CN110814892A - In-situ polishing tool for inner wall of large-size coaxial hole of airplane and using method of in-situ polishing tool - Google Patents

Abstract

The invention discloses an in-situ polishing tool for the inner wall of a large-sized coaxial hole of an aircraft and a method for using the same, and relates to the technical field of workpiece polishing of the coaxial hole. The polishing tool of the present invention includes a rotating column that is coaxially clearance-fitted with the through hole, a polishing and grinding ring mounted on the rotating column, and a stop ring mounted on the rotating column to precisely limit the polishing and grinding ring; the outer peripheral side of the rotating column is A convex ring, an annular groove disposed between two adjacent convex rings, and a rotating connecting shaft disposed at an outer end of the rotating column are arranged around; the polishing and grinding ring includes a sleeve and a rotating ring, and the outer surface of the rotating ring passes through the bar-shaped The slotted wrap is fitted with sanding paper, and the stop rings are symmetrically mounted on both sides of each rotating ring. The invention realizes the in-situ polishing and repair of the inner wall of the large-size coaxial hole on the aircraft part, improves the repair work efficiency, avoids the damage to the aircraft part itself and the surrounding structure caused by repeated disassembly and assembly, avoids the elliptical phenomenon caused by the grinding deviation of the aperture, and improves the polishing and repairing performance. Tool stability during movement.

Description

An in-situ polishing tool for the inner wall of a large-size coaxial hole in an aircraft and a method of using the same

technical field

The invention belongs to the technical field of coaxial hole workpiece polishing, and in particular relates to an in-situ polishing tool for the inner wall of a large-sized coaxial hole of an aircraft and a method for using an in-situ polishing tool for the inner wall of the large-sized coaxial hole of an aircraft.

Background technique

In the prior art, the polishing and repairing of the inner wall of the large-size coaxial hole, including but not limited to fork lugs and large-size coaxial hole workpieces, all use the parts off-position and polishing on the machine tool. This repair method has limitations and can only be used. It is impossible to repair the inner wall of the part hole in-situ, and it is impossible to repair the inner wall of the part hole that cannot be dislocated due to space constraints. Therefore, in view of the above problems, the parts are not disassembled and disassembled to avoid repeated disassembly. On the basis of fixing the damage caused to the part itself and the surrounding structure, ensuring the accuracy of the inner wall size of the hole after polishing and repairing, and avoiding the ellipse phenomenon caused by the grinding deviation of the aperture, an in-situ polishing tool for the inner wall of a large-size coaxial hole and a method for using the same are provided. Solving the above problems has practical significance.

SUMMARY OF THE INVENTION

An in-situ polishing tool for the inner wall of a large-size coaxial hole of an aircraft and a method for using the same of the present invention realize the in-situ polishing and repair of the inner wall of the large-size coaxial hole on a part, improve the repair work efficiency, and avoid repeated disassembly and assembly on the part itself and its surroundings. The damage caused by the structure, the polishing tool ensures the accuracy of the inner wall size of the hole after polishing and repairing, avoids the ellipse phenomenon caused by the grinding deviation of the aperture, and improves the stability of the tool during the polishing and repairing movement.

In order to solve the above-mentioned technical problems, the present invention is achieved through the following technical solutions:

An in-situ polishing tool for the inner wall of a large-size coaxial hole in an aircraft of the present invention and a method of using the same, the polishing tool is used for polishing and grinding the inner wall of the through hole including but not limited to a workpiece with a large-size coaxial hole such as a fork lug, The polishing tool includes a rotating column that is coaxially gap-fitted with the through hole, a polishing and grinding ring installed on the rotating column, and a stop ring installed on the rotating column to precisely limit the polishing and grinding ring;

The outer peripheral side of the rotating column is provided with a convex ring corresponding to the through hole and with clearance fit, an annular groove disposed between two adjacent convex rings, and a rotating connecting shaft disposed at an outer end of the rotating column;

The polishing and grinding ring includes a sleeve and a rotating ring arranged at the end of the sleeve. The side of the rotating ring is provided with a strip-shaped slit, and the outer side of the rotating ring is installed by wrapping around the strip-shaped slit. There is grinding sandpaper, and the grinding sandpaper on the outer wall of the rotating ring is pressed and fitted with the inner peripheral side wall of the through hole;

The retaining rings are symmetrically installed on both sides of each rotating ring.

Further, the end of the rotating connecting shaft is fixedly installed in the drill chuck or conical sleeve of the air drill or electric drill and rotates synchronously therewith.

Further, first threads are uniformly distributed around the outer side wall of the convex ring.

Further, the inner peripheral side wall of the rotating ring is provided with a second thread connected to the first thread thread, and the outer peripheral side wall of the rotating ring is uniformly provided with rotating anti-skid lines.

