CN115871955B - Method for repairing front edge skin of airplane wing and tail wing - Google Patents
Method for repairing front edge skin of airplane wing and tail wing Download PDFInfo
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- CN115871955B CN115871955B CN202310143410.0A CN202310143410A CN115871955B CN 115871955 B CN115871955 B CN 115871955B CN 202310143410 A CN202310143410 A CN 202310143410A CN 115871955 B CN115871955 B CN 115871955B
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Abstract
The invention relates to a method for repairing the front edge skin of an airplane wing and an empennage, which comprises the following steps of S1, performing 3D modeling according to the size of a damaged skin to obtain a 3D model of a die; s2, importing the 3D model into 3D printing software, and obtaining a die through 3D printing, wherein two side surfaces and a top cambered surface of the die form a forming surface, and the bottom surface of the die is a horizontal supporting surface; s3, supporting a supporting surface of the die by a support, horizontally placing the skin sheet on the top of the die, compacting and fixing the skin sheet on the top of the die by using a first roller and a second roller, respectively moving the first roller and the second roller downwards along two side surfaces of the die, and press-bending the skin sheet to be attached to the molding surface to obtain a new skin; and S4, installing the new skin at the damaged position. The invention can quickly repair the skin without a large machine tool, and is suitable for various machine types.
Description
Technical Field
The invention belongs to the technical field of aircraft maintenance, and particularly relates to a method for repairing a front edge skin of an aircraft wing and an empennage.
Background
The front edges of the wings and the tail wings of the aircraft are used as windward surfaces and mainly bear pneumatic loads parallel to the aircraft, and threatens to the front edges mainly come from the flying direction, and are mainly bird-strike, air-drift strike, ground scratch and the like at ordinary times. Because the aircraft is fast, even the very small object can cause serious damage to it, light then skin is sunken, and heavy then punctures the skin.
The surfaces of the front edge skins of the wings and the tail wings have good pneumatic smoothness, so that the damaged areas are repaired by adopting inlaid repair or internal repair, the repair patch is completely attached to the skins, and the gaps at the attached positions have strict size requirements. The existing repairing modes include the following steps:
1. and (3) adopting integral replacement, namely using a manufacturing die of the front edge skin, and gate-pressing to form a new skin on a large machine tool to replace the old skin. However, this repair must be performed at the original manufacturer, which is time consuming and difficult to implement by the maintenance department of the aircraft.
2. Repairing personnel repair by adopting a manual polishing mode, namely, manually roughly forming the patch according to the shape of the skin, and then continuously comparing the formed patches to repair and polish the patch until the patches can be completely attached. The repair mode is a very skilled aircraft repair mode, the aircraft repair personnel can finish the manufacture and repair of the skin only by taking 2.5 hours on average, the repair mode has high requirements on the capability of the repair personnel, once the repair personnel make errors in the skin polishing process, the skin manufacture failure can be caused, and the efficiency and the reliability are lower from beginning to end.
3. The mould is manufactured by adopting a machining mode, then the mould is used for manufacturing the skin, and as the radius of the front edge skin gradually decreases from the wing root to the wing tip, the corresponding mould also has a certain taper, and a proper mould is difficult to manufacture by a traditional numerical control machine tool.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for repairing the front edge skin of an airplane wing and an empennage, which can quickly repair the skin without a large machine tool and is suitable for various types of aircraft.
In order to solve the problems, the invention adopts the following technical scheme: the method for repairing the front edge skin of the wings and the tail wings of the aircraft comprises the following steps of
S1, performing 3D modeling according to the damaged skin size to obtain a 3D model of the die;
s2, importing the 3D model into 3D printing software, and obtaining a die through 3D printing, wherein two side surfaces and a top cambered surface of the die form a forming surface, and the bottom surface of the die is a horizontal supporting surface;
s3, supporting a supporting surface of the die by a support, horizontally placing the skin sheet on the top of the die, compacting and fixing the skin sheet on the top of the die by using a first roller and a second roller, respectively moving the first roller and the second roller downwards along two side surfaces of the die, and press-bending the skin sheet to be attached to the molding surface to obtain a new skin;
and S4, installing the new skin at the damaged position.
