CN118023046A - Repairing device for aircraft skin and repairing method thereof - Google Patents
Repairing device for aircraft skin and repairing method thereof Download PDFInfo
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- CN118023046A CN118023046A CN202410431469.4A CN202410431469A CN118023046A CN 118023046 A CN118023046 A CN 118023046A CN 202410431469 A CN202410431469 A CN 202410431469A CN 118023046 A CN118023046 A CN 118023046A
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000005498 polishing Methods 0.000 claims abstract description 53
- 238000010438 heat treatment Methods 0.000 claims abstract description 28
- 238000009434 installation Methods 0.000 claims abstract description 20
- 238000001179 sorption measurement Methods 0.000 claims abstract description 15
- 230000008439 repair process Effects 0.000 claims description 62
- 230000007246 mechanism Effects 0.000 claims description 37
- 239000000463 material Substances 0.000 claims description 22
- 239000007921 spray Substances 0.000 claims description 19
- 230000005540 biological transmission Effects 0.000 claims description 9
- 238000005507 spraying Methods 0.000 claims description 5
- 230000033001 locomotion Effects 0.000 abstract description 3
- 230000008569 process Effects 0.000 description 11
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
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Abstract
The invention provides a repairing device and a repairing method for an aircraft skin, and relates to the technical field of aircraft repairing. The prosthetic device includes: the mounting rack is rectangular; the adsorption component is arranged on the mounting frame and is detachably connected with the outer side wall of the aircraft; the sliding rail is arranged on the mounting frame; the movable end of the movable telescopic frame is arranged towards the outer side wall of the airplane and performs telescopic movement towards the outer side wall of the airplane; the installation component is installed on the movable end of the movable telescopic frame; the polishing assembly is arranged on the mounting assembly; the repairing assembly is arranged on the mounting assembly and is arranged in a staggered manner with the polishing assembly; and the heating component is arranged on the movable telescopic frame and positioned on one side of the installation component. According to the aircraft skin repairing device, the aircraft skin is polished and repaired through the repairing device, so that the labor intensity of workers is reduced, and meanwhile, the danger caused by high-altitude operation is reduced.
Description
Technical Field
The invention relates to the technical field of aircraft repair, in particular to a repair device for an aircraft skin and a repair method thereof.
Background
The aircraft skin is a dimensional member which is surrounded outside an aircraft skeleton structure and fixed on the skeleton by using an adhesive or rivets to form the aerodynamic profile of the aircraft, the skin structure formed by the aircraft skin and the skeleton has larger bearing capacity and rigidity, has very light dead weight, plays a role in bearing and transmitting aerodynamic load, transmits acting force to the connected fuselage wing skeleton after bearing aerodynamic force, has complex stress, and is directly contacted with the outside, so that the skin material is required to have high strength and good plasticity, and has smooth surface and higher corrosion resistance.
During the flight process, the outer side wall of the aircraft can rub against dust in the air, so that cracks or pits appear on the skin of the aircraft, and therefore, the outer side wall of the aircraft needs to be inspected after the aircraft flies for a certain time. If cracks or pits appear on the outer side wall, the existing repairing mode is to fix the outer side wall at the place where the fine cracks appear by adopting a new skin through riveting, and the repairing mode is not suitable for repairing deeper cracks.
Disclosure of Invention
The invention aims to solve the technical problems, and provides the repairing device for the aircraft skin, which is characterized in that after the repairing device is lifted to a preset height by lifting equipment, a repairing part on the repairing device is aligned with an area to be repaired of an aircraft, then the repairing device is fixed on the outer side wall of the aircraft by an adsorption assembly, the area to be repaired is repaired by the repairing part, and the labor intensity of workers is effectively reduced by adopting automatic operation. The invention also provides a repairing method of the aircraft skin.
