Wing drilling equipment applied to aircraft composite material plate and using method
By designing an automated wing hole making equipment, the problems of low efficiency and cumbersome operation of traditional manual methods on aircraft wing composite plates are solved, and an efficient and precise hole making process is achieved, which is suitable for large-scale production.
Patent Information
- Application Number
- CN202411597020.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-11
- Publication Date
- 2025-03-28
AI Technical Summary
The traditional manual method has low efficiency in making holes on the composite material plate of the aircraft wing, cumbersome operation, and is greatly affected by human factors and has poor stability.
A wing hole making equipment including drilling machine bed body, Z-axis sliding track, hole making combination device, X-axis feed sliding track, drilling machine column and Y-axis radial sliding track are designed. The hole making process is automated using the drive motor sensor, speed adjustment controller and drill bit steering converter in the hole making combination device.
It realizes efficient hole making of wing composite plates, reduces the work difficulty of operators, reduces the influence of human factors, improves the accuracy and efficiency of hole making, and is suitable for large batches of aircraft wing hole making.
Smart Images
Figure CN119704323A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of aircraft wing hole making, and in particular to a wing hole making device applied to aircraft composite material plates and a use method thereof. Background Art
[0002] With the accelerated replacement of aviation products and the continuous improvement of performance requirements for aviation products, the aircraft manufacturing industry has also put forward high-quality and low-cost requirements for aircraft assembly technology. As one of the important components of an aircraft, the wing is mainly used to control the airflow to generate lift and change the direction of the airflow. At present, part of the aircraft wing is made of composite materials. In the future, with the update of science and technology and the strict control of aircraft take-off weight, the proportion of composite materials used in aircraft will be further expanded. Therefore, the traditional manual method of making holes in wing composite materials is not only labor-intensive, time-consuming and labor-intensive, but also has extremely low hole-making efficiency. In addition, the operator needs to strictly follow the traditional process step by step. The operation process is cumbersome, involving a series of operation processes such as line drawing, initial hole, hole expansion, and countersinking. At the same time, manual hole making is related to the actual operator's personal hole-making technical level and experience, and is greatly affected by human factors and has poor stability. Summary of the invention
[0003] The technical problem solved by the present invention is to provide a wing hole making device and a use method applied to aircraft composite material panels to solve the problems in the above-mentioned background technology.
[0004] The technical problem solved by the present invention is achieved by adopting the following technical solutions:
[0005] A wing hole-making device applied to composite material plates of aircraft comprises a drilling machine bed, a Z-axis sliding track, a hole-making assembly device, an X-axis feed sliding track, a drilling machine column and a Y-axis radial sliding track, wherein the drilling machine bed is provided with an X-axis feed sliding track for carrying the movement of the drilling machine bed and a Z-axis sliding track for driving the hole-making assembly device to move up and down, the drilling machine bed moves linearly along the X-axis sliding track, the hole-making assembly device is provided with a drill fixture, a hole-making drill bit and a built-in drilling motor, the drill fixture is installed with a hole-making drill bit, the built-in drilling motor is connected to the hole-making drill bit, the hole-making drill bit moves up and down along the Z-axis direction, and the Y-axis radial sliding track for carrying the drilling machine column to move radially is provided in the middle of the drilling machine bed.
[0006] In the present invention, the hole-making assembly device also includes a drive motor sensor, an adjustment speed controller and a drill steering converter, the adjustment speed controller is connected to the drive motor sensor, the drive motor sensor is connected to the drilling built-in motor, and the drill steering converter is connected to the hole-making drill bit.
[0007] A method for using a wing hole making device applied to an aircraft composite material plate, the specific steps are as follows:
[0008] 1) Set the movement path of the drill assembly and the wing hole processing parameters
[0009] According to the digital model of the aircraft wing, the specific parameters of the wing hole making are obtained, and then according to the specific parameters of the wing composite material plate hole making, the movement route of the drill assembly device and the wing hole making processing parameters are set;
[0010] 2) Correction of wing hole processing parameters
[0011] Firstly, the wing composite material plate and the wing truss are positioned, and then the wing shape contour and the wing truss are scanned and measured to obtain the actual shape contour model of the wing composite material plate and the wing truss, and then the obtained actual shape contour model hole making data is compared with the wing hole making processing parameters in the aircraft wing digital model, and the movement route of the drill assembly device and the wing hole making processing parameters are corrected to make the movement route of the drill assembly device and the wing hole making processing parameters consistent with the actual situation;
[0012] 3) Check the drilling point location
[0013] According to the movement route of the drill assembly device, the wing composite material plate is positioned and marked. After the marking is completed, the correctness and rationality of the drilling point position are checked again;
[0014] 4) Hole making and countersinking
[0015] According to the movement route of the drill assembly and the corrected wing hole making processing parameters, the wing composite material plate is drilled and countersunk. For the drilling points in the non-fatigue zone, the holes are drilled to the final hole and countersunk is performed; for the drilling points in the fatigue zone, the holes are drilled to the initial hole without countersunk.