Further, the retaining ring adopts a spiral retaining ring.

A method for using an in-situ polishing tool for the inner wall of an aircraft large-size coaxial hole, comprising the following steps:

S01. Select the polishing and grinding ring: according to the size of the workpiece to be polished, select the polishing and grinding ring of the size corresponding to the size of the through hole;

S02, install grinding sandpaper: install grinding sandpaper through strip slits on the polishing and grinding ring, so that the grinding sandpaper is attached to the outer peripheral side wall of the sleeve;

S03. Install the polishing tool: first set the polishing ring with the sandpaper installed between the two fork ears of the large-size coaxial hole workpiece, and arrange stoppers on both sides of each polishing ring Through the rotating column, it passes through the stop ring, the through hole, and the polishing ring in turn, so that the stop ring and the polishing ring are respectively sleeved between the annular grooves, and then the ring grooves are set between the two fork ears. The two sides are screwed into the convex rings on both sides respectively, so that the second thread on the rotating ring is matched with the first thread thread on the convex ring, until the two polishing and grinding rings are just clamped to the two fork ears. The grinding sandpaper on the outer peripheral side wall of the sleeve is pressed and fitted with the inner wall of the through hole to be ground. The stop rings on both sides of the polishing ring are used to limit the screw position: finally, the end of the rotating connecting shaft is fixedly connected with the drill chuck or conical sleeve of the air drill or electric drill;

S04. Grinding the workpiece: Fix the bottom end of the fork lug large-sized coaxial hole workpiece, start the air drill or electric drill, grind and polish the inner wall of the through hole until the grinding is completed, disassemble the polishing tool in reverse according to the above steps, and take out The workpiece after grinding and polishing is completed.

The present invention has the following beneficial effects:

1. The present invention realizes the in-situ polishing and repair of the inner wall of the large-size coaxial hole on the aircraft part, improves the repair work efficiency, and avoids the damage to the part itself and the surrounding structure caused by repeated disassembly and assembly. High precision, avoiding the ellipse phenomenon caused by the grinding deviation of the aperture, and improving the stability of the tool during the polishing and repairing movement.

2. The polishing tool of the present invention is based on the concept of ergonomic humanization and comfortable design, the overall structure is simple and practical, and can realize the in-situ polishing and repair of the inner wall of the large-sized coaxial hole on the fork lug parts. The conventional method overcomes the disadvantages of using limitations, and has the advantages of comprehensive functions, low cost, simplified structure, easy manufacture, safety and reliability, energy saving and environmental protection, and easy operation.

Of course, it is not necessary for any product embodying the present invention to achieve all of the above-described advantages simultaneously.

Description of drawings

In order to illustrate the technical solutions of the embodiments of the present invention more clearly, the following briefly introduces the accompanying drawings used in the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can also be obtained from these drawings without any creative effort.

1 is a schematic structural diagram of an aircraft large-size coaxial hole inner wall in-situ polishing tool of the present invention installed on a fork lug large-size coaxial hole workpiece;

2 is a schematic structural diagram of an in-situ polishing tool for the inner wall of a large-size coaxial hole of an aircraft according to the present invention;

Fig. 3 is the structural representation of the rotating column of the present invention;

Fig. 4 is the left side view of the structure of Fig. 3;

Fig. 5 is the structural representation of the polishing and grinding ring of the present invention;

Fig. 6 is the right side view of the structure of Fig. 5;

7 is a schematic structural diagram of the installation of the polishing ring and the polishing sandpaper of the present invention;

Fig. 8 is the right side view of the structure of the fork lug type large-size coaxial hole type workpiece;

9 is a step diagram of a method of using an in-situ polishing tool for the inner wall of an aircraft large-size coaxial hole according to the present invention;

In the accompanying drawings, the list of components represented by each number is as follows:

1-Rotating column, 101-Protruding ring, 1011-First thread, 102-Annular groove, 103-Rotating connecting shaft, 2-Polishing grinding ring, 201-Rotating ring, 2011-Rotating anti-skid pattern, 2012-Second thread, 202-Sleeve, 2021-Slotted strip, 3-Stop ring, 4-Sandpaper, 5-Fork lug large size coaxial hole workpiece, 501-Through hole.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

In the description of the present invention, it should be understood that the terms "peripheral side", "an outer end", "end", "side", "lateral", etc. indicate orientation or positional relationships, and are only for the convenience of describing the present invention. The invention and simplified description do not indicate or imply that the components or elements referred to must have a particular orientation, be constructed and operate in a particular orientation, and therefore should not be construed as limiting the invention.

