Aircraft wing skin crack removal device

Abstract

The present invention discloses a device for removing cracks from an aircraft wing skin, belonging to the technical field of aircraft maintenance equipment. The device comprises an outer shell, a removal tool, and a clamping mechanism. The device is characterized in that: a clamping mechanism and an elastic protective mechanism are installed inside the outer shell, the elastic protective mechanism is connected to the clamping mechanism, and the removal tool is clamped and installed inside the clamping mechanism; a guide sleeve is sleeved on the upper end of the clamping mechanism and slidably engages with the clamping mechanism; a guide blind hole is provided at the lower end of the outer shell, the upper end of the guide sleeve is inserted into the guide blind hole of the outer shell and slidably engages with the guide blind hole, and the upper end of the guide sleeve is connected to the top wall of the guide blind hole of the outer shell via a compression spring; the guide sleeve is connected to the elastic protective mechanism, and a pressure sensor is connected to a control valve of a telescopic cylinder via a circuit. Compared with the prior art, the device has the advantage of preventing damage to the wing rear beam when removing cracks from the lower wing skin.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft maintenance equipment, in particular to an aircraft wing skin crack removal device. Background Art

[0002] After a certain number of years of operation, the E190 aircraft will develop fatigue cracks on the wing skin at ribs 9-11. Therefore, this area requires regular inspection and modification. If cracks are found during inspection, they need to be removed and then repaired with reinforcement plates.

[0003] Cracks on aircraft wings generally occur at the fastener holes and continue to expand outward. The structure here has several layers stacked together, such as the wing lower skin and the wing rear beam. The cracks only occur on the wing lower skin. Therefore, it is only necessary to cut out the cracks in the wing lower skin. The traditional cutting method is to first remove as many fasteners as possible around the crack, and then insert a layer of steel plate between the two side structures to prevent damage to the lower structure, and then use a hand drill to continuously drill holes around the crack to form an incision, and finally trim the incision to the specified size. The above method is time-consuming and labor-intensive. When the structural thickness of the wing lower skin and the wing rear beam is large, it is difficult to insert a whole steel plate between the two sides. Therefore, it is easy to cause damage to the lower structure during cutting. Summary of the Invention

[0004] The purpose of the present invention is to provide an aircraft wing skin crack removal device to address the deficiency of the prior art that the wing rear beam is easily damaged when the cracks in the wing lower skin are removed, so as to achieve the purpose of preventing damage to the wing rear beam when the cracks in the wing lower skin are removed.

[0005] The present invention provides an aircraft wing skin crack removal device, comprising an outer shell, a removal tool and a clamping mechanism; the characteristics are that: a clamping mechanism and an elastic protective mechanism are installed inside the outer shell, the elastic protective mechanism is connected to the clamping mechanism, and a removal tool is clamped and installed inside the clamping mechanism; the upper end of the clamping mechanism is sleeved with a guide sleeve that slides with it; the lower end of the outer shell is provided with a guide blind hole, the upper end of the guide sleeve is inserted into the guide blind hole of the outer shell, and slides with the guide blind hole, and the upper end of the guide sleeve is connected to the top wall of the guide blind hole of the outer shell by a compression spring; the guide sleeve is connected to the elastic protective mechanism, the elastic protective mechanism comprises a positioning block, a limit plate, a lifting plate, a fixed block and a telescopic cylinder, the inner part of the outer shell is provided with a guide groove, the guide groove and the slide groove are connected by a connecting hole, a limit plate is installed in the guide groove, and the limit The positioning plate slides in cooperation with the guide groove, and a positioning block is installed in the connecting hole. The positioning block elastically slides in cooperation with the connecting hole. A positioning groove is provided on the guide sleeve, and the inner end of the positioning block is inserted in the positioning groove of the guide sleeve, and the outer end is pressed against the limit plate; the limit plate is located below the positioning block and is provided with a driving groove, and the upper end wall of the driving groove is provided with an inclined surface, and the outer end of the positioning block is provided with an inclined surface corresponding to the inclined surface of the driving groove; the upper end of the guide groove of the outer shell is provided with a placement cavity, and the placement cavity is connected with the guide groove, and the upper end of the limit plate passes through the guide groove and is connected to the lifting plate, and a corresponding fixed block is provided above the lifting plate stroke, and the fixed block is installed on the outer wall of the guide sleeve, and the upper end of the lifting plate is connected to the telescopic cylinder, and the telescopic cylinder is installed in the placement cavity of the outer shell; a pressure sensor is installed on the top of the guide sleeve cavity, and the pressure sensor is connected to the control valve that controls the telescopic cylinder through the circuit.