Further, the step S1 specifically includes:
s11, placing the large end of the skin segment on a horizontal table top;
s12, placing a rotary platform on a horizontal table top, enabling an opening of the skin segment to face the rotary platform, placing an infrared range finder on the table top, and enabling an infrared emission end of the infrared range finder to face the inner side face of the skin segment;
s13, utilizing a rotating platform to drive an infrared distance meter to rotate at a constant speed, and measuring and recording the distance of the infrared distance meter at intervals to obtain a plurality of distance data;
s14, fitting the measured distance data to obtain a smooth curve of the inner side surface of the skin segment;
s15, determining the section size of the die, and lofting the smooth curve according to the taper of the wing or the tail wing of the airplane to obtain a 3D model of the die.
Further, in step S2, a polylactic acid printing mold is used.
Further, the mold is a hollow mold.
Further, the support is a jacking mechanism, the lengths of the first roller and the second roller are larger than those of the die, the first roller and the second roller are respectively connected with a first inclined hydraulic rod and a second inclined hydraulic rod, and the upper ends of the first hydraulic rod and the second hydraulic rod are connected to the frame;
in step S3, the first hydraulic rod and the second hydraulic rod apply thrust to the first roller and the second roller respectively, the jacking mechanism pushes the mold to move upwards, the skin plate is driven to move upwards, the first hydraulic rod and the second hydraulic rod shrink gradually, the first roller and the second roller move downwards relative to two sides of the mold, and the skin plate is pressed and bent to two sides of the bonding mold under the thrust action of the first roller and the second roller.
Further, two first hydraulic rods are arranged at two ends of the first roller, and a first telescopic supporting rod is arranged between each first hydraulic rod and the frame; the two second hydraulic rods are arranged at two ends of the second roller, and a second telescopic supporting rod is arranged between each second hydraulic rod and the frame;
in step S3, the lengths of the two first telescopic supporting rods are adjusted to adjust the inclination of the first roller, and the lengths of the two second telescopic supporting rods are adjusted to adjust the inclination of the second roller.
Further, the lifting mechanism is a jack.
Further, the frame includes the base and sets up the mount at the base both ends, every be provided with the crane on the mount, link to each other through the crossbeam between two crane tops, the upper end of first hydraulic stem and second hydraulic stem articulates in the crane, the upper end of first flexible bracing piece and second flexible bracing piece articulates in the crossbeam.
Further, a graduated scale is arranged on the fixing frame;
further, a height sensor is arranged on the lifting mechanism.
The beneficial effects of the invention are as follows: 1. according to the invention, the 3D printing equipment is adopted to prepare the new die, the skin can be molded by adopting simple roll molding equipment, large-scale machining equipment and molding equipment are not needed, and the implementation cost is low.
2. By means of advanced 3D printing technology, a mould which completely accords with the sizes of the front edge skins of the aircraft wings and the tail wings is manufactured, and full-automatic mechanical manufacturing of the front edge skins of the aircraft wings is realized. The maintenance department can repair the skin on site without returning to a factory, so that the repair efficiency is improved, and the skin can be immediately put into use after repair.
3. The invention is suitable for various types of machines, such as fighter or civil aircraft with the third generation below half, and has wide application range.
Drawings
FIG. 1 is a schematic illustration of a skin segment;
FIG. 2 is a schematic top view of skin segment ranging;
FIG. 3 is a schematic view of a mold;
FIG. 4 is a schematic rolling diagram;
FIG. 5 is a schematic view of a rolling apparatus;
FIG. 6 is a schematic view of the data fitting of step S14;
reference numerals: 11-forming surface; 12-a supporting surface; 21-a first roller; 22-a second roller; 23-a support; 24-a first hydraulic lever; 25-a frame; 251-a base; 252-a fixing frame; 253-lifting frame; 254-a cross beam; 26-a second hydraulic lever; 27-a first telescopic support rod; 28-a second telescopic support rod; 29-a height sensor; 3-skin segments; 31-a table top; 32-rotating the platform; 33-infrared rangefinder.
