JP2018103865A - Method for repairing aircraft outside plate, electric power tool and attachment - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a technique for reducing number of man-hour required for repairing a scratch existing on a surface of an aircraft outside plate.SOLUTION: A method for repairing an aircraft outside plate comprises: a step at which an electric power tool comprising a pad having a principal surface to which an abrasive cloth paper is attached, a battery, and a power mechanism which receives supply of electric power from the battery, and so drives the pad as to move the pad in a direction parallel to the principal surface without rotating the pad are prepared; a step at which a tabular template having an opening is pressed onto the aircraft outside plate so that a defect generated on a surface of the aircraft outside plate is positioned in the opening; and a step at which the template is pressed onto the aircraft outside plate, and the pad is driven by the power mechanism in the state that the abrasive cloth paper is pressed onto an exposed portion positioned in the opening of the aircraft outside plate, whereby the exposed portion of the aircraft outside plate is polished.SELECTED DRAWING: Figure 12

Description

  The present invention relates to an aircraft skin repair method, a power tool, and an attachment.

  Stress skin structures are often used in aircraft fuselages and main wings. The stress skin structure is most typically formed by joining a skin (also referred to as a skin) that forms an outer shape to a structural member for maintaining strength. For example, an aircraft fuselage is most typically formed by joining a skin to a structure made up of a frame and a stringer. The main wing is most typically formed by joining an outer plate to a structure composed of spurs, stringers and ribs.

  Since the aircraft outer plate is a large member, there are difficulties in handling and transportation. For this reason, especially when the aircraft skin is made of metal (typically an aluminum alloy), receiving the aircraft skin from a factory or logistics base often causes damage to the surface of the received aircraft skin. (Defect) exists.

  Most of the scratches present on the surface of the aircraft skin are extremely shallow (typically 0.01 to 0.03 mm in depth), so there is no problem from the viewpoint of strength. However, since the aircraft skin is a member that affects the appearance of the aircraft, it is desirable that scratches existing on the surface of the aircraft skin be removed as much as possible. For this reason, scratches present in the aircraft skin that are not problematic in terms of strength are often repaired by polishing the aircraft skin.

  One problem in repairing scratches on the surface of an aircraft skin is that there are various restrictions on the operations that may be performed on the aircraft skin from the viewpoint of ensuring aircraft safety. The thickness of the aircraft skin is generally thin (for example, about 6 mm), and the aircraft skin alone does not have high strength. For this reason, careful handling is required when any work is performed on the aircraft skin. For example, in the processing of an aircraft skin, the use of a power tool is limited to prevent damage, and the use of a rotary tool driven by a power source (for example, an electric motor or compressed air) is not allowed.

  For this reason, the applicant's employee is carrying out the operation | work which grind | polishes and repairs the damage | wound which exists in the surface of an aircraft skin | plate at the time of application of this application by hand. However, manual repair requires a great number of man hours and increases the cost.

  From such a background, it is desired to provide a technique for reducing the number of man-hours required for repairing scratches on the surface of the aircraft skin while avoiding the problem of processing restrictions on the aircraft skin.

  In addition, about the repair method of a metal member, it is disclosed by Unexamined-Japanese-Patent No. 2016-1332072 and patent 5996789, for example. A method for repairing a polycarbonate light cover is disclosed in International Publication No. WO2014 / 016941.

JP 2016-1332072 A Patent No. 5996789 International Publication No. WO2014 / 016941

  One of the objects of the present invention is to provide a technique for reducing the man-hours required for repairing a flaw existing on the surface of an aircraft skin. Other objects and novel features of the invention will be apparent to those skilled in the art from the following disclosure.