[0006] Furthermore, the clamping mechanism includes a mounting sleeve, a tightening ring body, an arc-shaped clamping plate and a driving rod. The mounting sleeve is provided with a cavity with an opening at the lower end, an external thread is provided on the outer wall of the lower end of the mounting sleeve, an annular groove is provided on the inner wall of the mounting sleeve, and a plurality of guide through holes evenly distributed in a circular shape are provided on the outer wall of the mounting sleeve. The guide through holes are connected to the annular groove. The inner end of the driving rod passes through the guide through holes and is connected to the outer end of the arc-shaped clamping plate. The outer end of the arc-shaped clamping plate is placed in the groove, and the outer end of the driving rod is exposed at the outer end of the mounting sleeve; the tightening ring body is provided with a threaded hole, and the lower end of the threaded hole is provided with a tapered hole. The threaded hole of the tightening ring body is threadedly matched with the external thread of the mounting sleeve, and the outer end of the driving rod is pressed against the inner wall of the tapered hole.

[0007] Furthermore, two symmetrically distributed threaded blind holes are provided on the outer wall of the tightening ring body, and the threaded blind holes of the tightening ring body are threadedly connected to the operating rod.

[0008] Furthermore, a guide block is installed on the outer wall of the guide sleeve, a slide groove is provided on the inner wall of the guide blind hole of the outer shell, and the guide block is placed in the slide groove; a positioning groove is provided on the guide block, and the inner end of the positioning block is inserted into the positioning groove of the guide block.

[0009] Furthermore, the telescopic cylinder is an air cylinder, and the pressure sensor is connected to the electromagnetic valve that controls the air cylinder through a circuit.

[0010] Furthermore, the outer shell is connected to the base mechanism through a mechanical arm.

[0011] Furthermore, the base mechanism includes a base plate and a connecting plate. Two symmetrically distributed connecting plates are installed at the lower end of the base plate. One end of the connecting plate is hinged to the base plate. The connecting plate is provided with a plurality of linearly evenly distributed mounting through holes.

[0012] Furthermore, a groove is provided at the lower end of the positioning block, and a protrusion is provided on the lower end wall of the communicating hole. The protrusion is located in the groove of the positioning block. The inner wall of the positioning block groove and the protrusion are connected by a compression spring, and the compression spring pushes the positioning block into the positioning groove.

[0013] Compared with the prior art, the present invention has the following outstanding beneficial effects:

[0014] 1. The base mechanism of the present invention includes a base plate and a connecting plate. One end of the connecting plate is hinged to the base plate. When in use, the angle and position between the two connecting plates can be flexibly adjusted. Bolts are passed through the through holes of the connecting plate and fixed to the fastener holes on the lower surface of the aircraft wing to fix the present invention to the aircraft wing.

[0015] 2. When using the present invention to cut cracks in an aircraft wing, a wedge is first inserted between the lower wing skin and the wing rear spar to create a gap between the crack in the wing skin and the wing rear spar. When the cutting tool penetrates the wing skin, the elastic protective mechanism can drive the cutting mechanism to contract, thereby preventing the cutting tool from continuing to cut the wing rear spar and causing damage to the wing rear spar. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of the present invention.

[0017] Figure 2 It is a structural schematic diagram of the clamping mechanism of the present invention.