Description of the embodiments
The invention will be further described with reference to the drawings and examples.
The method for repairing the front edge skin of the wings and the tail wings of the aircraft comprises the following steps of
S1, performing 3D modeling according to the damaged skin size to obtain a 3D model of the die.
The front edge skin of the wing and the tail wing of the aircraft is divided into a plurality of sections, the skin shape of one section is shown in fig. 1, and the skin sizes of different sections are different.
When the skin of a section of the leading edge of the wing and tail of an aircraft is damaged, it is necessary to remove the skin of that section and replace it with a new skin section 3 without having to replace the entire skin.
In order to quickly obtain the 3D model of the damaged skin segment 3, all skin segments of the front edges of wings and tail wings of all models can be subjected to mold modeling to form a skin mold model database, when a certain skin segment 3 of a certain model is damaged, the corresponding 3D model can be directly called from the database and directly subjected to mold manufacturing, and site modeling is not needed, so that the damaged skin can be repaired more timely.
The specific process of modeling the skin of a certain section is as follows:
s11, as shown in fig. 2, the large end of the skin segment 3 is placed on a horizontal table 31. The table top 31 may be a flat ground or a flat table top, as long as the level is ensured.
S12, placing a rotating platform 32 on a horizontal table top 31, opening the skin segment 3 towards the rotating platform 32, and placing an infrared range finder 33 on the table top 31, wherein the infrared emission end of the infrared range finder 33 faces the inner side surface of the skin segment 3. The rotating platform 32 is a rotatable platform and is used for driving the infrared distance meter 33 to rotate, and the infrared distance meter 33 is used for detecting the distance from the infrared distance meter 33 to the inner side surface of the skin segment 3 so as to determine coordinates of a plurality of points at a certain height on the inner side surface of the skin segment 3.
And S13, utilizing the rotating platform 32 to drive the infrared distance meter 33 to rotate at a constant speed, and measuring and recording the distance of the infrared distance meter 33 at intervals to obtain a plurality of distance data.
The infrared range finder 33 emits infrared rays towards the inner side surface of the skin segment 3, the infrared rays are guaranteed to be in a horizontal state, the infrared range finder 33 measures once every 0.1 second to obtain distance data from the infrared range finder 33 to the inner side surface of the skin segment 3, and when the infrared rays horizontally scan the inner side surface of the skin segment 3, a plurality of distance data can be obtained.
And S14, fitting the measured distance data to obtain a smooth curve of the inner side surface of the skin segment 3.
The coordinates of a plurality of points on the inner side surface of the skin segment 3 can be determined according to the angle and distance of the infrared rays at the time of measurement by constructing a plane coordinate system with the point where the infrared emission head of the infrared range finder 33 is located as an origin, and as shown in fig. 6, fitting the points to obtain a smooth curve, the shape of which is similar to a parabola, as a horizontal section line of the inner side surface of the skin segment 3, and also as a section curve of the mold molding surface 11.
S15, determining the cross section size of the die, and lofting the cross section of the die according to the taper of the wing or the tail wing of the airplane to obtain a 3D model of the die.
The cross-sectional shape and size of the mold is determined by the mold material and skin size, so long as it has sufficient strength to withstand the forces of subsequent roll forming.
From the taper of the aircraft wing or tail, the loft length of the section of the mould should be greater than the length of the skin segment 3, so that the mould has a sufficiently long moulding surface 11.
And 3D modeling is carried out on each skin segment 3 of each model in the mode, so that a 3D model database of the mold is obtained. When repairing, 3D printing can be performed by only calling the model in the database to prepare the die.
S2, importing the 3D model into 3D printing software, and obtaining a die through 3D printing, wherein two side surfaces and a top cambered surface of the die form a forming surface 11, and the bottom surface of the die is a horizontal supporting surface 12. The specific structure of the mold is shown in fig. 3.
In the forming process of the skin, the mold can be subjected to extrusion force, so that the mold obtained by 3D printing has certain extrusion resistance. The printed mold should meet the strength requirements.
