Tool design method for precisely manufacturing connecting holes in multi-layer structural part of semi-closed area of aircraft component

Abstract

The invention discloses a tool design method for precisely manufacturing a connecting hole in a multi-layer structural part of a semi-closed area of an aircraft component, and belongs to the technical field of connecting holes in the semi-closed area of the aircraft component. The electric tool comprises a cutter gear box body, a motor gear box body, a power shaft, a transmission shaft, a bevel gear set, a cutter and a mounting seat, and determining the relationship between the size of each part of the electric tool and the narrow space of the multilayer structural member of the semi-closed area of the aircraft component, and manufacturing and using the electric tool according to the relationship. According to the method, the connecting holes of other structural parts can be determined according to the initial hole of the inner-layer part in the multi-layer structural part, and the hole wall is used as the guide of the cutter to realize the standard consistency of the connecting holes of the multi-layer structural part, so that the hole coaxiality of the inner-layer part and the outer-layer part is good; the tool is small in size and can work in a semi-closed area of an aircraft component, and the corresponding specification of the tool can be selected according to the aperture of a primary hole for guiding and different materials of outer-layer parts. Compared with a conventional method, the method is more accurate and convenient.

Description

Technical Field

[0001] The invention belongs to the technical field of connecting holes in semi-enclosed areas of aircraft components and relates to the connection of multi-layer structural parts. Background Art

[0002] The structure of aviation products is becoming more and more compact. The main structure mostly adopts integrated wall panels and frame sections. The integrated design will have narrow and long cavities or closed angle areas in some spaces, which will inevitably produce closed or semi-closed working states during assembly. At the same time, the inner structure frame sections of aviation products often have structures such as reinforcing ribs and bosses, which require higher position accuracy than the outer wall panels, connecting plates and other parts. Therefore, it is necessary to make the hole positions first; some inner structures are used as the basis for the coordination of multiple parts and components, and assembly holes need to be made, and some assembly holes cannot avoid multi-layer connection areas, etc. At present, domestic aviation companies use conventional methods such as marking, manual measurement, and template transfer to lead the holes on the inner parts to the outer parts. When encountering multi-curvature parts and a large number of return holes, the conventional methods are not ideal and accurate in terms of hole position accuracy and efficient operation. Conventional means are not suitable for the development trend of rapid manufacturing and high quality of aviation products. Therefore, it is urgent to invent a method that can achieve efficient completion of the hole making operation in the semi-closed area and ensure the accuracy of the hole positions on multi-layer structural parts. Summary of the invention

[0003] The purpose of the present invention is to design and invent an electric marking and drilling tool for narrow spaces, which is used in the narrow and long semi-enclosed area of ​​component connection. The tool uses the inner layer part hole as a guide to accurately locate the connection hole of the outer layer structure. In order to achieve the accuracy, convenience and universal applicability of the outward return hole, a set of electric mechanical devices is designed. The device has a replaceable tool with a guide. According to the prefabricated holes of different diameters on the inner layer parts of the component, the corresponding tool is selected to determine the center of the hole on the outer layer part.

[0004] The technical solution of the present invention is to design a tool structure based on a theoretical model of a hole-making tool constructed in a semi-enclosed area structure of an aircraft component:

[0005] The tool design method for accurately making connection holes for multi-layer structural parts in semi-enclosed areas of aircraft components includes the following steps:

[0006] Step 1: Basic structural design of power tools with replaceable tools

[0007] The electric tool comprises a tool gear housing 1, a motor gear housing 2, a power shaft 3, a transmission shaft 4, a bevel gear set 5, a tool 6 and a mounting seat 7;