  In one aspect of the present invention, an aircraft skin repair method includes a pad having a main surface to which an abrasive cloth is attached, a battery, a main surface that receives power supply from the battery and does not rotate the pad. Preparing a power tool having a power mechanism for driving the pad so as to move the pad in a parallel direction; and a plate-shaped template having an opening, and a defect occurring on the surface of the aircraft outer plate is placed inside the opening. Press against the aircraft skin so that it is positioned, press the template against the aircraft skin, and press the pad with the power mechanism with the abrasive cloth pressed against the exposed part located inside the opening of the aircraft skin. And polishing the exposed portion of the aircraft skin.

  In another aspect of the present invention, an electric power tool includes a pad having a main surface, an attachment attached to the main surface of the pad, a battery, power supplied from the battery, and parallel to the main surface without rotating the pad. A power mechanism for driving the pad to move the pad in any direction. The attachment includes a base portion that is bonded to the main surface of the pad, and a protruding portion that is bonded to the base portion and protrudes in a direction opposite to the pad from the base portion. Further, abrasive cloth paper is joined to the protrusion of the attachment.

  In still another aspect of the present invention, a pad is provided and is applied to a power tool configured to drive the pad to move the pad in a direction parallel to the pad main surface. An attachment is provided. The attachment includes a base portion that is bonded to the main surface of the pad and a protruding portion that protrudes from the base portion in a direction opposite to the pad. A mounting structure for mounting abrasive cloth paper is formed on the protrusion.

  ADVANTAGE OF THE INVENTION According to this invention, the man-hour required for repairing the damage | wound of the surface of an aircraft outer plate | board can be reduced, avoiding the problem of the restrictions of an aircraft outer plate | board processing.

It is a side view which shows the structure of the electric tool in one Embodiment. It is a figure which shows roughly the structure of the power mechanism which drives a pad in this embodiment. It is a figure which shows schematically the structure of the dust collection | recovery mechanism which collects dust in this embodiment. It is a perspective view which shows the structure of the attachment in this embodiment. It is a perspective view which shows the structure of the attachment in this embodiment. It is a top view which shows the structure of the attachment in this embodiment. It is a top view which shows the structure of the attachment in this embodiment. It is sectional drawing which shows the structure of the attachment in this embodiment. It is sectional drawing which shows the structure of the attachment in this embodiment. It is a figure which shows the structure which joins an attachment to a pad in this embodiment. It is sectional drawing which shows the structure which joins an abrasive cloth paper to an attachment in this embodiment. It is a flowchart which shows the repair method of the aircraft outer plate | board in this embodiment. It is a top view which shows the structure of the template in this embodiment. It is sectional drawing which shows the structure of the template in this embodiment. In this embodiment, it is a top view which shows the state which has arrange | positioned the template on the surface of the aircraft outer plate | board. In this embodiment, it is sectional drawing which shows the state which has arrange | positioned the template on the surface of an aircraft outer plate | board. It is a conceptual diagram which shows grinding | polishing of the aircraft outer plate | board using the electric tool in this embodiment. It is a conceptual diagram which shows the example of the track | orbit of the protrusion part of an attachment when an electric tool is moved in the case of grinding | polishing of the aircraft outer plate | board in this embodiment.

  Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings.

  The aircraft skin repair method of the present embodiment repairs the aircraft skin by polishing the position where the surface of the aircraft skin is scratched and its periphery. The aircraft skin is made of metal and is most typically formed of an aluminum alloy. In the present embodiment, an electric tool is used for polishing an aircraft skin. Below, the structure of the electric tool used in the repair method of the aircraft outer plate | board in this embodiment is demonstrated first.

