Civil aircraft and fuselage and wing connecting method thereof

Abstract

The invention belongs to the technical field of aircraft manufacturing, and discloses a civil aircraft and a fuselage and wing connecting method thereof.The civil aircraft comprises a fuselage and wings, the fuselage comprises a general curved surface and a connecting area, and the connecting area is an area where the fuselage and the wings are connected and comprises a plane shape correction area, a front transition area, a rear transition area and a wing rib positioning surface; one side of the plane modification area in the width direction is tangent to the general curved surface, the other side of the plane modification area is connected with the wing rib positioning surface, the front transition area is connected with the front side of the plane modification area and the general curved surface, the rear transition area is connected with the rear side of the plane modification area and the general curved surface, and the plane modification area and the wing rib positioning surface are planes. The front transition area and the rear transition area are both curved surfaces, and the wings are connected with the connecting area in an attached mode. According to the civil aircraft, the aircraft body and the wings can be stably connected, when a worker fixes the boundaries of the aircraft body and the wings, the operation space is not further limited, and the connecting difficulty of the wings and the aircraft body is low.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft manufacturing, and in particular to a civil aircraft and a method for connecting a fuselage and wings thereof. Background Art

[0002] The aerodynamic layout of existing civil aircraft is a conventional aerodynamic layout, which mainly includes a cylindrical fuselage for carrying people and cargo, and wings installed in the middle section of the fuselage. Among them, the wings are used to generate lift and lateral control. The structure of the connection between the wings and the fuselage in existing civil aircraft is designed according to the structure of the fuselage so that the fuselage and the wings can be connected in a snug fit. Since the fuselage is a cylindrical structure, the fuselage and the wings are connected by two curved surfaces. The connection method of the two curved surfaces makes the connection structure unstable in areas with larger curvature. There is an angle between the wing and the fuselage of a civil aircraft. When the staff fix the boundary between the fuselage and the wing, the operating space will be limited by the angle. Due to the cylindrical structure of the fuselage, the operating space will be further reduced, resulting in difficulties in connecting the fuselage and the wing of existing civil aircraft.

[0003] Therefore, there is an urgent need for a civil aircraft and a method for connecting its fuselage and wings to solve the above technical problems. Summary of the Invention

[0004] The first purpose of the present invention is to provide a civil aircraft in which the fuselage and wings can be firmly connected, and the operating space of the staff will not be restricted when fixing the boundary between the fuselage and the wings, thereby reducing the difficulty of connecting the wings and the fuselage.

[0005] To achieve this object, the present invention adopts the following technical solutions:

[0006] A civil aircraft comprising:

[0007] A fuselage and a wing, wherein the fuselage includes a general curved surface and a connection area, the connection area is the area where the fuselage is connected to the wing, the connection area includes a plane shaping area, a front transition area, a rear transition area and a wing rib station surface, the plane shaping area is tangent to the general curved surface on one side along the width direction, and is connected to the wing rib station surface on the other side along the width direction, the front transition area is used to connect the front edge of the plane shaping area and the general curved surface, the rear transition area is used to connect the rear edge of the plane shaping area and the general curved surface, the plane shaping area and the wing rib station surface are both planar structures, the front transition area and the rear transition area are both curved surface structures, and the wing is fit-connected to the connection area.

[0008] As a preferred technical solution for civil aircraft, the plane where the plane shaping area is located is parallel to or at an angle to the symmetry plane of the civil aircraft.

[0009] As the preferred technical scheme of the civil aircraft, the front transition region and the rear transition region are both hyperbolic surface structures.

[0010] As the preferred technical scheme of the civil aircraft, the front transition region and the rear transition region are both tangent to the general curved surface.

[0011] As the preferred technical scheme of the civil aircraft, the front transition region and the rear transition region are both tangent to the planar fairing region.

[0012] As the preferred technical scheme of the civil aircraft, the front transition region is filled with a single curved surface or a hyperbolic surface;

[0013] The rear transition region is filled with a single curved surface or a hyperbolic surface.

[0014] As the preferred technical scheme of the civil aircraft, the plane where the wing rib station surface is located is parallel to the symmetry plane of the fuselage or forms a certain angle.