The technical scheme adopted by the invention is as follows:
A repair device for an aircraft skin, comprising:
the mounting rack is rectangular;
The adsorption assembly is arranged on the mounting frame and is detachably connected with the outer side wall of the aircraft;
The sliding rail is arranged on the mounting frame;
the movable telescopic frame is arranged on the sliding rail, and the movable end of the movable telescopic frame faces the outer side wall of the airplane;
The installation component is installed on the movable end of the movable telescopic frame;
The polishing assembly is arranged on the mounting assembly and used for polishing the outer side wall of the airplane;
the repairing assembly is arranged on the mounting assembly and is arranged in a staggered manner with the polishing assembly; and
And the heating component is arranged on the movable telescopic frame and positioned on one side of the installation component, and is used for heating the repair area.
Optionally, the adsorption assembly comprises:
the fixed end of the telescopic supporting leg is connected with the mounting frame, and the movable end of the telescopic supporting leg faces the outer side wall of the aircraft;
the sucker is arranged at the end part of the movable end of the supporting leg;
and the vacuum pump is arranged on the supporting leg and is communicated with the sucker through a pipeline.
Optionally, the sliding rail includes:
The two guide rail beams are arranged along the length direction of the mounting frame, and a mounting area is formed between the two guide rail beams;
The guide rail beams are respectively provided with a guide screw, and the movable telescopic frame is slidably arranged on the guide screws;
The driving mechanism is connected with the screw rod through a transmission assembly.
Optionally, the movable telescopic frame includes:
The two ends of the sliding rod are respectively provided with a screw nut, and the screw nuts are matched with the two screw rods;
The mounting disc is slidably mounted on the sliding rod;
The two telescopic pieces are arranged on the mounting plate, the movable ends of the telescopic pieces are arranged away from the mounting plate, and the mounting assembly is arranged between the two telescopic pieces and is positioned at the end parts of the movable ends of the telescopic pieces;
and the two ends of the driving mechanism are respectively matched with the two screw rods, and the movable part of the driving mechanism is connected with the mounting plate to drive the mounting plate to move along the axial direction of the sliding rod.
Optionally, the mounting assembly comprises:
The two mounting seats are respectively arranged at the ends of the movable ends of the two movable telescopic frames;
The installation piece is rotatably installed between the two installation seats, the polishing assembly and the repairing assembly are installed on the installation piece, and the polishing assembly and the repairing assembly are arranged in a back-to-back manner after being installed;
and the rotating motor is arranged on one of the mounting seats, and the power output end of the rotating motor is connected with the mounting piece.
Optionally, the polishing assembly comprises:
the angle adjusting motor is arranged on the mounting frame, and the axis of the power output shaft of the angle adjusting motor is parallel to the axis of the power output shaft of the rotating motor;
The fixed seat is arranged on the output shaft of the angle adjusting motor;
the polishing motor is arranged on the fixing seat, and the axis of an output shaft of the polishing motor is perpendicular to the axis of an output shaft of the angle adjusting motor;
and the polishing head is detachably arranged at the end part of the output shaft of the polishing motor.
Optionally, the repair assembly includes:
a rotating frame mounted on the mounting member;
The fine tuning motor is arranged on the mounting frame, and the axis of an output shaft of the fine tuning motor is parallel to the axis of an output shaft of the rotating motor;
The spray head is arranged on the rotating shaft of the rotating frame, and the output end of the fine adjustment motor is connected with the rotating shaft of the rotating frame;
And the feeding assembly is communicated with the spray head through a conveying pipeline.
Optionally, the feed assembly comprises:
A supply tank in which a repair material is stored;
the conveying pump is arranged in the feeding box, and the conveying pipeline is communicated with a discharge hole of the conveying pump;
The filter screen is arranged at the feed inlet of the conveying pump.
Optionally, the heating assembly includes:
the adjusting rod is arranged on the movable telescopic frame, and the movable end of the adjusting rod is arranged towards one end of the outer side wall of the airplane;
the mounting plate is mounted at the movable end part of the adjusting rod;
and the heating plate is installed on the mounting plate and is arranged towards the outer side wall of the airplane after being installed.