[0008] The tool gear box body 1 is coaxially connected with the motor gear box body 2. One end of the transmission shaft 4 in the tool gear box body 1 and the motor gear box body 2 is connected to the power shaft 3 through a bevel gear set 5 at the end of the motor gear box body 2, and the power shaft 3 is connected to the motor and the speed regulator; the axial direction of the power shaft 3 is perpendicular to the axial direction of the transmission shaft 4; in the motor gear box body 2, the bevel gear set 5 is used to realize the transmission and direction conversion between the power shaft 3 and the transmission shaft 4; the other end of the transmission shaft 4 is connected to the mounting seat 7 through the bevel gear set 5, the axial direction of the mounting seat 7 is perpendicular to the axial direction of the transmission shaft 4, and the bevel gear set 5 is used in the tool gear box body 1 to realize the transmission and direction conversion between the transmission shaft 4 and the mounting seat 7; the tool 6 is fixed on the mounting seat 7.

[0009] Furthermore, according to the diameter of the prefabricated hole on the inner part of the multilayer structure of the semi-enclosed area of ​​the aircraft component and the material of the multilayer structure of the semi-enclosed area of ​​the aircraft component, the diameter d of the guide section of the tool 6 is 1 Designed into series of different specifications to meet different application scenarios, the head of tool 6 adopts a spherical diamond grinding head, and the tail end of tool 6 adopts a hexagonal head step seat with a width of S;

[0010] Furthermore, the mounting seat 7 is fixed inside the tool gear housing 1, and the hexagonal groove with a width of S is used to install the hexagonal head step seat of the tool 6, so that quick release and secure installation can be achieved through clearance fit.

[0011] Furthermore, the power input part adopts a DC motor to drive the power shaft 3, and the speed regulator is used to perform stepless changes in the electric speed machine to meet the hole making requirements of component structures of different laminated materials.

[0012] Step 2: Determine the relationship between the dimensions of the various parts of the power tool and the narrow space of the multi-layer structure in the semi-enclosed area of ​​the aircraft component:

[0013] (2.1) According to the spatial height dimension L of the semi-enclosed area of ​​the multi-layer structure of the semi-enclosed area of ​​the aircraft component 0 , determine the overall size of the power tool and reserve a space Δ (not less than 2mm) for the power tool to move. The overall size of the power tool needs to consider the height of the outer contour of the tool gear housing 1 and the height of the tool 6 protruding from the tool gear housing 1. Suppose the height L of the outer contour of the tool gear housing 1 is 1 The height of the replaceable tool 6 protruding from the tool gear housing 1 is L 2 Then you need to meet:

[0014] L 1 +L 2 +Δ<L 0 (1)

[0015] (2.2) According to the initial hole D on the inner part of the multi-layer structure of the semi-enclosed area of ​​the aircraft component 0, the replaceable tool 6 is designed to guide the diameter d of the section 1 ;Thickness of inner parts h 0 The height h of the tool tip is determined. In order to ensure the coaxiality of the holes of the outer structure and the inner part, the length of the tool guide section in the inner structure hole must be sufficient, that is, the height h of the tool tip cannot be too large. Its value can be determined based on the thickness h of the inner part. 0 Sure:

[0016] h≤(0.25~0.3)h 0 (2)

[0017] (2.3) The internal space of the electric tool is affected by the height L 1 Limitations: The transmission axes of the tool end and the power end cannot be in the same direction. At the same time, the tool needs to output stably at a speed of n≤1000r / min. Therefore, an orthogonal transmission spur bevel gear set with a transmission ratio of i=1 is selected. At this time, the pitch cone angle δ of each gear in the gear set is 45°.

[0018] (2.4) Basic tooth profiles of bevel gears and their dimensional parameters: tooth profile angle α, tooth top height coefficient h a , the top clearance coefficient c complies with the provisions of GB 12369. 1 Limitations, pitch circle diameter d, installation distance A need to be determined according to the structure; the large end face module m conforms to the provisions of GB 12368. In order to avoid undercutting, the number of teeth z is at least

[0019]

[0020] Furthermore, the large end face modulus m is 0.3 to 0.6 mm.