[0015] As the preferred technical scheme of the civil aircraft, the planar fairing region includes four boundary lines, namely a line, a b line, a c line and a d line, the planar fairing region and the general curved surface are tangent to the a line, the planar fairing region and the front transition region are tangent to the b line, the planar fairing region and the rear transition region are tangent to the c line, the planar fairing region and the wing rib station surface are tangent to the d line, and the upper boundary lines where the front transition region and the rear transition region are tangent to the general curved surface are both the extension lines of the a line.

[0016] The second object of the present application is to provide a method for connecting the fuselage and the wing of a civil aircraft, and for achieving the object, the present application adopts the following technical scheme:

[0017] A method for connecting the fuselage and the wing of a civil aircraft is suitable for the civil aircraft described in any one of the preceding embodiments, and the method for connecting the fuselage and the wing of the civil aircraft comprises the following steps:

[0018] A connecting area is arranged on the fuselage, and the connecting area is distributed into a planar fairing region, a front transition region, a rear transition region and a wing rib station surface;

[0019] The planar fairing region and the wing rib station surface are designed as planes, and the front transition region and the rear transition region are designed as curved surfaces;

[0020] The structure of the wing connected to the surface of the fuselage is designed according to the structure of the connecting area, so that the wing and the connecting area can be connected in close contact.

[0021] As the preferred technical scheme of the fuselage and wing connection method of the civil aircraft, one boundary of the planar modified area along the width direction is tangent to the general curved surface, the other boundary along the width direction is coplanar or at an angle with the wing rib standing surface, the planar modified area is divided into a front boundary and a rear boundary along the length direction, the front boundary is tangent to the front transition area, the rear boundary is tangent to the rear transition area, and the front boundary is close to the nose.

[0022] The beneficial effects of the present application are:

[0023] The civil aircraft provided by the present application has the following advantages: the planar modified area and the wing rib standing surface are designed as planar structures, the intermediate area of the fuselage and wing connection is planarly attached, the planar attachment connection mode does not have a large-curvature connection surface compared with the existing curved attachment connection mode, and the fuselage and wing can be stably connected, so that the safety of the civil aircraft is further improved; the front transition area and the rear transition area are both designed as curved structures, so that the front and rear boundaries of the planar modified area are connected to the general curved surface through curved transition, that is, the two side areas of the fuselage and wing connection are designed as small-arc curved surfaces, so that the pressure difference resistance and friction resistance of the civil aircraft during flight can be avoided, and the stability of the civil aircraft during flight can be ensured; the front transition area and the rear transition area enable the planar modified area to be connected to the general curved surface through small-arc curved transition, compared with the existing overall cylindrical structure of the fuselage, the curved arc of the fuselage can be further reduced, and a certain operation space at the junction of the fuselage and wing is released, so that the staff can relatively more easily fix the two side positions of the fuselage and wing. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 is a structure diagram of the connection area and the general curved surface of the civil aircraft provided by the present application;

[0025] Figure 2 is a flowchart of the fuselage and wing connection method of the civil aircraft provided by the present application.

[0026] In the drawings:

[0027] 10, general curved surface; 11, connection area;

[0028] 111, planar modified area; 1111, a line; 1112, b line; 1113, c line; 1114, d line; 112, front transition area; 113, rear transition area; 114, wing rib standing surface. DETAILED DESCRIPTION

[0029] The application will be further described below in conjunction with the drawings and embodiments. It is to be understood that the specific embodiments described herein are intended to be illustrative only and not limiting of the scope of the application. In addition, it is to be understood that where the description above refers to embodiments, it is not necessary that all of the described embodiments actually be present. Rather, description "wherein" features are present is intended to cover each individual implementation of the described feature.

[0030] In the description of the application, unless otherwise clearly specified and limited, the terms "connected", "connected", "fixed" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the application can be understood according to the specific circumstances.

[0031] In the present application, unless otherwise clearly specified and limited, the "upper" or "lower" of the first feature to the second feature can include the direct contact of the first and second features, or the indirect contact of the first and second features through another feature between them. Moreover, the "upper", "above" and "above" of the first feature to the second feature includes the vertical direction of the first feature above and oblique above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The "below", "below" and "below" of the first feature to the second feature includes the vertical direction of the first feature below and oblique below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0032] In the description of the present embodiment, the terms "upper", "lower", "right", and the like orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the application. In addition, the terms "first", "second" are only used to distinguish in the description, and have no special meaning.