[0018] Figure 3 It is a structural schematic diagram of the elastic protection mechanism of the present invention. DETAILED DESCRIPTION

[0019] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0020] like Figure 1 As shown, the present invention includes an outer shell 1, a cutting tool 3, a clamping mechanism 2 and an elastic protective mechanism 6.

[0021] The outer shell 1 is internally mounted with a clamping mechanism 2 and an elastic protection mechanism 6 . The elastic protection mechanism 6 is connected to the clamping mechanism 2 and can move the clamping mechanism 2 upward. A cutting tool 3 is clamped and installed inside the clamping mechanism 2 .

[0022] like Figure 2 As shown, the clamping mechanism 2 includes a mounting sleeve 202, a tightening ring 201, an arc-shaped clamping plate 204 and a driving rod 203. The mounting sleeve 202 is provided with a cavity with an opening at the lower end, and an external thread is provided on the outer wall of the lower end of the mounting sleeve 202. An annular groove is provided on the inner wall of the mounting sleeve 202. A plurality of guide through holes uniformly distributed in a circular shape are provided on the outer wall of the mounting sleeve 202. The guide through holes are connected to the annular groove. The inner end of the driving rod 203 passes through the guide through holes and is fixedly connected to the outer end of the arc-shaped clamping plate 204. The outer end of the arc-shaped clamping plate 204 is placed in the groove. The outer end of the driving rod 203 is hemispherical and exposed at the outer end of the mounting sleeve 202.

[0023] The outer wall of the tightening ring body 201 is provided with two symmetrically distributed threaded blind holes, and the threaded blind holes of the tightening ring body 201 are threadedly connected to the operating rod 205. When the operating rod 205 is not in use, the operating rod 205 can be removed from the tightening ring body 201.

[0024] The tightening ring 201 is provided with a threaded hole, and the lower end of the threaded hole is provided with a tapered hole. The threaded hole of the tightening ring 201 is matched with the external thread of the mounting sleeve 202, and the outer end of the driving rod 203 is pressed against the inner wall of the tapered hole.

[0025] In the optimized solution, the guide through hole of the mounting sleeve 202 is a stepped through hole, the outer end diameter of the stepped through hole is larger than the inner end diameter, the outer end of the driving rod 203 is connected to the hemispherical contact, and the diameter of the hemispherical contact is larger than the diameter of the driving rod 203, thereby preventing the driving rod 203 from falling off from the guide through hole.

[0026] The cutting tool 3 is mounted in the cavity of the mounting sleeve 202, with the drill bit of the cutting tool 3 exposed at the outer end of the mounting sleeve 202. When the tightening ring 201 is rotated and moved downward, the inner wall of the tapered hole of the tightening ring 201 can squeeze the driving rod 203 inward, so that the arc-shaped clamp can clamp the cutting tool 3.

[0027] In this embodiment, the cutting tool 3 is an electric drill or a pneumatic drill.

[0028] The upper end of the clamping mechanism 2 is sheathed with a guide sleeve 7 and slides with the guide sleeve 7. In this embodiment, the mounting sleeve 202 is mounted inside the guide sleeve 7 and slides with it. A pressure sensor 606 is mounted on the top of the guide sleeve 7 cavity. The opening area of ​​the guide sleeve 7 cavity is smaller than the cross-sectional area of ​​the internal cavity.

[0029] The mounting sleeve 202 has a stepped structure. One end of the mounting sleeve 202 with an opening is a small cylinder, and the other end is a large cylinder. The diameter of the small cylinder is smaller than that of the large cylinder. The cross-sectional area of ​​the small cylinder of the mounting sleeve 202 is smaller than the opening area of ​​the guide sleeve 7 cavity, while the cross-sectional area of ​​the large cylinder is larger than the opening area of ​​the guide sleeve 7 cavity. The large cylinder is mounted inside the guide sleeve 7, and the small cylinder passes through the opening of the guide sleeve 7 and is exposed to the outside. As a result, the mounting sleeve 202 can move up and down within the cavity of the guide sleeve 7 without falling out of the guide sleeve 7.

