Forming tool for aircraft skin

Abstract

The utility model discloses an aircraft skin forming tool which comprises a supporting frame, a shaping face is arranged on the upper surface of the supporting frame, the shaping face is of an inwards-sunken curved surface structure, a plurality of fixing assemblies are arranged on a structural framework and located above the shaping face, and the fixing assemblies are used for fixing an aircraft skin. A plurality of limiting assemblies are arranged on the shaping surface, are movably connected with the shaping surface, and are used for supporting a window structure on the aircraft skin; according to the utility model, the shaping surface, the fixing component and the limiting component are arranged on the support frame, the shaping surface can support the aircraft skin, the fixing component fixes the aircraft skin, and the limiting component is arranged on the shaping surface and can be adjusted left and right, so that the spacing between windows on the aircraft skin can be adapted; the aircraft skin is fixed and supported through cooperation of the shaping face, the fixing assembly and the limiting assembly, subsequent heating and shaping are facilitated, and meanwhile, the window structure of the aircraft skin can be prevented from deforming in the heating process.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft skin processing, and particularly relates to a forming tooling for an aircraft skin. Background Art

[0002] During the aircraft processing and assembly process, in order to avoid excessive splicing points on the aircraft skin, the processing of the aircraft skin tends to be integrally formed. Especially in the production process of large airliner skins, due to their large volume and several windows provided on the skin, the windows need to be supported during the processing. After the bonded aircraft skin is fixed and pressed, the fixing device and the aircraft skin are sent into a heating furnace for heat setting. Since the window positions of the aircraft skin are relatively thin, deformation is likely to occur during the heating process. Therefore, it is necessary to provide support under the window structure of the aircraft skin to prevent heating deformation. The traditional aircraft skin processing device has a fixed structure and can only be applicable to aircraft skins with fixed window structures. Its window support structure cannot be adjusted according to the positional relationship of the windows, and the applicable range is narrow. Summary of the Utility Model

[0003] The purpose of the utility model is to provide a forming tooling for an aircraft skin. By setting a shaping surface, a fixing component and a limiting component on a support frame, the shaping surface can support the aircraft skin, the fixing component fixes the aircraft skin, the limiting component is adjustable and can adapt to the spacing of the windows on the aircraft skin. The shaping surface, the fixing component and the limiting component cooperate to fix and support the aircraft skin, facilitating subsequent heat setting.

[0004] The utility model is realized by the following technical solutions:

[0005] A forming tooling for an aircraft skin, comprising a support frame. A shaping surface is arranged on the upper surface of the support frame. The shaping surface is a curved surface structure that is concave inward. A plurality of fixing components are arranged above the shaping surface on the support frame. The fixing components are used to fix the aircraft skin. A plurality of limiting components are arranged on the shaping surface. The limiting components are movably connected to the shaping surface. The limiting components are used to support the window structure on the aircraft skin.

[0006] Further, the fixing component includes a support rod, a support beam, a fixing pin and a pressing plate. The support rod is arranged on one side edge of the support frame. The support rod is fixedly connected to the support frame. The support beam is hinged to the support rod. The fixing pin is arranged at the other end of the support beam. The fixing pin passes through the support beam and is threadedly connected to the support frame. The pressing plate is arranged in the middle of the support beam and faces the shaping surface.

[0007] Further, the bottom edge of the pressing plate is matched with the shaping surface. There are three relief grooves provided on the pressing plate, and the three relief grooves are spaced apart from each other. A honeycomb beam is provided on the aircraft skin, and the relief grooves are used to provide clearance for the honeycomb beam.

[0008] Further, the limiting component includes a first limiting member and a second limiting member. The first limiting member is arranged above the second limiting member. The size of the first limiting member is smaller than that of the second limiting member. The first limiting member and the second limiting member are connected by a fixing bolt. An adjusting groove is provided on the shaping surface, and the fixing bolt passes through the first limiting member and the second limiting member and is connected to the adjusting groove.

[0009] Further, positioning pins are arranged on both the left and right sides of the adjusting groove on the shaping surface. The two positioning pins are on the same axis. Waist-shaped holes are correspondingly arranged on the left and right sides of the fixing bolt on the first limiting member and the second limiting member, and the waist-shaped holes are matched with the positioning pins.

[0010] Further, hoisting members are arranged on both the left and right sides of the support frame. Through holes are provided on the hoisting members, and the hoisting members are used for hoisting the support frame.