The device is used for fixed-point repair of the outer side wall of the aircraft, automatic operation is performed in the repair process, labor intensity of workers is reduced, and adjustment is convenient according to the curve of the outer side wall of the aircraft, so that different parts of the aircraft can be repaired conveniently. In order to facilitate the understanding of users, the invention also provides a method for repairing the aircraft skin. The method specifically comprises the following steps:
step S01, lifting the repairing device to a set height through lifting equipment, and attaching the repairing device to the outer side wall of the aircraft; step S02, adjusting the position of the movable telescopic frame to enable a heating assembly arranged on the movable telescopic frame to heat the area to be repaired;
step S03, adjusting the polishing assembly to enable the polishing assembly to face the outer side wall of the airplane, polishing the area to be repaired, and obtaining a repaired area after polishing;
step S04, adjusting the repair assembly to enable the spray head of the repair assembly to face the repair area, and spraying repair materials to the repair area to finish repairing the repair area.
Compared with the prior art, the invention has the beneficial effects that:
1. After lifting the repairing device to a preset height through lifting equipment, aligning the repairing part on the repairing device with the area to be repaired of the aircraft, fixing the repairing device on the outer side wall of the aircraft through the adsorption assembly, repairing the area to be repaired by the repairing part, and effectively reducing the labor intensity of workers by adopting automatic operation.
2. In the repairing process, in order to conveniently adjust the position of the repairing part, a sliding rail is arranged on the mounting frame, the movable telescopic frame slides on the sliding rail to adjust the position of the repairing part mounted on the movable telescopic frame, and the repairing part is convenient to carry out fine adjustment during repairing.
Drawings
In order to more clearly illustrate the embodiments of the application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic overall structure of a prosthetic device for an aircraft skin.
Fig. 2 is a schematic structural view of a repair device for an aircraft skin.
FIG. 3 is a schematic view of a partial structure of a prosthetic device for an aircraft skin.
Fig. 4 is a partial structural schematic view of the state of use of the repair device for the aircraft skin.
Reference numerals:
1. A mounting frame;
2. an adsorption assembly; 21. supporting feet; 22. a suction cup; 23. a vacuum pump;
3. a slide rail; 31. a guide rail beam; 32. a screw rod; 33. a driving mechanism;
4. moving the telescopic frame; 41. a slide bar; 42. a nut; 43. a mounting plate; 44. a telescoping member; 45. a screw rod mechanism;
5. a mounting assembly; 51. a mounting base; 52. a mounting member; 53. a rotating motor;
6. a polishing assembly; 61. an angle adjusting motor; 62. a fixing seat; 63. polishing a motor; 64. polishing head;
7. Repairing the component; 71. a rotating frame; 72. a fine tuning motor; 73. a spray head; 74. a feed assembly; 741. a feed box; 742. a transfer pump; 743. a filter screen;
8. a heating assembly; 81. an adjusting rod; 82. a mounting plate; 83. and (5) heating the plate.
Detailed Description
Hereinafter, only certain exemplary embodiments are briefly described. As will be recognized by those of skill in the pertinent art, the described embodiments may be modified in various different ways without departing from the spirit or scope of the present invention. Accordingly, the drawings and description are to be regarded as illustrative in nature and not as restrictive.
In the description of the present invention, it should be understood that the terms "length," "upper," "inner," "outer," "axial," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or orientations or positional relationships conventionally put in use of the product of the present invention, or orientations or positional relationships conventionally understood by those skilled in the art, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; the device can be mechanically connected, electrically connected and communicated; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is less level than the second feature.
The following disclosure provides many different embodiments, or examples, for implementing different features of the invention. In order to simplify the present disclosure, components and arrangements of specific examples are described below. They are, of course, merely examples and are not intended to limit the invention. Furthermore, the present invention may repeat reference numerals and/or letters in the various examples, which are for the purpose of brevity and clarity, and which do not themselves indicate the relationship between the various embodiments and/or arrangements discussed. In addition, the present invention provides examples of various specific processes and materials, but one of ordinary skill in the art will recognize the application of other processes and/or the use of other materials.