In addition, on the premise of ensuring that the strength meets the requirement, the mold quality is ensured not to be too large, and the mold is convenient to carry; the material of the die is common, so that the die is convenient for later-stage supplement; the material of the mould is nontoxic and harmless to human body, and meets the environmental protection requirement. According to the extrusion force of the skin mold, the polylactic acid (PLA) printing consumable material made of biological materials is selected according to the requirements of good strength, low density, high popularization rate and environment protection standard, and in order to lighten the weight of the mold and improve the 3D printing efficiency, the mold is a hollow mold. The basic properties of polylactic acid are as follows:
| glass transition temperature | 61℃ | Impact strength of simply supported beam | 2.2±1.03KJ/m 3 |
| Vicat softening temperature | 62℃ | Flexural Strength | 8.1±1.9MPa |
| Melting temperature | 149℃ | Tensile Strength | 28.1±1.3MPa |
| Crystallization temperature | 112℃ | Young's modulus | 1979±109MPa |
S3, as shown in FIG. 4, the supporting surface 12 of the mold is supported by a support 23, the skin sheet is horizontally arranged on the top of the mold, the skin sheet is pressed and fixed on the top of the mold by using a first roller 21 and a second roller 22, then the first roller 21 and the second roller 22 respectively move downwards along the two side surfaces of the mold, and the skin sheet is pressed and bent to be attached to the molding surface 11, so that a new skin is obtained.
The top of the support 23 is provided with a horizontal bearing surface, and the supporting surface 12 of the die is attached to the bearing surface, so that the stability of the die is ensured. The first roller 21 and the second roller 22 apply pressure to the skin sheet, thereby bending the skin sheet so that the skin sheet is formed into a new skin. The first roller 21 and the second roller 22 comprise an intermediate shaft and a rolling cylinder, the rolling cylinder can rotate relative to the intermediate shaft, the outer surface of the rolling cylinder is smooth, and when in rolling, the first roller 21 and the second roller 22 rotate to reduce friction between the first roller 21 and the second roller 22 and the skin plate, and the skin plate is prevented from being worn and pressed.
Because the skin segments 3 are irregularly shaped, the sizes of the skin plates adopted by the skins of different segments are different, in order to rapidly blanking the skin plates, a database consisting of the skin plate sizes required by each skin segment 3 of each model can be constructed, and the skin plates can be directly obtained by calculation according to the size of each skin segment 3.
When a new skin is manufactured, the size of the skin plate corresponding to the damaged skin segment 3 is obtained from the data, and then the material is cut and blanked. And trimming is not needed after the skin is formed.
And S4, installing the new skin at the damaged position.
When the skin is formed, the support 23 can be kept fixed, and the first roller 21 and the second roller 22 are pushed to roll by adopting hydraulic cylinder and other pressure equipment, so that the skin sheet is pressed and formed. If this way is adopted, in order to ensure that the first roller 21 and the second roller 22 roll stably, the pressure of the first roller 21 and the second roller 22 on the skin plate must be always perpendicular to the two sides of the mold, otherwise, slipping occurs, but since the two sides of the mold are irregularly shaped surfaces, the direction of the perpendicular line is constantly changed, the hydraulic cylinder cannot be controlled to be always perpendicular to the two sides of the mold, and the implementation difficulty is very high.
As a preferred embodiment of the present invention:
as shown in fig. 5, the support 23 is a lifting mechanism, the lengths of the first roller 21 and the second roller 22 are greater than the length of the mold, the first roller 21 and the second roller 22 are respectively connected with a first hydraulic rod 24 and a second hydraulic rod 26 which are inclined, and the upper ends of the first hydraulic rod 24 and the second hydraulic rod 26 are hinged on the frame 25.
In step S3, the first hydraulic rod 24 and the second hydraulic rod 26 apply thrust to the first roller 21 and the second roller 22, respectively, the jacking mechanism pushes the mold to move upwards, drives the skin sheet to move upwards, the first hydraulic rod 24 and the second hydraulic rod 26 gradually shrink, and the first roller 21 and the second roller 22 move downwards relative to two sides of the mold, and the skin sheet is pressed and bent to two sides of the bonding mold under the thrust of the first roller 21 and the second roller 22.