[0030] The lower end of the outer shell 1 is provided with a guide blind hole, the upper end of the guide sleeve 7 is inserted into the guide blind hole of the outer shell 1 and slides with the guide blind hole. The upper end of the guide sleeve 7 is connected to the top wall of the guide blind hole of the outer shell 1 through a compression spring. A guide block 607 is installed on the outer wall of the guide sleeve 7, and a slide groove is provided on the inner wall of the guide blind hole of the outer shell 1, and the guide block 607 is placed in the slide groove.

[0031] like Figure 3 As shown, the guide sleeve 7 is connected to the elastic protection mechanism 6, and the elastic protection mechanism 6 includes a positioning block 605, a limiting plate 604, a lifting plate 603, a fixing block 602 and a telescopic cylinder 601. A guide groove is provided inside the outer shell 1, and a connecting hole is provided between the guide groove and the slide groove. A limiting plate 604 is installed in the guide groove, and the limiting plate 604 slides in cooperation with the guide groove. A positioning block 605 is installed in the connecting hole, and a positioning groove is provided on the guide block 607. The inner end of the positioning block 605 is inserted into the positioning groove of the guide block 607, and the outer end is pressed against the limiting plate 604.

[0032] In this embodiment, the telescopic cylinder 601 is an air cylinder. Since the inner rod of the air cylinder can be quickly extended or contracted, it can drive the drill bit to contract quickly, minimizing damage to the wing rear beam.

[0033] The limiting plate 604 is provided with a driving groove below the positioning block 605 , the upper end wall of the driving groove is provided with an inclined surface, and the outer end of the positioning block 605 is provided with an inclined surface corresponding to the inclined surface of the driving groove.

[0034] The lower end of the positioning block 605 is provided with a groove, and the lower end wall of the communicating hole is provided with a protrusion, which is located in the groove of the positioning block 605. The inner wall of the groove of the positioning block 605 and the protrusion are connected by a compression spring, which pushes the positioning block 605 into the positioning groove of the guide block 607.

[0035] The upper end of the guide groove of the outer shell 1 is provided with a placement cavity, which is communicated with the guide groove. The upper end of the limit plate 604 passes through the guide groove and is fixedly connected to the lifting plate 603. A corresponding fixed block 602 is provided above the stroke of the lifting plate 603. The fixed block 602 is fixedly installed on the outer wall of the guide sleeve 7. The upper end of the lifting plate 603 is fixedly connected to the telescopic cylinder 601, and the telescopic cylinder 601 is fixedly installed in the placement cavity of the outer shell 1.

[0036] The pressure sensor 606 is connected to the electromagnetic valve of the cylinder through a circuit. The circuit is a prior art and its specific structure is not described in detail. When the pressure of the pressure sensor 606 disappears, the electromagnetic valve can be used to control the cylinder to react quickly.

[0037] In this embodiment, the movement stroke of the mounting sleeve 202 inside the guide sleeve 7 is smaller than the movement stroke of the guide sleeve 7 driven by the telescopic cylinder 601. In the process of lifting the cutting tool 3, the lowering stroke of the cutting tool 3 is prevented from being greater than the lifting stroke, thereby failing to achieve the lifting effect.

[0038] In this embodiment, the outer shell 1 is connected to the base mechanism 5 via a mechanical arm 4. The mechanical arm 4 is a prior art and its specific structure will not be described in detail.

[0039] The base mechanism 5 includes a base plate 501 and a connecting plate 502. Two symmetrically distributed connecting plates 502 are installed at the lower end of the base plate 501. One end of the connecting plate 502 is hinged to the base plate 501. The connecting plate 502 is provided with a plurality of linearly evenly distributed mounting through holes. When in use, bolts can be used to fix the through holes of the connecting plate 502 to the fastener holes on the lower surface of the aircraft wing to fix the base mechanism 5 on the aircraft wing.