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
As shown in fig. 1 and 4, an embodiment of the present invention provides a repair device for an aircraft skin, including: the device comprises a mounting frame 1, an adsorption component 2, a sliding rail 3, a movable telescopic frame 4, a mounting component 5, a polishing component 6, a repairing component 7 and a heating component 8 which are arranged in a rectangular mode. The adsorption component 2 is installed on the installation frame 1, and the adsorption end of the adsorption component 2 is arranged towards the outer side wall of the airplane, so that the adsorption component 2 is conveniently fixed on the outer side wall of the airplane. The slide rail 3 is installed on the mounting frame 1, and the movable telescopic frame 4 is installed on the slide rail 3, and can move along the track direction of the slide rail 3 after being installed. The mounting assembly 5 is mounted on the movable end of the mobile telescopic frame 4. The polishing component 6 and the repairing component 7 are both installed on the installation component 5, and are arranged in a back-to-back manner after the polishing component 6 and the repairing component 7 are installed. The heating component 8 is arranged on the movable expansion bracket 4 and is positioned on one side of the installation component 5, so that the area needing to be repaired can be heated conveniently.
In use, the mounting frame 1 is lifted by a truss or other lifting device so that the area to be repaired is located within the mounting frame 1. The adsorption component 2 arranged on one side of the mounting frame 1 adsorbs on the outer side wall of the aircraft, and after the mounting frame 1 is fixed on the outer side wall of the aircraft, the position of the movable telescopic frame 4 is adjusted so that the mounting component 5 mounted on the movable telescopic frame 4 is aligned with the area needing to be repaired. The sanding assembly 6 or the repair assembly 7 is then moved towards one end of the outer sidewall of the aircraft by moving the telescopic frame 4. Repair of the repaired area is accomplished by the sanding assembly 6 and the repair assembly 7.
After the polishing component 6 polishes the area to be repaired, the heating component 8 heats the area to raise the temperature of the area to be repaired, lower the temperature of the area to be repaired and the adjacent surface thereof, and enable the material sprayed by the repairing component 7 to be better fused on the polished outer surface when contacting with the material.
It should be noted that the positions of the grinding assembly 6 and the repairing assembly 7 are adjusted by the mounting assembly 5 during the repairing process. More specifically, when it is desired to polish the repair area, the mounting assembly 5 is rotated such that the polishing assembly 6 is directed toward the outboard wall of the aircraft. After finishing polishing, the position of the movable telescopic frame 4 is adjusted, so that the heating assembly 8 is aligned with the polished area, and the heating assembly 8 carries out heating treatment on the area. After the temperature of the polished area reaches a preset value, the position of the movable telescopic frame 4 is adjusted, and meanwhile the installation component 5 arranged on the movable telescopic frame 4 moves, so that the repair component 7 faces the outer side wall of the aircraft, and the repair component 7 sprays powder to repair the polished area.
If the surface has obvious uneven problem after repairing, the surface can be polished by the polishing component 6 to be even more flat.
In one embodiment, as shown in fig. 1 and 2, the adsorption assembly 2 includes: a telescopic supporting leg 21, a sucker 22 and a vacuum pump 23. The fixed end of the supporting leg 21 is fixedly arranged on one side wall of the mounting frame 1, and the movable end of the supporting leg 21 is arranged towards the outer side wall of the airplane. The suction cup 22 is provided at the movable end portion of the support leg 21. The vacuum pump 23 is mounted on the support leg 21 and communicates with the suction cup 22 to facilitate the fixing of the mounting frame 1 to the outer side wall of the aircraft.
When the aircraft is used, the area to be repaired is aligned in the rectangular mounting frame 1, and then the extending distance of each supporting leg 21 is adjusted according to the radian of the curved surface of the outer side wall of the aircraft, so that the sucker 22 is in contact with the outer side wall of the aircraft. The vacuum pump 23 is operated after the suction cup 22 is in contact with the outer sidewall so that a vacuum area is formed between the suction cup 22 and the outer sidewall of the aircraft. The mounting 1 is now firmly secured to the outer side wall of the aircraft by means of the suction cups 22.
In one embodiment, as shown in fig. 1 and 2, the sliding rail 3 includes: two guide rail beams 31, a screw 32 and a driving mechanism 33. The two guide rail beams 31 are arranged along the length direction of the mounting frame 1, and a mounting area is formed between the two guide rail beams 31. The two guide rail beams 31 are provided with mounting notches on opposite side walls thereof, the screw rods 32 are mounted in the mounting notches, and the movable expansion bracket 4 is mounted between the two screw rods 32. The driving mechanism 33 is installed at one end of the guide rail, and the power output end of the driving mechanism 33 is connected with the screw rod 32 through a transmission assembly.