  FIG. 1 is a side view showing a structure of an electric power tool 10 according to an embodiment. The electric tool 10 includes a main body 1, a grip 2, and a pad 3. An operator can hold the electric power tool 10 by holding the grip 2 when using the electric power tool 10. The pad 3 includes a main surface 5 to which the attachment 4 is attached. In the present embodiment, the main surface 5 is substantially rectangular. The attachment 4 is used to join the polishing cloth 6 used for polishing the outer skin of the aircraft to the main surface 5 of the pad 3. The attachment 4 includes a base 41 that is coupled to the main surface 5 of the pad 3 and a protrusion 42 that protrudes from the base 41 in the direction opposite to the pad 3. The abrasive cloth paper 6 is joined to the protrusion 42. The attachment 4 is made of a resin, for example, Teflon (registered trademark). The structure of the attachment 4 will be described later in detail. The polishing cloth 6 is composed of a sheet-like base material (for example, cloth or paper) and an abrasive bonded to the base material. In the present embodiment, sandpaper is used as the polishing cloth 6.

  The electric power tool 10 is configured to drive the pad 3 so as to move the pad 3 in a direction parallel to the main surface 5 along a predetermined path. By driving the pad 3 in a state in which the polishing cloth 6 bonded to the main surface 5 of the pad 3 by the attachment 4 is pressed against the aircraft outer plate, the aircraft outer plate can be polished.

  More specifically, in the present embodiment, the electric power tool 10 is configured to drive the pad 3 so that the pad 3 moves eccentrically. FIG. 2 is a diagram schematically showing the configuration of the power mechanism 20 that drives the pad 3. The power mechanism 20 is configured to drive the pad 3 by receiving power supplied from the battery 11, and includes an electric motor 12, a control unit 13, a pulley 14, and a base 15. The pad 3 described above is bonded to the base 15.

  The electric motor 12 receives supply of electric power from the battery 11 and rotates the rotor 16. A rotating shaft 16 a of the rotor 16 of the electric motor 12 is oriented in a direction perpendicular to the main surface 5 of the pad 3. The control unit 13 controls the supply of electric power from the battery 11 to the electric motor 12. The pulley 14 has a disk shape and is joined to the rotor 16 of the electric motor 12. Here, the pulley 14 is joined to the rotor 16 in a state where the central axis 14 a of the pulley 14 is deviated from the rotation axis 16 a of the rotor 16. The base 15 includes a cylindrical receptor 17, and a pulley 14 is accommodated inside the receptor 17 of the base 15. The inner surface of the receptor 17 provided on the base 15 is slidably pressed against the side surface of the pulley 14. When the rotor 16 of the electric motor 12 rotates, the pulley 14 moves eccentrically. The pulley 14 eccentrically moves while the side surface of the pulley 14 and the inner surface of the receptor 17 of the base 15 slide, whereby the base 15 and the pad 3 joined to the base 15 also perform eccentric movement.

  It should be noted that the power mechanism 20 is not configured to rotate the pad 3 itself in driving the pad 3. At each moment when the pad 3 is being driven, the pad 3 is translated in a direction parallel to the main surface 5, and the pad 3 itself does not rotate. That is, the electric tool 10 is not a rotary tool. The electric power tool 10 having such a configuration has a low possibility of damaging the aircraft skin and can be used for processing the aircraft skin.

  Moreover, the electric power tool 10 includes a dust collection mechanism, and is configured to be able to collect dust generated when the aircraft outer plate is polished by the dust collection mechanism. FIG. 3 is a diagram schematically illustrating a configuration of a dust collection mechanism provided in the electric tool 10. In FIG. 3, the dust collection mechanism is referred to by reference numeral 30.

  The dust collection mechanism 30 includes a chamber 31, a suction mechanism 32, and a dust collection box 33. The chamber 31 is provided inside the main body 1 of the electric power tool 10. Although not shown in FIG. 3, the chamber 31 has a structure that does not interfere with the components of the power mechanism 20 (for example, the electric motor 12, the control unit 13, and the pulley 14). The attachment 4, the pad 3, and the base 15 are provided with through holes 4 a, 3 a, and 15 a that communicate with the internal space of the chamber 31, respectively. The suction mechanism 32 is supplied with electric power from the battery 11, sucks air in the internal space of the chamber 31, and sends it to the dust collection box 33. The dust collection box 33 is provided with a filter 34 for collecting dust. When the pad 3 is driven with the abrasive cloth 6 pressed against the aircraft outer plate, dust is generated in the vicinity of the abrasive cloth 6. When the suction mechanism 32 sucks air in the internal space of the chamber 31, the air near the polishing cloth 6 is sucked through the through holes 4 a, 3 a, 15 a and the chamber 31, and the sucked air is collected in the dust collection box 33. Flow into. The air that flows into the dust collection box 33 is discharged through the filter 34. At this time, the dust contained in the air flowing into the dust collection box 33 is separated by the filter 34. Thereby, the dust generated when the aircraft outer plate is polished can be collected.