[0011] Compared with the prior art, the present utility model has the following advantages and beneficial effects:

[0012] In the present utility model, a shaping surface, a fixing component and a limiting component are arranged on the support frame. The shaping surface can support the aircraft skin, the fixing component fixes the aircraft skin, and the limiting component is arranged on the shaping surface and can be adjusted left and right, so as to adapt to the distance between the windows on the aircraft skin. The aircraft skin is fixed and supported through the cooperation of the shaping surface, the fixing component and the limiting component, which is convenient for subsequent heat setting, and at the same time can prevent the window structure of the aircraft skin from deforming during the heating process. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the following will briefly introduce the drawings in the embodiments. It should be understood that the following drawings only show some embodiments of the present utility model, and thus should not be regarded as limiting the scope. For those of ordinary skill in the art, other related drawings can be obtained based on these drawings without creative efforts.

[0014] Figure 1 It is a schematic structural diagram of the forming tooling for the aircraft skin of the present utility model.

[0015] Figure 2 It is Figure 1 a schematic diagram of the structure at A in

[0016] Figure 3 It is a side view of the forming tooling for the aircraft skin of the present utility model.

[0017] Figure 4 This is a schematic structural diagram of the aircraft skin in the present utility model.

[0018] Among them: 1 - support frame, 2 - shaping surface, 3 - fixing component, 31 - support rod, 32 - support beam, 33 - fixing pin, 34 - pressing plate, 4 - limiting component, 41 - first limiting member, 42 - second limiting member, 43 - kidney-shaped hole, 44 - fixing bolt, 5 - positioning pin, 6 - lifting member, 7 - aircraft skin. Specific implementation mode

[0019] To make the objectives, technical solutions, and advantages of the embodiments of the present utility model clearer, the technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are some, but not all, of the embodiments of the present utility model.

[0020] Embodiment 1:

[0021] The main structure of this embodiment is a forming tooling for an aircraft skin. As shown in Figure 1 , Figure 3 and Figure 4 , it includes a support frame 1. The support frame 1 is a rectangular steel structure framework. A shaping surface 2 is provided on the upper surface of the support frame 1. The shaping surface 2 is a curved surface structure that is recessed inward, so as to adapt to the curved surface structure of the aircraft skin 7. The shaping surface 2 is used to support the aircraft skin 7, and the aircraft skin 7 is attached to the shaping surface 2. A number of fixing components 3 are provided above the shaping surface 2 on the structure framework. The fixing components 3 are movably connected to the structure framework. The fixing components 3 are used to fix the aircraft skin 7 and press the aircraft skin 7 on the shaping surface 2. At the same time, a plurality of limiting components 4 are also provided on the shaping surface 2. The limiting components 4 are arranged at intervals. The limiting components 4 are movably connected to the shaping surface 2. The limiting components 4 can be adjusted left and right on the shaping surface 2. The limiting components 4 are used to support the window structure on the aircraft skin 7 and prevent the window structure of the aircraft skin 7 from deforming during the heating and shaping process. Lifting members 6 are provided on both the left and right sides of the support frame 1. Through holes are provided on the lifting members 6. The lifting members 6 are used for lifting the support frame 1. When heating the aircraft skin 7, it is necessary to put the support frame 1 and the aircraft skin 7 into the heating furnace for heating together. Usually, a lifting mechanism is connected to the lifting member 6 of the support frame 1 to send the support frame 1 and the aircraft skin 7 into the heating furnace for heating together.

[0022] The fixing component 3 includes a support rod 31, a support beam 32, a fixing pin 33 and a pressing plate 34. The support rod 31 is arranged on one side edge of the support frame 1, and the support rod 31 is fixedly connected with the support frame 1, usually fixed by welding. The support beam 32 is hinged to the support rod 31, and the support beam 32 can rotate on the support rod 31. The fixing pin 33 is arranged at the other end of the support beam 32, and the fixing pin 33 passes through the support beam 32 and is threadedly connected with the support frame 1. Rotating the fixing pin 33 can fix the support beam 32 on the support frame 1, so that the pressing plate 34 below the support beam 32 presses the aircraft skin 7 tightly; the pressing plate 34 is arranged in the middle of the support beam 32 and faces the shaping surface 2; the bottom edge of the pressing plate 34 cooperates with the shaping surface 2, the bottom edge of the pressing plate 34 is a convex curved surface structure, and there are three relief grooves arranged at the bottom edge position of the pressing plate 34, and the three relief grooves are arranged at intervals. At the same time, a honeycomb beam is arranged on the aircraft skin 7, and the honeycomb beam supports the aircraft skin 7 and prevents deformation, and the relief groove cooperates with the honeycomb beam to make way for the honeycomb beam. Other parts of this embodiment are the same as those of the above embodiment, and will not be described in detail here.