When the position of the movable telescopic frame 4 needs to be adjusted, the driving mechanism 33 moves to drive the screw rod 32 to rotate, so that the movable telescopic frame 4 mounted on the screw rod 32 moves along the direction of the screw rod 32.
The driving mechanism 33 in the present embodiment is a driving motor. The drive assembly is of an existing design and can be understood as a reversing structure in the existing design.
In one embodiment, as shown in fig. 1, 2 and 3, the movable telescopic frame 4 includes: a slide bar 41, a mounting plate 43, two telescopic members 44 and a driving mechanism. Both ends of the slide bar 41 are respectively connected with the screw 32 through the screw 32, so that the slide bar 41 can move along the axial direction of the screw 32 under the drive of the driving mechanism 33. The mounting plate 43 is slidably mounted on the slide bar 41. The two telescopic members 44 are mounted on the mounting plate 43, the movable ends of the telescopic members 44 are arranged towards the outer side wall of the aircraft, and the mounting assembly 5 is mounted at the movable end parts of the two telescopic members 44. The two ends of the driving mechanism are respectively matched with the two screw rods 32, and the output end of the driving mechanism is connected with the mounting plate 43 to drive the mounting plate 43 to move along the axial direction of the sliding rod 41.
In use, the slide bar 41 is connected to the screw 32 by a nut 42, the nut 42 moving along the axis of the screw 32 as the screw 32 is rotated. The nut 42 moves with the slide bar 41 connected thereto during the movement, and the mounting plate 43 mounted on the slide bar 41 also moves with the nut 42, and the driving mechanism 33 stops working after the mounting plate 43 moves to a designated area. The telescopic members 44 mounted on the mounting plate 43 are then extended and retracted, bringing the mounting assembly 5 mounted on the telescopic members 44 closer to or farther from the outer side wall of the aircraft.
In use, since the mounting plate 43 is slidably disposed on the sliding rod 41, the driving mechanism is a screw mechanism 45 or other mechanism capable of achieving reciprocating motion for conveniently driving the mounting plate 43 to move along the axial direction of the sliding rod 41. When the drive mechanism is a screw mechanism 45, the drive mechanism includes: the device comprises a transmission screw rod, a moving block and a motor. The two ends of the transmission screw rod are provided with transmission blocks which are matched with the screw rod 32 of the sliding rail 3. The moving block is matched with the transmission screw rod, and the mounting plate 43 is fixedly arranged on the moving block. When the motor drives the transmission screw to rotate, the moving block moves along the axial direction of the transmission screw, and drives the mounting plate 43 mounted on the moving block to move.
In one embodiment, as shown in fig. 3, the mounting assembly 5 includes: two mounting seats 51, a mounting piece 52 and a rotating motor 53. Two mounting seats 51 are mounted on the free end portions of the two telescoping members 44, respectively. The mounting piece 52 is rotatably arranged between the two mounting seats 51, the polishing assembly 6 and the repairing assembly 7 are arranged on the mounting frame 1, and the polishing assembly 6 and the repairing assembly 7 are arranged in a back-to-back manner after being arranged. The rotating motor 53 is installed on one of the installation seats 51, the power output end of the rotating motor 53 is connected with the installation piece 52, and the rotating motor 53 rotates to drive the installation piece 52 to rotate, so that the polishing assembly 6 and the repairing assembly 7 are turned over.
In use, the motor 53 is rotated according to the process requirements to rotate the mounting member 52 between the mounting seats 51 such that the sanding assembly 6 or the repair assembly 7 mounted on the mounting member 52 is disposed toward the outer sidewall of the aircraft. The grinding assembly 6 and the repairing assembly 7 are effectively prevented from being disturbed in the use process.