[0016] In the present invention, a spiral milling method is used for feeding during drilling. In the first step, the wing composite material plate is firstly drilled, and the processing is stopped when the hole-making drill is processed to a distance from the material separation surface; in the second step, the processing parameters and rotation speed of the hole-making drill are adjusted to adapt to the drilling processing of the wing truss; in the third step, the wing composite material plate is separated from the wing truss, and the initial hole in the fatigue zone on the wing truss is cold-extruded. After the cold extrusion work is completed, the wing composite material plate and the wing truss are positioned and fitted again, and finally the initial hole is processed to the final hole, and the countersink is made.
[0017] Beneficial effects: The present invention can save manpower and reduce the difficulty of hole making for operators, and is not affected by external human factors. Even operators with no hole making experience can use this equipment to make holes in wing composite material plates. They only need to set the processing parameters and drill speed in advance to perform tool feeding processing, which not only improves the hole making accuracy, but also improves the hole making efficiency. It is suitable for large-scale aircraft wing hole making. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 It is a front view of a preferred embodiment of the present invention.
[0019] Figure 2 It is a side view of a preferred embodiment of the present invention.
[0020] Figure 3 It is a schematic diagram of the installation of the hole-making drill bit in the preferred embodiment of the present invention.
[0021] Figure 4 It is a schematic diagram of the installation of the hole-making assembly device in the preferred embodiment of the present invention. DETAILED DESCRIPTION
[0022] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below with reference to specific diagrams.
[0023] See also Figures 1 to 4 A wing hole-making device for aircraft composite material panels comprises a drilling machine bed 1, a Z-axis sliding track 2, a hole-making assembly device 3, an X-axis feeding sliding track 4, a drilling machine column 5, a hole-making drill 6, a drill fixture 7, a Y-axis radial sliding track 8 and a drilling built-in motor 9, wherein the drilling machine bed 1 is provided with an X-axis feeding sliding track 4 for carrying the movement of the drilling machine bed 1 and a Z-axis sliding track 2 for driving the hole-making assembly device 3 to move up and down, the drilling machine bed 1 moves linearly along the X-axis sliding track 4, the hole-making assembly device 3 is provided with a drill fixture 7, a hole-making drill 6 and a drilling built-in motor 9, the drill fixture 7 is equipped with a hole-making drill 6, the drilling built-in motor 9 is connected to the hole-making drill 6, the hole-making drill 6 moves up and down along the Z-axis direction, and the Y-axis radial sliding track 8 for carrying the drilling machine column 5 for radial movement is arranged in the middle of the drilling machine bed 1.
[0024] In this embodiment, the hole-making combination device 3 also includes a drive motor sensor, an adjustment speed controller and a drill steering converter. The adjustment speed controller is connected to the drive motor sensor, the drive motor sensor is connected to the drilling built-in motor 9, and the drill steering converter is connected to the hole-making drill bit 6.
[0025] In this embodiment, different hole-making drill bits 6 and drilling feed speeds are used for hole-making according to different materials of the aircraft wing wall panel. At the same time, the three-dimensional direction of the hole-making drill bit 6 can be adjusted to make holes according to different requirements of the hole-making point positions of the aircraft composite material plate. The specific method is as follows: the first step is to determine the position of the hole point to be drilled on the aircraft composite material plate and the size of the drilling hole diameter; the second step is to select the hole-making assembly device 3; the third step is to set the processing parameters such as the rotation speed of the hole-making drill bit 6 by adjusting the speed controller in the drill assembly device 3, and finally start the drill assembly device 3 to drill holes; therefore, the use of this equipment can save manpower and cost to a great extent, and there are no specific requirements for operators, so it is suitable for large-scale hole making.
[0026] In this embodiment, a method for using a wing hole making device applied to an aircraft composite material plate comprises the following specific steps:
[0027] 1) Setting the movement route of the drill assembly 3 and the wing hole making processing parameters
[0028] According to the aircraft wing digital model, the specific parameters of the wing hole making are obtained, and then according to the specific parameters of the wing composite material plate hole making, the movement route of the drill assembly device 3 and the wing hole making processing parameters are set;
[0029] 2) Correction of wing hole processing parameters
[0030] First, the wing composite material plate and the wing truss are positioned, and then the wing shape contour and the wing truss are scanned and measured to obtain the actual shape contour model of the wing composite material plate and the wing truss. After comparing the obtained hole making data of the actual shape contour model with the wing hole making processing parameters in the aircraft wing digital model, the movement route of the drill assembly device 3 and the wing hole making processing parameters are correspondingly corrected to make the movement route of the drill assembly device 3 and the wing hole making processing parameters consistent with the actual situation;
[0031] 3) Check the drilling point location
[0032] According to the movement route of the drill assembly device 3, the wing composite material plate is positioned and traced. After the trace is completed, the correctness and rationality of the drilling point position are checked again;
[0033] 4) Hole making and countersinking
[0034] According to the movement route of the drill assembly 3 and the corrected wing hole making processing parameters, as shown in Table 1, the wing composite material plate is drilled and countersunk. For the drilling points in the non-fatigue zone, the holes are drilled to the final hole and countersunk is performed. For the drilling points in the fatigue zone, the holes are drilled to the initial hole without countersunk.