The jacking mechanism can push the die and the skin plate to move upwards integrally, and hydraulic mechanisms such as jacks can be adopted. The axial direction of the first and second hydraulic stems 24 and 26 can be maintained constant during the molding process, so that the first and second hydraulic stems 24 and 26 can be mounted very conveniently. The inclination angles of the first hydraulic lever 24 and the second hydraulic lever 26 should satisfy: at the initial stage of extrusion, the first hydraulic rod 24 and the second hydraulic rod 26 can be smoothly contracted; while the first 24 and second 26 hydraulic stems are perpendicular to the skin (or mold side), the first 21 and second 22 rollers are just pressed to the skin ends. In the process that the jacking mechanism pushes the mold and the skin plate to move upwards, the first hydraulic rod 24 and the second hydraulic rod 26 gradually shrink, and the thrust applied by the first hydraulic rod 24 and the second hydraulic rod 26 to the first roller 21 and the second roller 22 always meets the following conditions: the component of the thrust force in the direction perpendicular to the sides of the mold is greater than the pressure that presses the skin sheet against the sides of the mold to ensure that the skin sheet abuts against the molding surface 11 of the mold.
The length of the first roller 21 and the second roller 22 is longer than the length of the mold, so that the edges of the first roller 21 and the second roller 22 can be prevented from leaving an impression on the skin surface. When the radius of the roller can ensure bending, the skin can be tightly jacked by the mould and smoothly bent along the mould, so that the radius of the roller is calculated and analyzed according to the minimum bending radius of the front edge skins of wings and tail wings of different types of aircraft so as to ensure the optimal bending effect.
The front edge skins of the aircraft wings and the tail wings are of asymmetric structures, and skin plates are reasonably placed on a die before bending, so that the requirements can be met after bending. First, a mark is made at the top of the leading edge skin mold. And then calculating the lengths of the two sides of the top of the front edge skin by using a neutral layer theory, and marking on the skin plate according to a calculation result. And finally, placing the skin plate on a die, and ensuring that the mark of the skin plate is positioned at the top of the die. And the included angles between the first hydraulic rod 24 and the second hydraulic rod 26 and the vertical beam of the frame 25 are adjusted, so that the first roller 21 and the second roller 22 are ensured to press the skin plate. The invention can establish the size databases of the upper side and the lower side of the front edge skin of each model so as to quickly determine the vertexes of the skin plates.
Because the front edge skin is gradually tapered along the direction from the wing root to the wing tip, in order to ensure that the first roller 21 and the second roller 22 are completely attached to the pressed skin and the die in the rolling process, the axial installation angles of the first roller 21 and the second roller 22 should be adjusted according to the taper of the front edge skin of different types.
Specifically, two first hydraulic rods 24 are provided and are arranged at two ends of the first roller 21, and a first telescopic supporting rod 27 is arranged between each first hydraulic rod 24 and the frame 25; the number of the second hydraulic rods 26 is two, the two second hydraulic rods are arranged at two ends of the second roller 22, and a second telescopic supporting rod 28 is arranged between each second hydraulic rod 26 and the frame 25.
The first telescopic supporting rod 27 is obliquely arranged, the lower end of the first telescopic supporting rod is hinged with the first hydraulic rod 24, and the upper end of the first telescopic supporting rod is hinged with the frame 25; the second telescopic supporting rod 28 is obliquely arranged, the lower end of the second telescopic supporting rod is hinged with the second hydraulic rod 26, and the upper end of the second telescopic supporting rod is hinged with the frame 25. The upper ends of the first and second hydraulic rods 24 and 26 are also hinged to the frame 25 to adjust the angles of the first and second telescopic support rods 27 and 28, and the first and second rollers 21 and 22 are respectively hinged to the first and second hydraulic rods 24 and 26 to adjust the inclination angles of the first and second rollers 21 and 22.
The first telescopic support rod 27 and the second telescopic support rod 28 may adopt a bidirectional adjusting threaded rod. Before forming, the inclination of the first roller 21 and the second roller 22 is determined according to the taper of the skin, so that the first roller 21 and the second roller 22 can be completely attached to the skin plate. In step S3, the lengths of the two first telescopic support rods 27 are adjusted to adjust the inclination of the first roller 21, and the lengths of the two second telescopic support rods 28 are adjusted to adjust the inclination of the second roller 22.