[0040] The operating process is as follows: To use the present invention, first insert a wedge-shaped block between the lower wing skin and the wing rear spar to create a gap between the two. Next, place the drill bit of the resection tool 3 against the resection location on the aircraft wing. Press down on the present invention device until the top of the mounting sleeve 202 contacts the pressure sensor 606 at the top of the guide sleeve 7 cavity. This activates the pressure sensor 606, which senses pressure. The resection tool 3 is then activated, causing the drill bit to gradually resect the cracked lower wing skin.

[0041] When the drill bit of the cutting tool 3 penetrates the lower wing skin and enters the gap between the wing skin and the wing rear spar, the force acting on the drill bit disappears. The pressure sensor 606 senses the loss of pressure and activates the telescopic cylinder 601 via the solenoid valve. The telescopic cylinder 601 drives the limit plate 604 to move upward rapidly. During the upward movement of the limit plate 604, the drive groove of the limit plate 604 moves to the position of the positioning plate. The compression spring in the positioning plate groove resets, driving the outer end of the positioning plate to insert into the drive groove of the limit plate 604, causing the positioning plate to leave the positioning groove of the guide block 607 and no longer hinder the movement of the guide sleeve 7. Then, the limit plate 604 continues to move upward. When the lifting plate 603 moves to the position of the fixed block 602, the lifting plate 603 drives the fixed block 602 upward, thereby driving the cutting tool 3 and the clamping mechanism 2 upward, preventing the drill bit of the cutting tool 3 from damaging the wing rear spar.

[0042] During the upward movement of the clamping mechanism 2, the compression spring between the guide sleeve 7 and the guide blind hole of the outer shell 1 is compressed. When the pressure sensor 606 is turned off, the telescopic cylinder 601 is reset. During the reset process, the telescopic cylinder 601 drives the lifting plate 603 and the limit plate 604 downward. The compression spring between the guide sleeve 7 and the guide blind hole of the outer shell 1 is reset, driving the guide sleeve 7 downward and reset. As the limit plate 604 continues to move downward, the inclined surface on the upper end wall of the drive groove squeezes the inclined surface of the outer end of the positioning block 605, causing the positioning block 605 to be reinserted into the positioning groove of the guide block 607.

[0043] It should be noted that the specific embodiments of the present invention have been described in detail. For those skilled in the art, various obvious changes to it without departing from the spirit and scope of the present invention are within the scope of protection of the present invention.

Claims

1. An aircraft wing skin crack removal device, comprising an outer shell (1), a removal tool (3) and a clamping mechanism (2); characterized in that: The outer shell (1) is internally provided with a clamping mechanism (2) and an elastic protection mechanism (6), the elastic protection mechanism (6) is connected to the clamping mechanism (2), and a cutting tool (3) is clamped and installed inside the clamping mechanism (2); the upper end of the clamping mechanism (2) is sleeved with a guide sleeve (7) that slides with it; the lower end of the outer shell (1) is provided with a guide blind hole, the upper end of the guide sleeve (7) is inserted into the guide blind hole of the outer shell (1), and slides with the guide blind hole, and the upper end of the guide sleeve (7) is in contact with the outer shell (1). The top wall of the guide blind hole is connected by a compression spring; the guide sleeve (7) is connected to the elastic protection mechanism (6), the elastic protection mechanism (6) includes a positioning block (605), a limiting plate (604), a lifting plate (603), a fixing block (602) and a telescopic cylinder (601), the outer shell (1) is provided with a guide groove inside, a connecting hole is provided between the guide groove and the slide groove, a limiting plate (604) is installed in the guide groove, the limiting plate (604) is slidably matched with the guide groove, a positioning block (605) is installed in the connecting hole, the positioning The block (605) is elastically slidably matched with the connecting hole, and a positioning groove is provided on the guide sleeve (7). The inner end of the positioning block (605) is inserted into the positioning groove of the guide sleeve (7), and the outer end is pressed against the limiting plate (604); the limiting plate (604) is located below the positioning block (605) and is provided with a driving groove, the upper end wall of the driving groove is provided with an inclined surface, and the outer end of the positioning block (605) is provided with an inclined surface corresponding to the inclined surface of the driving groove; the upper end of the guide groove of the outer shell (1) is provided with a placement cavity, the placement cavity is connected with the guide groove, and the limiting plate (604) is provided with a driving groove. The upper end of the positioning plate (604) passes through the guide groove and is connected to the lifting plate (603). A corresponding fixed block (602) is provided above the travel of the lifting plate (603). The fixed block (602) is mounted on the outer wall of the guide sleeve (7). The upper end of the lifting plate (603) is connected to the telescopic cylinder (601). The telescopic cylinder (601) is mounted in the placement cavity of the outer shell (1). A pressure sensor (606) is installed on the top of the cavity of the guide sleeve (7). The pressure sensor (606) is connected to a control valve that controls the telescopic cylinder through an electric circuit.