[0035] When drilling, a spiral milling method is used. In the first step, the wing composite material plate is drilled first, and the processing is stopped when the hole-making drill bit 6 is processed to the distance from the material separation surface; in the second step, the processing parameters and rotation speed of the hole-making drill bit 6 are adjusted to adapt to the drilling processing of the wing truss; in the third step, the wing composite material plate is separated from the wing truss, and the initial hole in the fatigue zone on the wing truss is cold-extruded. After the cold extrusion work is completed, the wing composite material plate and the wing truss are positioned and fitted again, and finally the initial hole is processed to the final hole and countersunk.
[0036] Table 1 Hole making processing parameters
[0037]
Claims
1. A wing hole making device for aircraft composite material panels, comprising a drilling machine bed, a Z-axis sliding track, a hole making assembly device, an X-axis feed sliding track, a drilling machine column and a Y-axis radial sliding track, characterized in that: The drilling machine bed is provided with an X-axis feed sliding track for carrying the movement of the drilling machine bed and a Z-axis sliding track for driving the hole-making assembly device to move up and down; the hole-making assembly device is provided with a drill fixture, a hole-making drill bit and a built-in drilling motor; the drill fixture is equipped with a hole-making drill bit, the built-in drilling motor is connected to the hole-making drill bit, the hole-making drill bit moves up and down along the Z-axis direction, and the Y-axis radial sliding track for carrying the drilling machine column for radial movement is provided in the middle of the drilling machine bed.
2. The wing hole making equipment for aircraft composite material panels according to claim 1, characterized in that: The hole-making assembly device also includes a drive motor sensor, a speed adjustment controller and a drill bit steering converter, wherein the speed adjustment controller is connected to the drive motor sensor, the drive motor sensor is connected to the drilling built-in motor, and the drill bit steering converter is connected to the hole-making drill bit.
3. A method for using the wing hole making device for aircraft composite material panels according to any one of claims 1 to 2, characterized in that: Firstly, according to the digital model of the aircraft wing, the movement route of the drill assembly and the wing hole making processing parameters are set. Then, according to the obtained actual shape contour model and the wing hole making processing parameters in the digital model of the aircraft wing, the wing hole making processing parameters are corrected; and the position of the drilling point is checked. Finally, according to the movement route of the drill assembly and the corrected hole making processing parameters, holes and countersinks are made on the wing composite material plate.
4. The method for using the wing hole making device for aircraft composite material panels according to claim 3, wherein: The specific steps are as follows: 1) Set the movement path of the drill assembly and the wing hole processing parameters According to the digital model of the aircraft wing, the specific parameters of the wing hole making are obtained, and then according to the specific parameters of the wing composite material plate hole making, the movement route of the drill assembly device and the wing hole making processing parameters are set; 2) Correction of wing hole processing parameters Firstly, the wing composite material plate and the wing truss are positioned, and then the wing shape contour and the wing truss are scanned and measured to obtain the actual shape contour model of the wing composite material plate and the wing truss, and then the obtained actual shape contour model hole making data is compared with the wing hole making processing parameters in the aircraft wing digital model, and the movement route of the drill assembly device and the wing hole making processing parameters are corrected to make the movement route of the drill assembly device and the wing hole making processing parameters consistent with the actual situation; 3) Check the drilling point location According to the movement route of the drill assembly device, the wing composite material plate is positioned and marked. After the marking is completed, the correctness and rationality of the drilling point position are checked again; 4) Hole making and countersinking According to the movement route of the drill assembly and the corrected wing hole making processing parameters, the wing composite material plate is drilled and countersunk. For the drilling points in the non-fatigue zone, the holes are drilled to the final hole and countersunk is performed. For the drilling points in the fatigue zone, the holes are drilled to the initial hole without countersunk.
5. The method for using the wing hole making device for aircraft composite material panels according to claim 4, wherein: In step 4), when drilling: the first step is to drill the wing composite material plate first, and stop the processing when the hole-making drill is processed to the distance from the material separation surface; the second step is to adjust the processing parameters and rotation speed of the hole-making drill to adapt to the wing truss drilling processing; the third step is to separate the wing composite material plate from the wing truss, and cold extrude the initial hole in the fatigue zone on the wing truss. After the cold extrusion work is completed, the wing composite material plate and the wing truss are positioned and fitted again, and finally the initial hole is processed to the final hole and countersunk.
6. A method for using the wing hole making device for aircraft composite material panels according to any one of claims 1 to 2 according to claim 5, characterized in that: The cutting tool is fed in spiral milling mode.