In one embodiment, as shown in fig. 3, the sharpening assembly 6 comprises: an angle adjusting motor 61, a fixing base 62, a polishing motor 63 and a polishing head 64. The angle adjusting motor 61 is mounted on the mounting frame 1. The fixed seat 62 is mounted on the output shaft of the angle adjusting motor 61. The grinding motor 63 is mounted on the fixing base 62, and the axis of the output shaft of the grinding motor 63 is perpendicular to the axis of the output shaft of the angle adjusting motor 61. The sanding head 64 is mounted at an end of an output shaft of the sanding motor 63.
When polishing, the driving mechanism 33 drives the screw rod 32 to rotate, and the screw rod 32 drives the screw nut 42 and the movable telescopic frame 4 connected with the screw nut 42 to move along the axial direction of the screw rod 32 in the rotating process. The mounting bracket 1 on the movable expansion bracket 4 slides on the slide bar 41 under the drive of the screw mechanism 45. The angle and the position of the polishing head 64 are adjusted by matching with the angle adjusting motor 61 in the sliding process, so that the polishing head 64 can conveniently polish the side walls with different angles and positions.
In one embodiment, as shown in fig. 1 and 3, the repair assembly 7 includes: a turret 71, a fine motor 72, a spray head 73, and a feed assembly 74. The turret 71 is mounted on the mounting frame 1. The fine adjustment motor 72 is mounted on the mounting frame 1, and the axis of the output shaft of the fine adjustment motor 72 and the axis of the output shaft of the rotation motor 53 are parallel to each other. The shower nozzle 73 is installed on the axis of rotation of rotating turret 71, and the output of fine setting motor 72 is connected with the axis of rotation of rotating turret 71, and shower nozzle 73 rotates under the drive of fine setting motor 72, carries out the spraying to the lateral wall of aircraft and restores. The feeding component 74 is communicated with the spray head 73 through a conveying pipeline, and the feeding component 74 can provide materials for the spray head 73 during repairing.
When the material is sprayed and repaired, the fine adjustment motor 72 drives the spray head 73 to rotate, the spray head 73 sprays repair materials in the area to be repaired in the rotating process, and the drive mechanism 33 and the screw rod mechanism 45 cooperate to drive the spray head 73 to carry out position adjustment in the area to be repaired until the area to be repaired is repaired.
More specifically, as shown in fig. 1 and 3, for convenience in providing the repair material to the shower head 73, the supply assembly 74 includes: a feed tank 741, a transfer pump 742 and a filter screen 743. The supply tank 741 stores a repair material therein. A delivery pump 742 is provided in the feed tank 741, and a discharge port of the delivery pump 742 communicates with a delivery pipe through which the repair material is supplied to the shower head 73. The filter screen 743 is disposed at the feed inlet of the transfer pump 742, which facilitates the filtration of the repairing material entering the transfer pump 742, and prevents the nozzle 73 from being blocked after the agglomerated material enters.
In one embodiment, as shown in fig. 2 and 3, the heating assembly 8 includes: an adjusting lever 81, a mounting plate 82 and a heating plate 83. The adjusting lever 81 is mounted on the movable telescopic frame 4 with its movable end disposed toward one end of the outer sidewall of the aircraft. The mounting panel 82 is installed at the loose end tip of adjusting the pole 81, and the hot plate 83 is installed on the mounting panel 82, and the hot plate 83 sets up towards the lateral wall of aircraft after the installation, makes things convenient for the hot plate 83 to carry out heat treatment to the lateral wall of aircraft.
When the aircraft skin heat transfer device is used, the driving motor and the screw rod mechanism 45 drive the heating plate 83 to perform position adjustment, the adjusting rod 81 moves after the adjustment is in place, the heating plate 83 is driven to move towards the outer side wall of the aircraft, the heating plate 83 is tightly attached to the outer side wall of the aircraft, and the heating plate 83 transfers heat to the aircraft skin after the attachment.