[0033] Embodiment one

[0034] As Figure 1As shown in the figure, the embodiment provides a civil aircraft, which comprises a fuselage and a wing. The fuselage comprises a general curved surface 10 and a connecting area 11. The connecting area 11 is a connecting position of the fuselage and the wing. The connecting area 11 comprises a planar modified area 111, a front transition area 112, a rear transition area 113 and a wing rib station surface 114. One side of the planar modified area 111 along the width direction is tangent to the general curved surface 10, and the other side of the planar modified area 111 along the width direction is connected to the wing rib station surface 114. The front transition area 112 is used to connect the front side of the planar modified area 111 and the general curved surface 10. The rear transition area 113 is used to connect the rear side of the planar modified area 111 and the general curved surface 10. The front side of the planar modified area 111 refers to the side of the planar modified area 111 close to the nose, and the rear side of the planar modified area 111 refers to the side away from the nose. The planar modified area 111 and the wing rib station surface 114 are both planar structures, the front transition area 112 and the rear transition area 113 are both curved surface structures, and the wing is connected to the connecting area 11 in a fit manner. The heading direction is the direction from the tail to the nose of the fuselage.

[0035] By designing the planar modified area 111 and the wing rib station surface 114 as planar structures, the middle area of the connection between the fuselage and the wing is planar fit. The planar fit connection method does not have a large curvature connecting surface compared with the existing curved surface fit connection method, realizes stable connection between the fuselage and the wing, and further improves the safety of the civil aircraft. By designing the front transition area 112 and the rear transition area 113 as curved surface structures, the front side and the rear side of the planar modified area 111 are connected to the general curved surface 10 in a curved surface transition manner, that is, the two side areas of the connection between the fuselage and the wing are designed as small-radian curved surfaces, which can avoid increasing the pressure difference resistance and friction resistance of the civil aircraft during flight, and ensure the stability of the civil aircraft during the process. The front transition area 112 and the rear transition area 113 realize that the planar modified area 111 can be connected to the general curved surface 10 in a small-radian curved surface transition manner. Compared with the existing overall cylindrical structure of the fuselage, the curved surface radius of the fuselage can be further reduced, and the operation space at the intersection between the fuselage and the wing is released, so that the staff can relatively more easily fix the two side positions of the fuselage and the wing.

[0036] In the embodiment, the plane where the planar modified area 111 is located is parallel to or at an angle to the symmetry plane of the civil aircraft. The symmetry plane of the civil aircraft refers to the plane determined by the center of gravity of the civil aircraft as the origin and the longitudinal axis and the transverse axis. In this way, the area of the wing covered or shielded by the fuselage can be reduced, the wing can be exposed to a larger surface area, the resistance of the airflow interference at the intersection between the fuselage and the wing of the civil aircraft can be reduced, and the flight of the civil aircraft is more stable. At the same time, the wing is exposed to a larger surface area, and the operation space of the staff is increased, which can reduce the difficulty of the staff in repairing and maintaining the civil aircraft.

[0037] In the embodiment, the front transition region 112 and the rear transition region 113 are both hyperbolic surface structures, which not only make the fuselage more conform to the air flow, reduce the pressure difference resistance and friction resistance of the civil aircraft during flight, and improve the fuel efficiency of the civil aircraft. It can also improve the lift distribution of the fuselage and optimize the airflow around the fuselage, further improving the stability of the aircraft in flight. The hyperbolic surface structure can also enable the civil aircraft to cope with the changing aerodynamic load during flight.

[0038] Further, the front transition region 112 and the rear transition region 113 are tangent to the general surface 10, so that the front transition region 112 and the rear transition region 113 can be more smoothly transitioned at the connection with the general surface 10. At the same time, the front transition region 112 and the rear transition region 113 are tangent to the planar shaping region 111, so that the front transition region 112 and the rear transition region 113 can be more smoothly transitioned at the connection with the planar shaping region 111. In this way, the fuselage can be more conform to the air flow, further reducing the pressure difference resistance and friction resistance of the aircraft during flight, and improving the fuel efficiency of the civil aircraft.