  Of the electric power tool 10 having the above-described mechanism, the constituent elements other than the attachment 4 and the polishing cloth 6 may be a generally distributed orbital sander. One problem is that commercial orbital sanders are generally not suitable for aircraft skin repair due to the large pad area. Many of the surface defects of the aircraft skin are considerably smaller than the size of the commercial orbital sander pad, and many of the commercial orbital sanders are not suitable for repairing the aircraft skin.

  In view of such a situation, in this embodiment, the attachment 4 is attached to the main surface 5 of the pad 3. The attachment 4 is for relaxing restrictions on the size of the polishing cloth in the specification of the electric power tool. By using the attachment 4, the polishing cloth 6 having a size suitable for repairing the aircraft outer plate can be attached to the electric tool 10.

  4A and 4B are perspective views showing the structure of the attachment 4. 4A is a perspective view seen from the direction in which the protrusion 42 of the attachment 4 can be seen, and FIG. 4B is from the direction in which the contact surface 41a contacting the main surface 5 of the pad 3 of the base 41 of the attachment 4 can be seen. FIG. 5A is a plan view of the attachment 4 as seen from the direction in which the protruding portion 42 can be seen, and FIG. 5B is a plan view of the attachment 4 as seen from the direction in which the contact surface 41a of the base 41 of the attachment 4 can be seen. 6A and 6B are cross-sectional views showing the structure of the attachment 4. 6A illustrates the structure of the attachment 4 in the section AA shown in FIGS. 5A and 5B, and FIG. 6B shows the attachment 4 in the section BB shown in FIGS. 5A and 5B. The structure of is shown. FIG. 7 is a plan view showing a structure in which the attachment 4 is bonded to the pad 3, and FIG. 8 is a cross-sectional view showing a structure in which the polishing cloth 6 is attached to the attachment 4.

  With reference to FIG. 4A and FIG. 4B, the attachment 4 is provided with the base 41 and the protrusion part 42 as above-mentioned. As shown in FIGS. 4A, 4B, and 6A, a counterbore 43 is formed in the base 41. The counterbore 43 is used to connect the attachment 4 to the main surface 5 of the pad 3. Specifically, as shown in FIG. 7, when the attachment 4 is coupled to the main surface 5 of the pad 3, the bolt 44 is inserted into the counterbore 43 with the attachment 4 being in contact with the main surface 5. Is done. The pad 3 is provided with a through hole (not shown) through which the bolt 44 passes, and the base 15 is formed with a female screw. The attachment 4 is attached to the main surface 5 of the pad 3 by screwing the bolt 44 into a female screw formed on the base 15.

  As shown in FIGS. 4B and 5B, a circular groove 45 is formed in the base 41, and a through hole 4 a is formed in the bottom surface of the groove 45. As illustrated in FIGS. 4A and 5A, the through hole 4 a is located in the vicinity of the protruding portion 42. The through hole 4 a of the attachment 4 is provided inside the main body 1 through the through holes 3 a and 15 a provided in the pad 3 and the base 15 when the attachment 4 is attached to the main surface 5 of the pad 3. It is arranged so as to communicate with the chamber 31. The structure in which the through hole 4 a is provided in the attachment 4 is adopted so that dust generated near the polishing cloth 6 can be recovered by the dust recovery mechanism 30.