The device is used for fixed-point repair of the outer side wall of the aircraft, automatic operation is performed in the repair process, labor intensity of workers is reduced, and adjustment is convenient according to the curve of the outer side wall of the aircraft, so that repair of different parts of the aircraft is facilitated. In order to facilitate the understanding of users, the invention also provides a method for repairing the aircraft skin. The method specifically comprises the following steps:
Step S01, lifting the repairing device to a set height through lifting equipment, and attaching the repairing device to the outer side wall of the aircraft; step S02, adjusting the position of the movable telescopic frame 4 so that a heating component 8 arranged on the movable telescopic frame 4 heats the area to be repaired;
Step S03, adjusting the polishing assembly 6 to enable the polishing assembly 6 to face the outer side wall of the airplane, polishing the area to be repaired, and obtaining a repaired area after polishing;
Step S04, adjusting the repair assembly 7 so that the spray head 73 of the repair assembly 7 faces the repair area, and spraying repair material to the repair area to complete repair of the repair area.
In repairing the skin of an aircraft, the mounting frame 1 is first lifted by means of trusses or external lifting devices arranged in the factory. After lifting, the mounting frame 1 is fixed on the outer side wall of the aircraft through a sucker 22 arranged on one side of the mounting frame 1. The area to be repaired is now located in the mounting frame 1, and the sanding assembly 6 mounted on the mounting member 52 is adjusted in position under the drive of the rotary motor 53 such that the sanding head 64 of the sanding assembly 6 faces the outer side wall of the aircraft. The polishing of the repair area is then achieved by the cooperation of the drive mechanism 33, the screw mechanism 45 and the angle adjustment motor 61. After finishing the polishing, the heating assembly 8 heats the polished area through the cooperation of the driving mechanism 33 and the screw rod mechanism 45.
After the area needing to be repaired is heated, the rotating motor 53 moves to enable the mounting piece 52 to rotate, the repairing assembly 7 mounted on the mounting piece 52 is turned over to one end towards the outer side wall of the aircraft, then the spray head 73 is driven to move in the mounting frame 1 through the cooperation of the driving mechanism 33 and the screw rod mechanism 45, and the spray hole angle of the spray head 73 is adjusted according to the outer side wall curve of the aircraft in the moving process, so that the sprayed repairing material can be better adhered in the repairing area of the aircraft.
Because the repair material is a powder material, the repair material can be adhered to the outer side wall of the aircraft rapidly by high-speed high-temperature spraying, and the sprayed outer surface is relatively smooth.
The telescoping member 44 may cooperate with the drive mechanism 33, the screw mechanism 45 to adjust the position of the sanding head 64 and the nozzle 73 and its distance from the outboard wall of the aircraft during sanding or repair.
Finally, it should be noted that: the foregoing description is only a preferred embodiment of the present invention, and the present invention is not limited thereto, but it is to be understood that modifications and equivalents of some of the technical features described in the foregoing embodiments may be made by those skilled in the art, although the present invention has been described in detail with reference to the foregoing embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A prosthetic device for an aircraft skin, comprising:
the mounting rack is rectangular;
The adsorption assembly is arranged on the mounting frame and is detachably connected with the outer side wall of the aircraft;
The sliding rail is arranged on the mounting frame;
the movable telescopic frame is arranged on the sliding rail, and the movable end of the movable telescopic frame faces the outer side wall of the airplane;
The installation component is installed on the movable end of the movable telescopic frame;
The polishing assembly is arranged on the mounting assembly and used for polishing the outer side wall of the airplane;
the repairing assembly is arranged on the mounting assembly and is arranged in a staggered manner with the polishing assembly; and
And the heating component is arranged on the movable telescopic frame and positioned on one side of the installation component, and is used for heating the repair area.
2. The repair device for an aircraft skin according to claim 1, wherein the adsorption assembly comprises:
the fixed end of the telescopic supporting leg is connected with the mounting frame, and the movable end of the telescopic supporting leg faces the outer side wall of the aircraft;
the sucker is arranged at the end part of the movable end of the supporting leg;
and the vacuum pump is arranged on the supporting leg and is communicated with the sucker through a pipeline.
3. The repair device for an aircraft skin according to claim 1, wherein the slide rail comprises:
The two guide rail beams are arranged along the length direction of the mounting frame, and a mounting area is formed between the two guide rail beams;
The guide rail beams are respectively provided with a guide screw, and the movable telescopic frame is slidably arranged on the guide screws;
The driving mechanism is connected with the screw rod through a transmission assembly.