[0021] Beneficial effects of the present invention:

[0022] This method can determine the connection holes of other structural parts based on the initial holes of the inner parts in the multi-layer structural parts, and use the hole wall as a guide for the tool to achieve the consistency of the reference of the connection holes of the multi-layer structural parts, so the coaxiality of the holes of the inner and outer parts is good; this tool is small and can work in the semi-enclosed area of ​​the aircraft parts, and the tool can be selected according to the initial hole diameter used as a guide and the different materials of the outer parts. Overview This method is more accurate and convenient than conventional methods. It has the following main advantages:

[0023] (1) The tool is small and less affected by the space of the working area. The transmission shaft 4 between the tool gear box 1 and the motor gear box 2 is appropriately extended to meet different working scenarios.

[0024] (2) The cutter 6 adopts a replaceable quick-release connection form, and different series of specifications can be selected according to the size of the prefabricated initial hole of the structural part; in addition, different material series can be selected according to the material of the outer layer parts of the component, so the scope of use is wider.

[0025] (3) The tool 6 has a guide structure, which uses the prefabricated hole on the inner layer part as a guide, and can ensure a high coaxial accuracy when determining the center hole of the outer layer part of the component.

[0026] (4) The connecting device is driven by a motor and a gear, and has a stable output power, which can avoid and reduce the adverse factors of uneven power and unstable tool cutting speed during manual operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is the main structure of the electric tool.

[0028] Figure 2 Schematic diagram of the disassembled structure of the mounting seat, bevel gear set and tool.

[0029] Figure 3 This is an application example diagram.

[0030] In the figure: 1-tool gear box; 2-motor gear box; 3-power shaft; 4-transmission shaft; 5-bevel gear set; 6-tool; 7-mounting seat. DETAILED DESCRIPTION

[0031] The technical solution of the present invention is further described below based on the accompanying drawings and embodiments.

[0032] 1. Develop the relationship between the various parts of the tool and the narrow space. The specific steps are as follows:

[0033] According to the semi-enclosed area space size L of the multi-layer structural part of the aircraft component 0 , determine the overall size of the tool and reserve a space for the tool to move (recommended to be no less than 2mm), and design the height L of the tool body 1 and the height L of the replaceable tool protruding from the tool body 2 :

[0034] L 1 +L 2 +Δ<L 0 (1)

[0035] According to the initial hole D on the inner part of the multi-layer structural part of the semi-enclosed area of ​​the aircraft component 0 , design replaceable tool for the diameter d of the guide section 1 ;Thickness of inner parts h 0The height h of the tool tip is determined to ensure the coaxiality of the holes of the outer structure and the inner part. The length of the tool guide section in the inner structure hole must be sufficient, that is, the height h of the tool tip cannot be too large. Its value can be determined based on the thickness h of the inner part. 0 Sure:

[0036] h≤(0.25~0.3)h 0 (2)

[0037] The internal space of the tool body is controlled by the height L 1 Limitations: The transmission axes of the tool end and the power end cannot be in the same direction. At the same time, the tool requires a low speed (n≤1000r / min) and stable output. Therefore, an orthogonal transmission spur bevel gear set with a transmission ratio of i=1 is selected. At this time, the pitch cone angle δ of each gear in the gear set is 45°.

[0038] The basic tooth profile of each bevel gear and its dimensional parameters: tooth profile angle α, tooth top height coefficient h a , the top clearance coefficient c complies with the provisions of GB12369. The height of the tool body L 1 Limitations, pitch circle diameter d, installation distance A need to be determined according to the structure; the large end face module m complies with the provisions of GB 12368. In this example, it is recommended to select a range of (0.3 to 0.6) mm; in order to avoid undercutting, the number of teeth z is at least

[0039]

[0040] 2. Design a set of electric tools with replaceable tools. The gear transmission, commutation and other methods inside the tool body are as described above. The replaceable tools are selected in different specifications according to the diameter of the prefabricated holes on the inner parts of the component and the structural material. The power input part adopts a DC motor to drive the gear set, and the speed regulator is used to change the electric speed machine steplessly to meet the hole-making requirements of component structures of different laminated materials.