[0039] In the embodiment, the front transition region 112 is filled with a single curved surface or a hyperbolic surface. At the same time, the rear transition region 113 is also filled with a single curved surface or a hyperbolic surface. The single curved surface has a simple machining process, relatively low processing cost and is easy to maintain. The single curved surface is a curved surface that bends in only one direction, and the single curved surface structure can effectively transmit axial load, such as the air pressure load of the fuselage, to ensure the service life of the fuselage. The hyperbolic surface is a curved surface that bends in two directions, and the hyperbolic surface structure has superior aerodynamic performance, which can optimize the local flow of the fuselage and improve the stability of the civil aircraft during flight. The hyperbolic surface structure can also disperse the stress on the fuselage, reduce the use of reinforcing members, and reduce the processing difficulty of the civil aircraft while ensuring the service life of the fuselage. As for the front transition region 112 and the rear transition region 113, either a single curved surface or a hyperbolic surface can be selected, and the specific selection can be based on the specifications of the civil aircraft, which is not limited here.

[0040] In the embodiment, the plane on which the wing rib station surface 114 is located is parallel to the symmetry plane of the fuselage or is set at a certain angle. In this way, when designing the wing, the installation angle of the first rib in the wing and the lower wall plate of the wing can be increased, thereby facilitating the assembly of the wing and the fuselage and reducing the assembly difficulty of the civil aircraft. In the embodiment, the first rib is the first wing rib close to the fuselage.

[0041] In this embodiment, the plane modification area 111 includes four boundary lines, namely, line a 1111, line b 1112, line c 1113, and line d 1114. The plane modification area 111 and the general curved surface 10 are tangent to each other at line a 1111, so that the plane modification area 111 and the general curved surface 10 are tangent to each other. The plane modification area 111 and the front transition area 112 are tangent to each other at line b 1112. The plane modification area 111 and the rear transition area 113 are tangent to each other at line c 1113, so that the plane modification area 111 and the front transition area 112 and the rear transition area 113 are tangent to each other. The plane modification area 111 and the wing rib station surface 114 are tangent to each other at line d 1114, so that the plane modification area 111 and the wing rib station surface 114 are tangent to each other. Furthermore, the upper boundary lines of the front transition region 112 and the rear transition region 113, where they are tangent to the general curved surface 10, are both extensions of line a 1111. This further ensures that the front transition region 112 smoothly connects to the front boundary of the plane-modified region 111 and the general curved surface 10, and that the rear transition region 113 smoothly connects to the rear boundary of the plane-modified region 111 and the general curved surface 10. Furthermore, the upper boundary lines of the front transition region 112 and the rear transition region 113 do not need to be set separately, which reduces the difficulty of machining the fuselage mid-connection area 11, reduces the number of welds on the fuselage, and improves the overall strength of the fuselage.

[0042] Example 2

[0043] like Figure 2 As shown, this embodiment provides a method for connecting the fuselage and wings of a civil aircraft, which is applicable to the civil aircraft in Example 1. The method for connecting the fuselage and wings of a civil aircraft includes the following steps:

[0044] A connection area 11 is provided on the fuselage and is divided into a plane shaping area 111, a front transition area 112, a rear transition area 113, and a wing rib station surface 114. The provision of the connection area 11 on the fuselage divides the fuselage into a general curved surface 10 and the connection area 11. The connection area 11 is the area where the fuselage connects to the wing.

[0045] The plane shaping area 111 and the wing rib station surface 114 are designed to be planes, and the front transition area 112 and the rear transition area 113 are designed to be curved surfaces. The plane shaping area 111 and the wing rib station surface 114 are both planes, which can ensure a stable connection between the wing and the middle area of ​​the connection area 11. The front transition area 112 and the rear transition area 113 are both curved surfaces, which can enable both sides of the plane shaping area 111 along the length direction to be transitionally connected to the general curved surface 10 with a small curved surface, reducing the curvature of the fuselage curved surface, freeing up operating space at the angle between the fuselage and the wing, and enabling workers to connect the fuselage and the two sides of the wing relatively more easily.

[0046] According to the structural design of the connecting area 11, the structure of the wing connecting with the fuselage is designed, so that the wing and the connecting area 11 can be connected in close contact.