  As shown in FIGS. 4A and 5A, the projecting portion 42 has a side surface 42a formed in a cylindrical shape. The size of the abrasive cloth 6 attached to the attachment 4 is determined by the diameter of the protrusion 42. In the present embodiment, the diameter of the protrusion 42 is smaller than the length of any side of the main surface 5 of the pad 3, so that even if the pad 3 is large, the polishing cloth has a size suitable for repairing the aircraft skin. Paper 6 can be attached.

  As shown in FIG. 6B, the protrusion 42 has a recess 42b. The recess 42 b of the protrusion 42 is used as a mounting structure used for mounting the polishing cloth 6 to the attachment 4. Specifically, as shown in FIG. 8, when the abrasive cloth 6 is attached to the attachment 4, a disk-shaped elastic adapter 7 is joined to the protrusion 42, and the abrasive cloth 6 is attached to the elastic adapter 7. Be joined. At this time, the elastic adapter 7 is joined to the protrusion 42 so that a part of the elastic adapter 7 is accommodated in the recess 42b. The elastic adapter 7 is formed of an elastic body, for example, rubber. The structure in which the elastic adapter 7 made of an elastic body is joined to the protruding portion 42 of the attachment 4 made of resin, and the polishing cloth 6 is joined to the elastic adapter 7 performs the work of repairing the aircraft skin. In this case, it is suitable for suppressing the occurrence of unnecessary scratches on the aircraft skin.

  Then, the repair method which repairs the damage | wound of an aircraft outer plate | board using the electric tool 10 and the attachment 4 of the above-mentioned structure is demonstrated.

  FIG. 9 is a flowchart illustrating an aircraft skin repair method according to an embodiment.

  First, a template is placed on the aircraft outer plate (step S01). FIG. 10A is a top view showing the structure of the template 51 arranged on the aircraft outer plate, and FIG. 10B is a cross-sectional view showing the structure of the template 51. FIG. 11A is a top view showing a state in which the template 51 is arranged on the surface of the aircraft skin, and FIG. 11B is a cross-sectional view. In FIG. 11A and FIG. 11B, the aircraft skin is indicated by reference numeral 60.

  As shown in FIG. 10A, the template 51 has a circular opening 51a. The opening 51 a is provided to define a range in which the aircraft outer plate 60 is polished by the electric tool 10. As illustrated in FIG. 10B, the template 51 includes a main body plate 52 and a protective sheet 53. The protective sheet 53 is joined to the main body plate 52. The main body plate 52 is made of resin, for example, Teflon, and the protective sheet 53 is made of an elastic body, for example, rubber. The opening 51 a is formed so as to penetrate both the main body plate 52 and the protective sheet 53. Moreover, the opening 51a of the template 51 is formed so that the diameter is larger than the diameter of the side surface 42a of the protrusion part 42 of the attachment 4 mentioned above.

  As shown in FIGS. 11A and 11B, the template 51 is disposed on the aircraft skin 60 such that the scratch 60a existing in the aircraft skin 60 is located inside the opening 51a. In one embodiment, a plurality of templates 51 having openings 51a of various diameters are prepared, and the template 51 actually used for repair is such that the diameter of the openings 51a is the size of the damage 60a of the aircraft skin 60 to be repaired. May be selected as appropriate to the situation. In order to prevent the surface of the aircraft skin 60 from being damaged by the template 51, the template 51 is disposed on the aircraft skin 60 so that the protective sheet 53 contacts the surface of the aircraft skin 60.

  Subsequently, as illustrated in FIG. 9, a portion (exposed portion) of the surface of the aircraft outer plate 60 positioned inside the opening 51 a is polished using the above-described electric power tool 10 ( Step S02). FIG. 12 is a conceptual diagram showing polishing of the aircraft outer plate 60 using the power tool 10 in step S02.