4. A repair device for an aircraft skin according to claim 3, wherein the mobile telescopic frame comprises:
The two ends of the sliding rod are respectively provided with a screw nut, and the screw nuts are matched with the two screw rods;
The mounting disc is slidably mounted on the sliding rod;
The two telescopic pieces are arranged on the mounting plate, the movable ends of the telescopic pieces are arranged away from the mounting plate, and the mounting assembly is arranged between the two telescopic pieces and is positioned at the end parts of the movable ends of the telescopic pieces;
and the two ends of the driving mechanism are respectively matched with the two screw rods, and the output end of the driving mechanism is connected with the mounting disc to drive the mounting disc to move along the axial direction of the sliding rod.
5. The repair device for an aircraft skin according to claim 1 or 4, wherein the mounting assembly comprises:
The two mounting seats are respectively arranged at the ends of the movable ends of the two movable telescopic frames;
The installation piece is rotatably installed between the two installation seats, the polishing assembly and the repairing assembly are installed on the installation piece, and the polishing assembly and the repairing assembly are arranged in a back-to-back manner after being installed;
and the rotating motor is arranged on one of the mounting seats, and the power output end of the rotating motor is connected with the mounting piece.
6. The aircraft skin repair device of claim 5, wherein said sanding assembly comprises:
the angle adjusting motor is arranged on the mounting frame, and the axis of the power output shaft of the angle adjusting motor is parallel to the axis of the power output shaft of the rotating motor;
The fixed seat is arranged on the output shaft of the angle adjusting motor;
the polishing motor is arranged on the fixing seat, and the axis of an output shaft of the polishing motor is perpendicular to the axis of an output shaft of the angle adjusting motor;
and the polishing head is detachably arranged at the end part of the output shaft of the polishing motor.
7. The repair device for an aircraft skin according to claim 5, wherein said repair assembly comprises:
a rotating frame mounted on the mounting member;
The fine tuning motor is arranged on the mounting frame, and the axis of an output shaft of the fine tuning motor is parallel to the axis of an output shaft of the rotating motor;
The spray head is arranged on the rotating shaft of the rotating frame, and the output end of the fine adjustment motor is connected with the rotating shaft of the rotating frame;
And the feeding assembly is communicated with the spray head through a conveying pipeline.
8. The repair device for an aircraft skin according to claim 7, wherein said feed assembly comprises:
A supply tank in which a repair material is stored;
the conveying pump is arranged in the feeding box, and the conveying pipeline is communicated with a discharge hole of the conveying pump;
The filter screen is arranged at the feed inlet of the conveying pump.
9. The repair device for an aircraft skin according to claim 1, wherein the heating assembly comprises:
the adjusting rod is arranged on the movable telescopic frame, and the movable end of the adjusting rod is arranged towards one end of the outer side wall of the airplane;
the mounting plate is mounted at the movable end part of the adjusting rod;
and the heating plate is installed on the mounting plate and is arranged towards the outer side wall of the airplane after being installed.
10. The method for repairing the aircraft skin is characterized by comprising the following steps of:
Step S01, lifting the repairing device in any one of claims 1-9 to a set height through lifting equipment, and attaching the repairing device to the outer side wall of the aircraft;
step S02, adjusting the position of the movable telescopic frame to enable a heating assembly arranged on the movable telescopic frame to heat the area to be repaired;
step S03, adjusting the polishing assembly to enable the polishing assembly to face the outer side wall of the airplane, polishing the area to be repaired, and obtaining a repaired area after polishing;
step S04, adjusting the repair assembly to enable the spray head of the repair assembly to face the repair area, and spraying repair materials to the repair area to finish repairing the repair area.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410431469.4A CN118023046A (en) | 2024-04-11 | 2024-04-11 | Repairing device for aircraft skin and repairing method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410431469.4A CN118023046A (en) | 2024-04-11 | 2024-04-11 | Repairing device for aircraft skin and repairing method thereof |
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| CN118023046A true CN118023046A (en) | 2024-05-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202410431469.4A Pending CN118023046A (en) | 2024-04-11 | 2024-04-11 | Repairing device for aircraft skin and repairing method thereof |
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| CN (1) | CN118023046A (en) |
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