2. The aircraft wing skin crack removal device according to claim 1, characterized in that: The clamping mechanism (2) includes a mounting sleeve (202), a tightening ring (201), an arc-shaped clamping plate (204) and a driving rod (203), wherein the mounting sleeve (202) is provided with a cavity with an opening at the lower end, an outer wall of the lower end of the mounting sleeve (202) is provided with an external thread, an inner wall of the mounting sleeve (202) is provided with an annular groove, and a plurality of guide holes evenly distributed in a circumferential shape are provided on the outer wall of the mounting sleeve (202), the guide holes are connected to the annular groove, and the driving rod ( The inner end of the driving rod (203) passes through the guide hole and is connected to the outer end of the arc-shaped clamping plate (204), the outer end of the arc-shaped clamping plate (204) is placed in the groove, and the outer end of the driving rod (203) is exposed at the outer end of the mounting sleeve (202); the tightening ring body (201) is provided with a threaded hole, and the lower end of the threaded hole is provided with a tapered hole, the threaded hole of the tightening ring body (201) is matched with the outer thread of the mounting sleeve (202), and the outer end of the driving rod (203) is pressed against the inner wall of the tapered hole.

3. The aircraft wing skin crack removal device according to claim 2, characterized in that: Two symmetrically distributed threaded blind holes are provided on the outer wall of the tightening ring body (201), and the threaded blind holes of the tightening ring body (201) are threadedly connected to the operating rod (205).

4. The aircraft wing skin crack removal device according to claim 1, characterized in that: A guide block (607) is installed on the outer wall of the guide sleeve (7), a slide groove is provided on the inner wall of the guide blind hole of the outer shell (1), and the guide block (607) is placed in the slide groove; a positioning groove is provided on the guide block (607), and the inner end of the positioning block (605) is inserted into the positioning groove of the guide block (607).

5. The aircraft wing skin crack removal device according to claim 1, characterized in that: The telescopic cylinder (601) is an air cylinder, and the pressure sensor (606) is connected to the electromagnetic valve that controls the air cylinder through a circuit.

6. The aircraft wing skin crack removal device according to claim 1, characterized in that: The outer shell (1) is connected to the base mechanism (5) via a mechanical arm (4).

7. The aircraft wing skin crack removal device according to claim 6, characterized in that: The base mechanism (5) comprises a base plate (501) and a connecting plate (502), wherein two symmetrically distributed connecting plates (502) are mounted on the lower end of the base plate (501), one end of the connecting plate (502) is hinged to the base plate (501), and a plurality of linearly evenly distributed mounting through holes are provided on the connecting plate (502).

8. The aircraft wing skin crack removal device according to claim 1, characterized in that: The lower end of the positioning block (605) is provided with a groove, and the lower end wall of the communicating hole is provided with a protrusion, which is located in the groove of the positioning block (605). The inner wall of the groove of the positioning block (605) and the protrusion are connected by a compression spring, and the compression spring pushes the positioning block (605) into the positioning groove.

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