Method of preparing a fairing for an aircraft for installation

Abstract

The application provides a method for manufacturing and installing a fairing device of an aircraft, and the method comprises the following steps: outer frame processing: the circumferential length is controlled through inner ring roller circle control, and then the diameter of the circle ring is regulated; the middle stand plate is cut out by water cutting, and a hollow annular piece with a size of φ4320X400 is directly cut out for basic processing; the outer frame roundness error is adjusted to be less than or equal to 6 mm; the guide surface of the outer frame is arranged to be axially parallel to the guide surface of the frame; and the flatness of the guide groove of the outer frame and the frame is adjusted to be less than or equal to 0.1; frame processing: the stand plate is fixed on a welded steel platform by using a tool, and a T-shaped frame is welded; after straightening after welding, annealing is performed; after annealing, the workpiece is horizontally placed, the steel plate is faced, the dust screen mounting surface is processed by one-time clamping of a numerical control longmen mill on the workpiece, and the mounting surface reaches a flatness of 0.12 mm; square hole module processing: the square hole module is composed of a module outer frame, a vertical partition plate, a horizontal partition plate, a partition plate and an arc plate, and the thickness of the square hole module outer frame stand plate is 5 mm.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of fairings, and particularly relates to a preparation and installation method of a fairing device for an aircraft. BACKGROUND

[0002] At present, the aerodynamic performance of an aircraft has an important influence on its overall performance and maneuverability, and a fairing device is one of the important means to improve the aerodynamic performance of an aircraft. The existing fairing device of an aircraft has problems such as complex structure, inconvenient installation, and unsatisfactory effect, therefore, it is of great significance to develop a fairing device with simple structure, convenient installation, and good effect, and a preparation and installation method thereof, for improving the aerodynamic performance of an aircraft.

[0003] At present, the fairing device of an aircraft mainly includes two types: one is a fairing device based on shape design, and the other is a fairing device based on material selection.

[0004] The fairing device based on shape design mainly changes the shape structure of the aircraft to optimize the aerodynamic performance of the aircraft. This type of fairing device includes various winglets, tail wings, spoilers, etc., and by carefully designing the shape, size and position of these components, the airflow on the surface of the aircraft can be effectively regulated, and the aerodynamic performance of the aircraft can be improved. However, this type of fairing device usually requires a large number of experiments and calculations for design and optimization, so the development cost is high, and the effect is not always ideal.

[0005] The fairing device based on material selection mainly selects appropriate aerodynamic materials to improve the aerodynamic performance of the aircraft. This type of fairing device includes various aerodynamic films, coatings, etc., which have different microstructures and properties and can have different effects on the airflow on the surface of the aircraft. However, this type of fairing device usually requires a large number of experiments and calculations to select appropriate aerodynamic materials, so the development cost is also high, and the effect is not always ideal.

[0006] In summary, the existing fairing device of an aircraft has problems such as complex structure, inconvenient installation, and unsatisfactory effect, therefore, it is of great significance to develop a fairing device with simple structure, convenient installation, and good effect, and a preparation and installation method thereof, for improving the aerodynamic performance of an aircraft.

[0007] Therefore, there is an urgent need for a preparation and installation method of a fairing device for an aircraft. SUMMARY

[0008] The application provides a preparation and installation method of a fairing device for an aircraft, which solves the problems of poor internal airflow of the aircraft, insufficient stability of the aircraft, poor preparation and installation precision of the entire fairing, and inability to be applied to high-demand flight missions in the prior art.

[0009] The technical scheme of the present application is implemented as follows: a method for preparing and installing a fairing device for an aircraft, comprising the following steps:

[0010] Outer frame processing:

[0011] The circumference length is controlled by the inner ring roller circle, and then the diameter of the ring is adjusted. The intermediate vertical plate is cut by water cutting to directly cut a hollow ring piece with a size of φ4320X400 for basic processing. The outer frame roundness error is adjusted to be ≤6mm, and the guide surface of the outer frame is set to be axially parallel to the guide surface of the frame. The flatness of the guide groove of the outer frame and the frame is adjusted to be ≤0.1.

[0012] Frame processing:

[0013] The vertical plate is fixed on the welded steel platform by a tool, and a T-shaped frame is welded. After straightening, annealing is performed. After annealing, the workpiece is placed horizontally, and the steel plate is faced. The dust screen mounting surface is machined by one-time clamping of the numerical control gantry milling machine on the workpiece, and the mounting surface reaches a flatness of 0.12mm.