Please refer to FIGS. 1-8 , an in-situ polishing tool for the inner wall of a large-sized coaxial hole in an aircraft of the present invention, the polishing tool is used for the through hole 501 of the workpiece 5 including but not limited to a large-sized coaxial hole such as a fork lug. The inner wall is polished and polished, and the polishing tool includes a rotating column 1 that is coaxially gap-fitted with the through hole 501, a polishing and grinding ring 2 installed on the rotating column 1, and a stopper installed on the rotating column 1 to precisely limit the polishing and grinding ring 2. moving ring 3;

The outer peripheral side of the rotating column 1 is provided with a convex ring 101 corresponding to the through hole 501 and with clearance fit, an annular groove 102 disposed between two adjacent convex rings 101 , and a rotating connection disposed at an outer end of the rotating column 1 . axis 103;

The polishing and grinding ring 2 includes a sleeve 202 and a rotating ring 201 arranged at the end of the sleeve 202. The side of the rotating ring 201 is provided with a strip-shaped slit 2021. Sandpaper 4 is installed on the wrap, and the sandpaper 4 on the outer wall of the rotating ring 201 is pressed against the inner peripheral side wall of the through hole 501 ; the stop ring 3 is symmetrically installed on both sides of each rotating ring 201 .

Wherein, the end of the rotating connecting shaft 103 is fixedly installed in the drill chuck or conical sleeve of the air drill or electric drill and rotates synchronously therewith.

The outer sidewall of the convex ring 101 is provided with first threads 1011 evenly distributed around it.

The inner peripheral sidewall of the rotating ring 201 is provided with second threads 2012 threadedly connected to the first thread 1011 , and the outer peripheral sidewall of the rotating ring 201 is provided with rotating anti-skid lines 2011 uniformly distributed around.

Among them, the retaining ring 3 adopts a spiral retaining ring.

As shown in Figure 9, a method for using an in-situ polishing tool for the inner wall of a large-size coaxial hole in an aircraft includes the following steps:

S01, select the polishing and grinding ring 2: select the polishing and grinding ring 2 of the size corresponding to the size of the through hole 501 according to the size of the workpiece to be polished;

S02, install the grinding sandpaper 4: install the grinding sandpaper 4 on the polishing and grinding ring 2 via the strip slit 2021, so that the grinding sandpaper 4 is attached to the outer peripheral side wall of the sleeve 202;

S03, install the polishing tool: first set the polishing and grinding ring 2 with the polished sandpaper 4 installed between the two fork ears of the large-size coaxial hole type workpiece 2, and arrange it on both sides of each polishing and grinding ring 2 The stop ring 3 passes through the stop ring 3, the through hole 501, and the polishing and grinding ring 2 in sequence through the rotating column 1, so that the stop ring 3 and the polishing and grinding ring 2 are respectively sleeved between the annular grooves 102, and then set by The protruding rings 101 on the two sides of the annular groove 102 between the two prongs are screwed in, so that the second thread 2012 on the rotating ring 201 is threaded with the first thread 1011 on the protruding ring 101 until the two are polished and ground. The ring 2 is just clamped to the two pronged ears. At this time, the sandpaper 4 on the outer peripheral side wall of the sleeve 202 is pressed and fitted with the inner wall of the through hole 501 to be polished. The side walls of the two rotating rings 201 face the side wall of the sleeve 202. Respectively cooperate with the side walls of the two fork ears to limit the position, and the stop ring 3 on both sides of the polishing and grinding ring 2 is used to limit the screw position: Finally, connect the end of the rotating connecting shaft 103 to the drill chuck of an air drill or electric drill or The conical sleeve is fixedly connected;

S04. Grinding the workpiece: fix the bottom end of the fork lug large-sized coaxial hole workpiece 5, start the air drill or electric drill, grind and polish the inner wall of the through hole 501 until the grinding is completed, and disassemble the polishing tool reversely according to the above steps , take out the workpiece after grinding and polishing.

The invention realizes the in-situ polishing and repair of the inner wall of the large-sized coaxial hole on the aircraft part, improves the repair work efficiency, and avoids the damage to the part itself and the surrounding structure caused by repeated disassembly and assembly. It avoids the ellipse phenomenon caused by the grinding deviation of the aperture, and improves the stability of the tool during the polishing and repairing movement. The polishing tool of the invention is based on the concept of ergonomic humanization and comfortable design, the overall structure is simple and practical, and can realize the in-situ polishing and repair of the inner wall of the large-sized coaxial hole on the fork lug parts. The conventional method overcomes the disadvantages of using limitations, and has the advantages of comprehensive functions, low cost, simplified structure, easy manufacture, safety and reliability, energy saving and environmental protection, and easy operation.

The above-disclosed preferred embodiments of the present invention are provided only to help illustrate the present invention. The preferred embodiments do not exhaust all the details, nor do they limit the invention to only the described embodiments. Obviously, many modifications and variations are possible in light of the content of this specification. The present specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can well understand and utilize the present invention. The present invention is to be limited only by the claims and their full scope and equivalents.