[0041] The tool is mainly composed of seven parts: tool gear box 1, motor gear box 2, power shaft 3, transmission shaft 4, bevel gear set 5, tool 6, and mounting seat 7. Among them, the outer profile height L of the tool gear box 1 is 1 The bevel gear set 5 is used inside to realize the transmission and direction conversion between the transmission shaft 4 and the mounting seat 7; the motor gear box 2 uses the bevel gear set 5 to realize the transmission and direction conversion between the power shaft 3 and the transmission shaft 4; the diameter d of the guide section of the tool 6 1 It is designed into a series of different specifications to meet different application scenarios. The head adopts a spherical diamond grinding head, and the tail end adopts a hexagonal step seat with a width of S; the mounting seat 7 is fixed inside the tool gear box 1, and the hexagonal groove with a width of S is used to install the hexagonal step seat of the tool 6, so that quick release and secure installation can be achieved through clearance fit.

[0042] Here’s how to use it:

[0043] S1 selects a tool 6 of corresponding specifications according to the diameter of the prefabricated hole on the inner layer part of the multi-layer structural part of the semi-enclosed area of ​​the aircraft component, and installs the tool 6 on the mounting seat 7;

[0044] S2 installs the device onto the motor module through the power shaft 3;

[0045] S3: placing the assembled device into the inner cavity of the multilayer structural member in the semi-enclosed area of ​​the aircraft component, and placing the tool 6 into the prefabricated hole of the inner layer part of the component;

[0046] S4 checks that the tool 6 is in the prefabricated hole, and the manual swing device senses that the tool 6 is stably placed in the prefabricated hole;

[0047] S5 adjusts the motor speed according to the material of the outer layer of the component, then turns on the power of the device, and manually holds the device to "drill" the center hole toward the outer layer along the hole wall;

[0048] S6 disassembles the interlayer of the component and checks the position accuracy of the center hole; after confirming that the deviation range is acceptable, reassembles the component and makes the remaining center holes.