[0047] In the embodiment, one boundary of the planar modified area 111 along the width direction is tangent to the general curved surface 10, and the other boundary along the width direction is coplanar with or at a certain angle with the wing rib station surface 114. The planar modified area 111 is divided into a front boundary and a rear boundary along the length direction, the front boundary is tangent to the front transition area 112, and the rear boundary is tangent to the rear transition area 113, wherein the front boundary is close to the nose.

[0048] Obviously, the above embodiments of the present application are only examples for clearly illustrating the present application, and are not intended to limit the embodiments of the present application. For those skilled in the art, various obvious changes, re-adjustments and substitutions can be made without departing from the scope of the present application. Here, it is unnecessary and impossible to enumerate all the embodiments. Any modification, equivalent substitution and improvement within the spirit and principle of the present application shall be included in the protection scope of the claims of the present application.

Claims

1. A civil aircraft, characterized in that: include: A fuselage and a wing, wherein the fuselage comprises a general curved surface (10) and a connection area (11), wherein the connection area (11) is an area where the fuselage and the wing are connected, wherein the connection area (11) comprises a plane shaping area (111), a front transition area (112), a rear transition area (113) and a wing rib station surface (114), wherein one side of the plane shaping area (111) along the width direction is tangent to the general curved surface (10), and the other side along the width direction is connected to the wing rib station surface (114). The front transition region (112) is used to connect the front edge of the plane shaping region (111) and the general curved surface (10), and the rear transition region (113) is used to connect the rear edge of the plane shaping region (111) and the general curved surface (10). The plane shaping region (111) and the wing rib station surface (114) are both planar structures, and the front transition region (112) and the rear transition region (113) are both curved surface structures. The wing is fitted and connected to the connection region (11).

2. The civil aircraft according to claim 1, characterized in that: The plane where the plane shaping area (111) is located is parallel to or at an angle to the symmetry plane of the civil aircraft.

3. The civil aircraft according to claim 2, characterized in that: The front transition region (112) and the rear transition region (113) are both hyperbolic surface structures.

4. The civil aircraft according to claim 3, characterized in that: The front transition region (112) and the rear transition region (113) are both tangent to the general curved surface (10).

5. The civil aircraft according to claim 4, characterized in that: The front transition area (112) and the rear transition area (113) are both tangent to the plane shaping area (111).

6. The civil aircraft according to claim 3, characterized in that: The front transition area (112) is filled with a single curved surface or a double curved surface; The rear transition area (113) is filled with a single curved surface or a double curved surface.

7. The civil aircraft according to claim 3, characterized in that: The plane where the wing rib position surface (114) is located is parallel to or forms a certain angle with the symmetry plane of the fuselage.

8. The civil aircraft according to claim 5, characterized in that: The plane shaping region (111) includes four boundary lines, namely, line a (1111), line b (1112), line c (1113) and line d (1114); the plane shaping region (111) is tangent to the general curved surface (10) at line a (1111); the plane shaping region (111) is tangent to the front transition region (112) at line b (1112); the plane shaping region (111) is tangent to the rear transition region (113) at line c (1113); the plane shaping region (111) is tangent to the wing rib station surface (114) at line d (1114); and the upper boundary lines of the front transition region (112) and the rear transition region (113) tangent to the general curved surface (10) are both extensions of the a line (1111).

9. A method for connecting the fuselage and wings of a civil aircraft, characterized in that: Applicable to the civil aircraft according to any one of claims 1 to 8, the method for connecting the fuselage and wings of the civil aircraft comprises the following steps: A connection area (11) is provided on the fuselage, and the connection area (111) is distributed into a plane shaping area (111), a front transition area (112), a rear transition area (113) and a wing rib station surface (114); The plane shaping area (111) and the wing rib station surface (114) are designed to be planes, and the front transition area (112) and the rear transition area (113) are designed to be curved surfaces; The structure of the side of the wing connected to the fuselage is designed according to the structure of the connecting area (11), so that the wing and the connecting area (11) can be closely connected.

10. The method for connecting the fuselage and wings of a civil aircraft according to claim 9, characterized in that: One boundary of the plane shaping area (111) along the width direction is tangent to the general curved surface (10), and the other boundary along the width direction is coplanar with or forms a certain angle with the wing rib station surface (114). The plane shaping area (111) is divided into a front boundary and a rear boundary along the length direction, the front boundary is tangent to the front transition area (112), and the rear boundary is tangent to the rear transition area (113), and the front boundary is close to the nose.

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