  When using the electric power tool 10, the elastic adapter 7 is attached to the recess 42 b of the protrusion 42 of the attachment 4, and the abrasive cloth 6 is joined to the elastic adapter 7. In this state, the attachment 4 is bonded to the main surface 5 of the pad 3. The structure in which the polishing cloth 6 is joined to the protrusion 42 of the attachment 4 through the elastic adapter 7 formed of an elastic body is unnecessary for the aircraft outer plate 60 when the aircraft outer plate 60 is repaired. It is suitable for suppressing the occurrence of scratches.

  When polishing the aircraft outer plate 60, the power of the electric tool 10 is turned on while the polishing cloth 6 is in contact with the exposed portion of the surface of the aircraft outer plate 60 (the portion located inside the opening 51 a). Then, the driving of the pad 3 is started. When the driving of the pad 3 is started, the pad 3 performs an eccentric motion, and the polishing cloth 6 bonded to the pad 3 by the attachment 4 slides on the surface of the aircraft outer plate 60. As a result, the surface of the aircraft outer plate 60 is polished by the polishing cloth 6. As shown in FIG. 13, the operator appropriately moves the power tool 10 while holding the grip 2, so that the portion located inside the opening 51 a on the surface of the aircraft skin 60 is entirely Polished. In FIG. 13, an example of the trajectory of the protrusion 42 of the attachment 4 when the electric tool 10 is moved is illustrated by arrows 54 and 55. The aircraft outer plate 60 is polished until the scratch 60a is removed.

  In this polishing, the template 51 plays a role of defining a range of the surface of the aircraft outer plate 60 to be polished. By defining the range to be polished by the template 51, the necessary minimum range in the vicinity of the scratch 60a on the surface of the aircraft outer plate 60 can be polished. In addition, since the opening 51a formed in the template 51 is circular and the side surface 42a of the protrusion 42 of the attachment 4 is cylindrical, the polishing of the aircraft outer plate 60 with the electric power tool 10 is performed. The side surface of the opening 51a and the side surface 42a of the protrusion 42 of the attachment 4 are in smooth contact. This is effective for enabling the operator to smoothly move the power tool 10 when the aircraft outer plate 60 is polished.

  After the polishing with the electric power tool 10 is completed, finish polishing by manual work may be performed as shown in FIG. 9 (step S03). The finish polishing may be performed using, for example, a commercially available polishing pad, for example, Scotch Bright (registered trademark). This completes the repair of the damage to the aircraft skin 60.

  According to the aircraft skin repair method of the present embodiment, since the surface of the aircraft skin 60 is polished using the electric tool 10, the number of man-hours required for repairing the aircraft skin 60 is reduced as compared with manual repair. It can be significantly reduced. At this time, since the electric power tool 10 used for repair is configured to drive the pad 3 in a direction parallel to the main surface 5 without rotating the pad 3 itself, the aircraft outer plate 60 is damaged during work. The possibility is low, and restrictions in processing the aircraft skin 60, for example, restrictions on prohibition of the use of rotary tools can be avoided.

  Further, in the aircraft skin repair method of the present embodiment, since the attachment 4 is attached to the main surface 5 of the pad 3 of the electric tool 10, the abrasive cloth 6 having a size suitable for repairing the aircraft skin 60 is used. Can be used. This is effective to improve the working efficiency while minimizing the range in which the aircraft skin 60 is polished.

  Although the embodiment of the present invention has been specifically described above, the present invention is not limited to the above embodiment. Those skilled in the art will appreciate that the invention may be practiced with various modifications.