[0014] Square hole module processing:

[0015] The square hole module is composed of a module outer frame, a vertical partition plate, a horizontal partition plate, a partition plate and an arc plate. The thickness of the vertical plate of the square hole module outer frame is 5mm. The vertical plate is cut by water cutting to the outer dimension. Four corners are connected by half-round steel pipes, welded by a welding tool, and matched by three vertical plate bending at the combined part with the outer frame.

[0016] During installation, the dust screen module is first cut according to the size of the outer frame. The dust screen with a winding steel rod is first fixed on the frame by pressing the net module and the bolt. At least two edges are fixed, and the corresponding edges are less than 2-4mm in width. The dust screen is tightened and straightened by the bolt, and the dust screen is configured according to the three-layer structure of coarse, fine and coarse from outside to inside.

[0017] Then the square hole module is assembled and welded. The square hole module outer frame is clamped by a special tool to control the deformation during welding. After welding, cooling is performed. Then the assembly is performed after the pressing plate is loosened. The square hole module is placed on the sliding support plate on the frame, and then assembled and welded. After welding, the weld is polished, and the assembled fairing is cleaned by compressed air and an industrial dust collector.

[0018] As a preferred embodiment, the horizontal partition plate and the vertical partition plate of the square hole module have the same structure and are perpendicular to each other. The horizontal partition plate and the vertical partition plate are processed with a 3mm thin-walled plate to be sleeved. The horizontal partition plate and the vertical partition plate are provided with a few type cross section on the side end surface connected with the partition plate.

[0019] As a preferred embodiment, the U-shaped section is formed by folding the horizontal partition plate and the vertical partition plate by a bending machine, and is slotted by a special tool.

[0020] As a preferred embodiment, when slotting, a special tool for milling a 2.2mm wide slot is used, the flatness of the flat surface of the tool is 0.02mm, the starting positioning surface is perpendicular to the length direction, and 3-4 equal height blocks are fixed on the upper surface according to the length of the partition plate. After fixing the partition plate, the starting positioning surface is abutted by the reference vertical surface.

[0021] After the above technical scheme is adopted, the beneficial effects of the present application are: the square hole module is nested and fixed by the outer frame, making the fairing device more stable and firm, improving its structural strength and stability. The frame is installed on the front end face of the square hole module, and the sliding supporting plate is arranged on the frame, so that the square hole unit can be fixed through the sliding supporting plate, and has better adjustability and adaptability, which can better adapt to the needs of different aircrafts. The dust screen module is installed on the front end face of the frame, and the dust screen module is connected with the outer frame through the fastening screw, which can effectively prevent the aircraft from being affected by dust and other sundries during flight, and improve the aerodynamic performance and reliability of the aircraft. The frame and the dust screen module are matched and fixed, and the square hole module is correspondingly matched with the frame, so that the cooperation between the various components of the fairing device is more closely and stably, and the aerodynamic performance and reliability of the fairing device are improved. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor.

[0023] Figure 1 The installation method flowchart of the present application; DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present application will be described clearly and completely in the following with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some embodiments of the present application, not all. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0025] Embodiment:

[0026] As shown in the drawings, Figure 1 A fairing device preparation and installation method for an aircraft, the method comprising the following steps:

[0027] Outer frame processing:

[0028] The length of the circumference is controlled by the inner ring roller circle, and then the diameter of the ring is regulated. The middle stand is cut by water cutting, and a hollow ring with a size of φ4320X400 is directly cut out for basic processing. The roundness error of the outer frame is adjusted to be less than or equal to 6mm, and the guide surface of the outer frame is set to be axially parallel to the guide surface of the frame. The flatness of the guide groove of the outer frame and the frame is adjusted to be less than or equal to 0.1.

[0029] Frame processing:

[0030] The stand is fixed on the welding steel platform by a tool, and a T-shaped frame is welded. After straightening, annealing is performed. After annealing, the workpiece is placed horizontally, and the steel plate is faced. The dust screen mounting surface is machined by numerical control gantry milling once, and the mounting surface is made to have a flatness of 0.12mm.

[0031] Square hole module processing:

[0032] The square hole module is composed of a module outer frame, a vertical partition, a horizontal partition, a partition, and an arc plate. The thickness of the square hole module outer frame stand is 5mm. The stand is cut by water cutting to the outer dimension. Four corners are connected by half-round steel pipes, welded by a welding tool, and matched by three stand bending at the combined part with the outer frame.