Because the aircraft is different in size, the sizes of the moulds of the wings and the tail wings are also different greatly, in order to ensure that one set of equipment meets the skin forming of a plurality of models, the first roller 21 and the second roller 22 for extruding the skin are not only required to be adjustable in inclination angle, but also required to be adjustable in height. In order to adjust the heights of the first roller 21 and the second roller 22, it is necessary to ensure that the stand connecting the first roller 21 and the second roller 22 has an up-down elevating function.
Specifically, the stand 25 includes a base 251 and fixing frames 252 disposed at two ends of the base 251, the base 251 is a rectangular frame, and may be formed by welding profiles, and rollers are disposed at two ends of the base 251 to facilitate movement of the stand 25. The fixing frames 252 are fixed on the base 251, each fixing frame 252 is provided with a lifting frame 253, the lifting frames 253 are connected with the fixing frames 252 through lifting mechanisms, the height of each lifting frame 253 can be adjusted through the lifting mechanisms, and the lifting mechanisms can be various existing mechanisms with adjustable heights. The tops of the two lifting frames 253 are connected through a horizontal cross beam 254, the cross beams 254 are parallel to each other, the upper ends of the first hydraulic rod 24 and the second hydraulic rod 26 are hinged to the lifting frames 253, and the upper ends of the first telescopic supporting rod 27 and the second telescopic supporting rod 28 are hinged to the cross beam 254.
In order to precisely control the height of the lifting frame 253 and the jacking height of the jacking mechanism, a scale is arranged on the fixing frame 252, and a height sensor 29 is arranged on the jacking mechanism.
Through early measurement, the deepest depth of the front edge skin in all related models is 284mm, so that the maximum lifting size of the customized jack is 300mm, and the lifting weight is 3T.
The jack is driven by the double-loop hydraulic pump, because the moulds of a plurality of models are involved, and the longitudinal extrusion depth of each mould is different during extrusion, in actual operation, because the hydraulic pump drives the jack to rise at a higher speed, if the hydraulic pump power supply can not be closed in time, the hydraulic jack can be easily caused to continuously rise after the extrusion forming of the skin is completed, and the first roller 21 and the second roller 22 exceed the mould range, so that equipment and the skin are damaged. In order to solve the problem, a numerical control system is added on the electric hydraulic pump, the front edge depth corresponding to each skin segment 3 is recorded into a control system, the control system is connected with the electric hydraulic pump, the double-loop jack is connected with a height sensor 29, and when the lifting height of the jack reaches the height required by the current mould, the electric hydraulic pump can automatically stop oil supply, so that the electric hydraulic pump can lift as required when facing skins of different wing parts of different models. Meanwhile, in order to ensure that the skin extrusion rising process is soft, the oil supply speed of the hydraulic pump is customized to be 3L/min, and an adjustable throttle valve is additionally arranged at the position of an oil outlet of the hydraulic pump, so that the hydraulic oil flow can be adjusted according to actual conditions, and the purpose of controlling the lifting speed of the jack is achieved.