1: Main body 2: Grip 3: Pad 3a: Through hole 4: Attachment 4a: Through hole 5: Main surface 6: Polishing cloth 7: Elastic adapter 10: Electric tool 11: Battery 12: Electric motor 13: Control unit 14: Pulley 14a: Center shaft 15: Base 15a: Through hole 16: Rotor 16a: Rotating shaft 17: Receptor 20: Power mechanism 30: Dust collection mechanism 31: Chamber 32: Suction mechanism 33: Dust collection box 34: Filter 41: Base 41a : Contact surface 42: Protruding portion 42a: Side surface 42b: Recess 43: Hole 44: Bolt 45: Groove 51: Template 51a: Opening 52: Body plate 53: Protection sheet 54: Arrow 55: Arrow 60: Aircraft outer plate 60a: Scratch

Claims (14)

A repair method for an aircraft skin,
A pad having a main surface to which a polishing cloth is attached; a battery; and the pad that receives power from the battery and moves the pad in a direction parallel to the main surface without rotating the pad. Preparing an electric tool including a power mechanism for driving
Polishing the region including scratches on the surface of the aircraft skin by driving the pad by the power mechanism,
The abrasive cloth is bonded to the main surface of the pad using an attachment,
The attachment is
A base joined to the main surface of the pad;
A protrusion that is joined to the base and protrudes in a direction opposite to the pad from the base;
The method of repairing an aircraft skin, wherein the abrasive cloth paper is coupled to the protrusion. An aircraft skin repair method according to claim 1,
The polishing step includes
Pressing a plate-like template having an opening against the aircraft skin so that the scratch on the surface of the aircraft skin is located inside the opening;
Repairing the aircraft skin, comprising: polishing the exposed portion by driving the pad by the power mechanism with the abrasive cloth pressed against the exposed portion located inside the opening of the aircraft skin Method. An aircraft skin repair method according to claim 2,
The side surface of the protrusion of the attachment is cylindrical.
The opening of the template is circular;
A method of repairing an aircraft skin, wherein the diameter of the protrusion is smaller than the diameter of the opening. An aircraft skin repair method according to claim 2,
The protrusion of the attachment is joined to an elastic adapter formed of an elastic body,
A method of repairing an aircraft skin, wherein the abrasive cloth is joined to the elastic adapter. An aircraft skin repair method according to claim 2,
The electric tool is
A chamber;
A dust collection box;
A suction mechanism for sucking air from the chamber and feeding it into a dust collection box;
The method of repairing an aircraft skin, wherein the attachment and the pad have a through hole communicating with the chamber. A pad having a main surface;
An attachment attached to the main surface of the pad;
Battery,
A power mechanism that receives power from the battery and drives the pad to move the pad in a direction parallel to the main surface without rotating the pad;
The attachment is
A base joined to the main surface of the pad;
A protrusion that is joined to the base and protrudes in a direction opposite to the pad from the base;
A power tool in which a polishing cloth is joined to the protruding portion of the attachment. The electric tool according to claim 6,
The side surface of the protrusion of the attachment is cylindrical.
The principal surface of the pad is substantially rectangular;
The power tool, wherein a diameter of the protruding portion is smaller than a length of any side of the main surface. The electric tool according to claim 6,
The protrusion of the attachment is joined to an elastic adapter formed of an elastic body,
An electric tool in which the abrasive cloth is joined to the elastic adapter. The electric tool according to claim 7,
In addition,
A chamber;
A dust collection box;
A suction mechanism for sucking air from the chamber and feeding it into a dust collection box,
The attachment and the pad have a through hole communicating with the chamber. The electric tool according to any one of claims 6 to 9,
The electric tool in which the attachment is formed of resin. An attachment joined to the main surface of the pad, the pad being applied to a power tool configured to drive the pad to move the pad in a direction parallel to the main surface of the pad. There,
A base joined to the main surface of the pad;
A protrusion projecting from the base in the opposite direction to the pad;
An attachment in which a mounting structure for mounting abrasive cloth is formed on the protrusion. The attachment according to claim 11,
The attachment has a cylindrical side surface. The attachment according to claim 11,
An attachment in which a through hole communicating with a chamber of a dust collection mechanism provided in the electric tool is formed in the base. The attachment according to any one of claims 11 to 13,
An attachment in which the base and the protrusion are made of resin.

Images