[0033] During installation, the dust screen module is first cut according to the size of the outer frame. The dust screen with a winding steel rod is fixed on the frame by pressing the net module and the bolt. At least two edges are fixed, and the corresponding edges are less than 2-4mm in width. The dust screen is tightened and straightened by the bolt, and the dust screen is configured according to the three-layer structure from outside to inside, i.e. coarse, fine, and coarse.

[0034] Then, the square hole module is assembled and welded. The outer frame of the square hole module is clamped by a special tool to control the deformation during welding. After welding, cooling is performed. Then, the assembly is assembled after the pressing plate is loosened. The square hole module is placed on the sliding support plate on the frame, and then assembled and welded. After welding, the weld is polished, and the assembled fairing is cleaned by compressed air and an industrial dust collector.

[0035] Firstly, the outer frame is processed. In this step, the length of the circumference is controlled by the inner ring roller circle, and then the diameter of the ring is regulated. A hollow ring with a size of φ4320X400 is directly cut out for basic processing. Then, the roundness error of the outer frame is adjusted to be less than or equal to 6mm, and the guide surface of the outer frame is set to be axially parallel to the guide surface of the frame. In addition, the flatness of the guide groove of the outer frame and the frame is adjusted to be less than or equal to 0.1.

[0036] Next, the frame is processed. In this step, the upright plate is fixed on the welded steel platform, welded into a T-shaped frame, and annealed after welding. Then, the annealed workpiece is placed horizontally, and the dust screen mounting surface is processed by numerical control gantry milling once clamped, and the mounting surface reaches a flatness of 0.12mm.

[0037] Next, the square socket module is processed. The square socket module is composed of a module outer frame, a vertical partition, a horizontal partition, a partition, and an arc plate. The thickness of the square socket module outer frame upright plate is 5mm, which is cut to the outer dimensions by water cutting. The four corners are connected by half-round steel pipes and welded by welding fixtures. In the combined part with the outer frame, three upright plate bends are matched.

[0038] After the above three steps are completed, the installation begins. First, the dust screen module is cut according to the outer frame size, and the wound steel rod dust screen is fixed on the frame by pressing the screen module and bolts. At least two edges are fixed, and the corresponding edges are less than 2-4mm in width, and the dust screen is tightened by bolts. Then, the dust screen is configured according to the three-layer structure of coarse, fine, and coarse from outside to inside.

[0039] Next, the square socket module is assembled and welded. Through special fixtures, the square socket module outer frame is clamped, and the welding process deformation is controlled. After welding is completed, cooling is performed, and then the pressure plate is loosened for assembly. The square socket module is placed on the sliding support plate on the frame, and then assembled and welded. After welding is completed, the weld is polished, and the assembled fairing is cleaned by compressed air and industrial dust collector.

[0040] The method is a preparation and installation method for a fairing device of an aircraft, including outer frame processing, frame processing, square socket module processing, and installation steps. Through these steps, a fairing device for an aircraft can be prepared and installed for the streamlined design of the aircraft and the reduction of air resistance. The method has high accuracy and reliability, and can provide an effective solution for the preparation of the fairing device of the aircraft.

[0041] The horizontal partition and vertical partition of the square socket module have the same structure and are perpendicular to each other. The horizontal partition and vertical partition are processed with a 3mm thin wall plate to fit together, and the horizontal partition and vertical partition are provided with several Chinese character type cross sections on one side of the end face connected with the partition. This square socket module is composed of horizontal partitions and vertical partitions. The structure of the two partitions is the same, and they are perpendicular to each other, forming four walls of the square socket. The horizontal partition and vertical partition are processed with a 3mm thin wall plate to fit together, which means that the two partitions are connected together by a fitting method. On one side of the end face connected with the partition, several Chinese character type cross sections are provided. These Chinese character type cross sections may be used to enhance the connection strength of the partition.

[0042] The U-shaped section is folded by a bending machine to form the transverse partition plate and the vertical partition plate, and is slotted by a special tool. The folding of the transverse partition plate and the vertical partition plate by the bending machine refers to the process of using the bending machine to fold the plate into a U-shaped shape during the manufacture of the transverse partition plate and the vertical partition plate.