Claims

1. A tool design method for accurately making connection holes in multi-layer structural parts in semi-enclosed areas of aircraft components, characterized in that: Here are the steps: Step 1: Basic structural design of power tools with replaceable tools The electric tool comprises a tool gear housing (1), a motor gear housing (2), a power shaft (3), a transmission shaft (4), a bevel gear set (5), a tool (6) and a mounting seat (7); The tool gear box (1) is coaxially connected to the motor gear box (2); one end of the transmission shaft (4) in the tool gear box (1) and the motor gear box (2) is connected to the power shaft (3) at the end of the motor gear box (2) through a bevel gear set (5); the power shaft (3) is connected to the motor and the speed regulator; the axial direction of the power shaft (3) is perpendicular to the axial direction of the transmission shaft (4); in the motor gear box (2), the bevel gear set (5) is used to realize transmission and direction conversion between the power shaft (3) and the transmission shaft (4); the other end of the transmission shaft (4) is connected to the mounting seat (7) through the bevel gear set (5); the axial direction of the mounting seat (7) is perpendicular to the axial direction of the transmission shaft (4); in the tool gear box (1), the bevel gear set (5) is used to realize transmission and direction conversion between the transmission shaft (4) and the mounting seat (7); a tool (6) is fixed on the mounting seat (7); Step 2: Determine the relationship between the dimensions of the various parts of the power tool and the narrow space of the multi-layer structure in the semi-enclosed area of ​​the aircraft component: (2.1) Based on the spatial height dimension L0 of the semi-enclosed area of ​​the multi-layer structure of the semi-enclosed area of ​​the aircraft component, the overall dimension of the electric tool is determined and a movable space Δ of the electric tool is reserved. The overall dimension of the electric tool needs to take into account the outer profile height of the tool gear housing (1) and the height of the tool (6) protruding from the tool gear housing (1). Assuming that the outer profile height L1 of the tool gear housing (1) and the height of the replaceable tool (6) protruding from the tool gear housing (1) are L2, then the following conditions need to be satisfied: L1+L2+Δ<L0 (1) (2.2) According to the initial hole D0 on the inner layer part of the multi-layer structure of the semi-enclosed area of ​​the aircraft component, a replaceable tool (6) is designed to guide the diameter d1 of the section; the thickness h0 of the inner layer part determines the height h of the tool tip. In order to ensure the coaxiality of the holes of the outer layer structure and the inner layer part, the length of the tool guide section in the inner layer structure hole needs to be sufficient, that is, the height h of the tool tip cannot be too large, and its value can be determined according to the thickness h0 of the inner layer part: h≤(0.25~0.3)h0 (2) (2.3) The internal space of the electric tool is limited by the height L1. The transmission axis of the tool end and the power end cannot be in the same direction. At the same time, the tool needs to output stably at a speed of n≤1000r / min. Therefore, an orthogonal transmission spur bevel gear set with a transmission ratio i=1 is selected. At this time, the pitch cone angle δ of each gear in the gear set is 45°; (2.4) Basic tooth profiles of bevel gears and their dimensional parameters: tooth profile angle α, tooth top height coefficient h a , the top clearance coefficient c complies with the provisions of GB12369; limited by the height L1, the pitch circle diameter d and the installation distance A need to be determined according to the structure; the large end face module m complies with the provisions of GB 12368. In order to avoid undercutting, the number of teeth z is at least 2. The tool design method for accurately making connection holes in multi-layer structural parts in semi-enclosed areas of aircraft parts according to claim 1, characterized in that: According to the diameter of the prefabricated hole on the inner layer part of the multilayer structure of the semi-enclosed area of ​​the aircraft component and the material of the multilayer structure of the semi-enclosed area of ​​the aircraft component, the diameter d1 of the guide section of the tool (6) is designed into a series of different specifications to meet different application scenarios. The head of the tool (6) adopts a spherical diamond grinding head, and the tail end of the tool (6) adopts a hexagonal head step seat with a width of S.

3. The tool design method for accurately making connection holes in multi-layer structural parts in semi-enclosed areas of aircraft parts according to claim 1 or 2, characterized in that: The mounting seat (7) is fixed inside the tool gear housing (1), and a hexagonal groove with a width of S is used to mount the hexagonal head step seat of the tool (6), so that quick release and secure installation are achieved through clearance fit.

4. The tool design method for accurately making connection holes in multi-layer structures in semi-enclosed areas of aircraft parts according to claim 1 or 2, characterized in that: The power input part adopts a DC motor to drive the power shaft (3), and the speed regulator is used to perform stepless changes in the electric speed machine to meet the hole making requirements of component structures of different laminated materials.

5. The tool design method for accurately making connection holes in multi-layer structural parts in semi-enclosed areas of aircraft parts according to claim 3, characterized in that: The power input part adopts a DC motor to drive the power shaft (3), and the speed regulator is used to perform stepless changes in the electric speed machine to meet the hole making requirements of component structures of different laminated materials.

6. The tool design method for accurately making connection holes in multi-layer structures in semi-enclosed areas of aircraft parts according to claim 1, 2 or 5, characterized in that: The large end face modulus m is 0.3~0.6mm.

7. The tool design method for accurately making connection holes in multi-layer structures in semi-enclosed areas of aircraft parts according to claim 3, characterized in that: The large end face modulus m is 0.3~0.6mm.

8. The tool design method for accurately making connection holes in multi-layer structural parts in semi-enclosed areas of aircraft parts according to claim 4, characterized in that: The large end face modulus m is 0.3~0.6mm.

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