking cover (14), a limiting block fastening knob (15), a distance adjusting telescopic device (16), an outer side bearing blanking cover (17), an outer side rolling bearing (18) and a bearing (19);

one end of the air inlet nozzle (1) is connected with an air source, and the other end of the air inlet nozzle is connected with the turbine motor (3) in a threaded connection mode; one end of a 90-degree angle head (4) is connected with a turbine motor (3), a corner end of the 90-degree angle head (4) is connected with a fastening nut (5), meanwhile, the 90-degree angle head (4) is in interference fit connection with a limiting tail end main body (6), the 90-degree angle head (4) and the limiting tail end main body (6) are fixed through two jackscrews (7) to guarantee the connection stability of the tool, and spring limiting pieces (9) are arranged at the front end and the rear end of the limiting tail end main body (6) and are in fastening connection through screws (8); the protruding part of the spring limiting piece (9) can assist in fixing the position of a tool, so that the tool can be conveniently pushed by hand to mill, the fastening nut (5) is connected with the cutter (10), the cutter (10) is in a 24-blade truncated cone shape, a bevel cutting edge cuts in the process that a skin falls when the cutter is inserted, and a vertical cutting edge cuts in the process that the tool is pushed; the bottom of a cutter bar of the cutter (10) is connected with a bearing (19) in an interference fit manner, the bearing (19) is positioned in a cylindrical groove of the limiting tail end main body (6), and the connection form is in interference fit connection; the limiting block (11) is positioned in a trapezoidal groove of the limiting tail end main body (6), the outer leakage shape is a rounded cuboid, the limiting block (11) is a milling positioning reference, and the inner side face of the limiting block is attached to the vertical face of the machined clean edge skin; the number of the inner rolling bearings (12) is 8, the inner rolling bearings are connected with the limiting tail end main body (6) and the inner bearing blocking cover (14) through half-thread headless nails (13), and the limiting block fastening knob (15) is cylindrical and is in threaded connection with the limiting tail end main body (6); the distance-adjusting telescopic device (16) is in a pitch adjusting form, the pitch is 1mm, the adjusting distance of each gear is 0.1mm, 5 adjusting gears are arranged, the number of the outer rolling bearings (18) is 4, and the outer rolling bearings are connected with the limiting tail end main body (6) and the outer bearing plug cover (17) through half-thread headless nails (13).