Claims (6)

1. An in-situ polishing tool for the inner wall of a large-size coaxial hole of an airplane, which is used for polishing and grinding the inner wall of a through hole (501) of a workpiece (5) including but not limited to a fork-ear large-size coaxial hole, and is characterized in that:

the polishing tool comprises a rotating column (1) which is coaxially in clearance fit with the through hole (501), a polishing and grinding ring (2) which is arranged on the rotating column (1), and a stop ring (3) which is arranged on the rotating column (1) and used for accurately limiting the polishing and grinding ring (2);

the periphery side of the rotating column (1) is provided with convex rings (101) which correspond to the through holes (501) and are in clearance fit with the through holes in a surrounding manner, an annular groove (102) arranged between every two adjacent convex rings (101), and a rotating connecting shaft (103) arranged at one outer end part of the rotating column (1);

the polishing and grinding ring (2) comprises a sleeve (202) and a rotating ring (201) arranged at the end of the sleeve (202), a strip-shaped slot (2021) is transversely formed in the side of the rotating ring (201), grinding abrasive paper (4) is wound and mounted on the outer side surface of the rotating ring (201) through the strip-shaped slot (2021), and the grinding abrasive paper (4) on the outer wall of the rotating ring (201) is attached to the inner peripheral side wall of the through hole (501) in an extrusion mode;

the stop rings (3) are symmetrically arranged on two sides of each rotating ring (201).

2. The in-situ polishing tool for the inner wall of the large-size coaxial hole of the airplane as claimed in claim 1, wherein the end part of the rotating connecting shaft (103) is fixedly arranged in a drill chuck or a conical sleeve of an air drill or an electric drill and rotates synchronously with the drill chuck or the conical sleeve.

3. The in-situ polishing tool for the inner wall of the large-size coaxial hole of the airplane as claimed in claim 1, wherein the outer side wall of the convex ring (101) is uniformly provided with first threads (1011) around.

4. The in-situ polishing tool for the inner wall of the large-size coaxial hole of the airplane as claimed in claim 1, wherein second threads (2012) connected with the first threads (1011) are uniformly distributed around the inner peripheral side wall of the rotating ring (201), and rotating anti-skid threads (2011) are uniformly distributed around the outer peripheral side wall of the rotating ring (201).

5. The in-situ polishing tool for the inner wall of the large-size coaxial hole of the airplane as claimed in claim 1, wherein the stop ring (3) is a spiral retainer ring.

6. The use method of the in-situ polishing tool for the inner wall of the large-size coaxial hole of the airplane as claimed in any one of claims 1 to 5, is characterized by comprising the following steps:

s01, selecting a polishing and grinding ring (2): a polishing and grinding ring (2) of which the size corresponds to that of the through hole (501) is selected according to the size of the ground workpiece;

s02, mounting and polishing abrasive paper (4): installing polishing abrasive paper (4) on the polishing and polishing ring (2) through a strip-shaped slit (2021), and enabling the polishing abrasive paper (4) to be attached to the peripheral side wall of the sleeve (202) in a surrounding mode;

s03, mounting a polishing tool: the polishing and grinding ring (2) provided with the polishing and grinding sand paper (4) is arranged between two fork lugs of a fork lug type large-size coaxial hole type workpiece (2), stop rings (3) are arranged on two sides of each polishing and grinding ring (2), the stop rings (3), through holes (501) and the polishing and grinding rings (2) sequentially penetrate through a rotating column (1), so that the stop rings (3) and the polishing and grinding rings (2) are respectively sleeved between annular grooves (102), then convex rings (101) arranged on the annular grooves (102) between the two fork lugs and towards two sides respectively are screwed in, so that second threads (2012) on the rotating ring (201) are in threaded fit with first threads (1011) on the convex rings (101) until the two polishing and grinding rings (2) clamp the two fork lugs, and at the moment, the polishing and grinding sand paper (4) on the peripheral side wall of the sleeve (202) is attached to the inner wall of the polished through holes (501) in an extruding manner, the side walls of the two rotating rings (201) facing the sleeve (202) are respectively in clearance fit with the side walls of the two fork lugs for limiting, and the stop rings (3) on the two sides of the polishing and grinding ring (2) are used for limiting the spiral position: finally, the end of the rotary connecting shaft (103) is fixedly connected with a drill chuck or a conical sleeve of an air drill or an electric drill;

s04, grinding the workpiece: fixing the bottom end of a fork ear type large-size coaxial hole type workpiece (5), starting an air drill or an electric drill, polishing the inner wall of the through hole (501) until polishing is completed, reversely disassembling a polishing tool according to the steps, and taking out the polished workpiece.

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