[0043] The slotted is performed by using a special tool. The special tool refers to a tool or equipment specially used for processing the U-shaped section, and the slotted refers to the further processing of the transverse partition plate and the vertical partition plate after being folded to form the U-shaped section.

[0044] When slotted, a special tool for milling a 2.2mm wide groove is made, the flatness of the flat surface on the tool is 0.02mm, the starting positioning surface is perpendicular to the length direction, and according to the length of the partition plate, 3-4 equal height blocks are fixed on the upper surface, and after the partition plate is fixed, the reference vertical surface is close to the starting positioning surface. First, a special tool for milling a 2.2mm wide groove is needed. This tool needs to fix 3-4 equal height blocks on the upper surface, and the height of these equal height blocks needs to be equal to ensure the accuracy and consistency of the processing. Before fixing the partition plate, the reference vertical surface needs to be close to the starting positioning surface, which is perpendicular to the length direction. This is to ensure the accuracy and accuracy of the processing, so that there is no deviation in the processing process. After fixing the partition plate, the reference vertical surface is close to the starting positioning surface, and the flatness of the upper surface of the tool is ground to 0.02mm accuracy by grinding. This high accuracy requires the use of high-precision grinding tools and processes to achieve. The process of making a special tool includes grinding flatness, fixing equal height blocks, and close to the starting positioning surface, etc. to ensure the accuracy of the processing.

[0045] The above only describes the preferred embodiments of the present application and does not limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A method for fabricating and installing a rectifier for an aircraft, characterized in that, The method includes the following steps: Outer frame processing: The circumference is controlled by the inner ring roller, thereby adjusting the diameter of the ring. The middle vertical plate is cut by water jet cutting to directly cut out a hollow ring part with a size of φ4320X400 for basic processing. The roundness error of the outer frame is adjusted to ≤6mm, and the guide surface of the outer frame is set to be axially parallel to the guide surface of the frame. The flatness of the guide groove of the outer frame and the frame is adjusted to ≤0.

1. Frame fabrication: The upright plate is fixed to the welding steel platform with tooling and welded into a T-shaped frame. After welding, it is straightened and then annealed to eliminate stress. After annealing, the workpiece is placed horizontally with the steel plate facing up. The dustproof net mounting surface is machined on the workpiece in one clamping operation using a CNC gantry milling machine, and the mounting surface achieves a flatness of 0.12mm. Square socket module processing: The square socket module consists of a module outer frame, vertical partitions, horizontal partitions, partitions and arched plates. The thickness of the vertical plate of the square socket module outer frame is 5mm. The vertical plate is cut to the external dimensions by water jet cutting. The four corners are connected by semi-circular steel pipes and welded using welding fixtures. The connection with the outer frame is achieved by bending three vertical plates. During installation, first cut the dustproof net module according to the outer frame size. Then, fix the dustproof net with the wrapped steel rod on at least two sides of the frame using the pressing module and bolts. The corresponding sides should be 2-4mm narrower than the frame. Tighten and straighten the dustproof net with bolts. Configure the dustproof net in a three-layer structure from the outside to the inside: coarse, fine, coarse. The square housing module is then welded together. Using specialized tooling, the outer frame of the square housing module is clamped to control deformation during the welding process. After welding, it is cooled, and then the pressure plate is released before assembly. The square housing module is placed on the sliding tray on the frame and then assembled and welded. After welding, the weld seam is ground, and the assembled fairing is cleaned with compressed air and an industrial vacuum cleaner.

2. The method for manufacturing and installing a rectifier device for an aircraft as described in claim 1, characterized in that, The horizontal and vertical partitions of the square cavity module have the same structure and are set perpendicular to each other. The horizontal and vertical partitions are made of 3mm thin-walled plates and are connected together. The horizontal and vertical partitions are provided with a Z-shaped cross section on the end face of the connection between the partitions.

3. The method for manufacturing and installing a rectifier for an aircraft as described in claim 2, characterized in that, The zigzag cross section is formed by folding the horizontal and vertical partitions using a bending machine, and then slotted using a special tooling.

4. The method for manufacturing and installing a rectifier device for an aircraft as described in claim 3, characterized in that, When slotting, a special tooling is made to mill a 2.2mm wide groove. The flatness of the surface of the tooling is ground to 0.02mm. The starting positioning surface is perpendicular to the length direction. According to the length of the partition, 3-4 equal height blocks are fixed on the upper surface. After the partition is fixed, it is pressed against the starting positioning surface through the reference elevation.

Images