The rolling device (namely the skin forming device) adopted by the invention has a simple structure, and all parts are common parts and can be manufactured quickly. The device can immediately carry out new skin forming after skin damage, and the skin is formed by rolling once, so that the forming efficiency is high, the timely repair of the aircraft skin can be realized, and the repair of the aircraft skin is not required to be returned to a factory.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. 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 (8)
1. The method for repairing the front edge skin of the wings and the tail wings of the aircraft is characterized by comprising the following steps of
S1, performing 3D modeling according to the damaged skin size to obtain a 3D model of the die;
s2, importing the 3D model into 3D printing software, and obtaining a die through 3D printing, wherein two side surfaces and a top cambered surface of the die form a forming surface (11), and the bottom surface of the die is a horizontal supporting surface (12);
s3, supporting a supporting surface (12) of a die by a support (23), horizontally arranging a skin plate on the top of the die, pressing and fixing the skin plate on the top of the die by using a first roller (21) and a second roller (22), wherein the support (23) is a lifting mechanism, the lengths of the first roller (21) and the second roller (22) are larger than those of the die, the first roller (21) and the second roller (22) are respectively connected with a first inclined hydraulic rod (24) and a second inclined hydraulic rod (26), and the upper ends of the first hydraulic rod (24) and the second hydraulic rod (26) are connected to a frame (25); the two first hydraulic rods (24) are arranged at two ends of the first roller (21), and a first telescopic supporting rod (27) is arranged between each first hydraulic rod (24) and the frame (25); the two second hydraulic rods (26) are arranged at two ends of the second roller (22), and a second telescopic supporting rod (28) is arranged between each second hydraulic rod (26) and the frame (25); the length of the two first telescopic support rods (27) is adjusted to adjust the inclination of the first roller (21), and the length of the two second telescopic support rods (28) is adjusted to adjust the inclination of the second roller (22); the first hydraulic rod (24) and the second hydraulic rod (26) respectively apply thrust to the first roller (21) and the second roller (22), the jacking mechanism pushes the mold to move upwards to drive the skin plate to move upwards, the first hydraulic rod (24) and the second hydraulic rod (26) gradually shrink, the first roller (21) and the second roller (22) move downwards relative to the two sides of the mold, and the skin plate is pressed and bent to the two sides of the bonding mold under the action of the thrust of the first roller (21) and the second roller (22) to obtain new skin;
and S4, installing the new skin at the damaged position.
2. The method for repairing the leading edge skin of the wings and the tail wings of an aircraft according to claim 1, wherein the step S1 specifically comprises:
s11, placing the large end of the skin segment (3) on a horizontal table top (31);
s12, placing a rotary platform (32) on a horizontal table top (31), wherein an opening of the skin segment (3) faces the rotary platform (32), and placing an infrared range finder (33) on the table top (31), wherein an infrared emission end of the infrared range finder (33) faces the inner side surface of the skin segment (3);
s13, driving an infrared distance meter (33) to rotate at a constant speed by utilizing a rotating platform (32), and measuring and recording the distance of the infrared distance meter (33) at intervals to obtain a plurality of distance data;
s14, fitting the measured distance data to obtain a smooth curve of the inner side surface of the skin segment (3);
s15, determining the cross section size of the die, and lofting the cross section of the die according to the taper of the wing or the tail wing of the airplane to obtain a 3D model of the die.
3. The method for repairing the leading edge skin of an aircraft wing and tail wing according to claim 1, wherein in step S2, a polylactic acid printing die is used.
4. The method of repairing a leading edge skin of an aircraft wing and tail according to claim 1, wherein the mold is a hollow mold.
5. The method of repairing a leading edge skin of an aircraft wing and tail according to claim 1, wherein the lifting mechanism is a jack.
6. The method for repairing the front edge skin of the wing and the tail wing of an aircraft according to claim 1, wherein the frame (25) comprises a base (251) and fixing frames (252) arranged at two ends of the base (251), each fixing frame (252) is provided with a lifting frame (253), the tops of the two lifting frames (253) are connected through a cross beam (254), the upper ends of the first hydraulic rod (24) and the second hydraulic rod (26) are hinged to the lifting frames (253), and the upper ends of the first telescopic supporting rod (27) and the second telescopic supporting rod (28) are hinged to the cross beam (254).
7. The method for repairing the leading edge skin of an aircraft wing and tail wing according to claim 6, wherein a graduated scale is arranged on the fixed frame (252).
8. Method for repairing the leading edge skin of an aircraft wing and tail according to claim 1, characterized in that the lifting mechanism is provided with a height sensor (29).
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| CN202310143410.0A CN115871955B (en) | 2023-02-21 | 2023-02-21 | Method for repairing front edge skin of airplane wing and tail wing |
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|---|---|---|---|
| CN202310143410.0A CN115871955B (en) | 2023-02-21 | 2023-02-21 | Method for repairing front edge skin of airplane wing and tail wing |
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| CN115871955B true CN115871955B (en) | 2023-06-06 |
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