[0023] Embodiment 2:

[0024] On the basis of the above embodiment, this embodiment further defines the limiting component 4, as Figure 2 shown. The limiting component 4 includes a first limiting member 41 and a second limiting member 42. The first limiting member 41 is arranged above the second limiting member 42, and the size of the first limiting member 41 is smaller than that of the second limiting member 42. The first limiting member 41 and the second limiting member 42 cooperate with the window stepped structure of the aircraft skin 7 to support and position it. The first limiting member 41 and the second limiting member 42 are connected by a fixing bolt 44. An adjustment groove is arranged on the shaping surface 2, and the fixing bolt 44 passes through the first limiting member 41 and the second limiting member 42 and is connected with the adjustment groove to fix the first limiting member 41 and the second limiting member 42 on the shaping surface 2; positioning pins 5 are arranged on both the left and right sides of the adjustment groove on the shaping surface 2, and the two positioning pins 5 are on the same axis. Waist-shaped holes 43 are correspondingly arranged on the left and right sides of the fixing bolt 44 on the first limiting member 41 and the second limiting member 42, and the waist-shaped holes 43 of the first limiting member 41 and the second limiting member 42 coincide with each other. The positioning pin 5 passes through the waist-shaped holes 43 on the second limiting member 42 and the first limiting member 41 in sequence to limit the first limiting member 41 and the second limiting member 42. After loosening the fixing bolt 44, the first limiting member 41 and the second limiting member 42 can be adjusted left and right within the range of the waist-shaped holes 43 along the direction of the adjustment groove to adapt to the window frame structures with different spacings on the aircraft skin 7. Other parts of this embodiment are the same as those of the above embodiment, and will not be described in detail here.

[0025] In the description of the present utility model, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the present utility model is customarily placed during use. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present utility model.

[0026] In addition, when the terms "horizontal" and "vertical" appear in the description of the present utility model, it does not mean that the components are required to be absolutely horizontal or hanging vertically, but they can be slightly inclined. For example, "horizontal" only means that its direction is more horizontal relative to "vertical", and it does not mean that the structure must be completely horizontal, but it can be slightly inclined.

[0027] In the description of the present utility model, it should also be noted that unless otherwise clearly specified and defined, if the terms "set", "installed", "connected", "connected" are understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific situations.

[0028] The above is only a preferred embodiment of the present utility model, and does not impose any form of limitation on the present utility model. Any simple modification and equivalent change made to the above embodiments based on the technical essence of the present utility model all fall within the protection scope of the present utility model.

Claims

1. A forming tool for aircraft skin, characterized in that: It comprises a support frame, the upper surface of which is provided with a shaping surface, the shaping surface is an inwardly concave curved surface structure, the support frame is provided with a plurality of fixing components above the shaping surface, the fixing components are used to fix the aircraft skin; the shaping surface is provided with a plurality of limiting components, the limiting components are movably connected with the shaping surface, and the limiting components are used to support the window structure on the aircraft skin.

2. The aircraft skin forming tool as claimed in claim 1, characterized in that: The fixing assembly includes a support rod, a support beam, a fixing pin and a pressure plate, the support rod is arranged on one side edge of the support frame, the support rod is fixedly connected to the support rod, the support beam is hinged to the support frame, the fixing pin is arranged at the other end of the support beam, the fixing pin passes through the support beam and is threadedly connected to the support frame, and the pressure plate is arranged in the middle of the support beam and facing the forming surface.

3. The aircraft skin forming tool as claimed in claim 2, characterized in that: The bottom edge of the pressure plate matches the shaping surface, and three clearance grooves are arranged on the pressure plate. The three clearance grooves are arranged at intervals. A honeycomb beam is arranged on the aircraft skin, and the clearance grooves are used to make way for the honeycomb beam.

4. The aircraft skin forming tool as claimed in claim 1, characterized in that: The limit assembly includes a first limit member and a second limit member, the first limit member is arranged above the second limit member, the size of the first limit member is smaller than the second limit member, the first limit member and the second limit member are connected by a fixing bolt, an adjustment groove is arranged on the shaping surface, and the fixing bolt passes through the first limit member and the second limit member and is connected to the adjustment groove.

5. The aircraft skin forming tool as claimed in claim 4, characterized in that: Positioning pins are arranged on the left and right sides of the adjusting groove on the shaping surface, and the two positioning pins are located on the same axis. Waist-shaped holes are correspondingly arranged on the left and right sides of the fixing bolt on the first limiting member and the second limiting member, and the waist-shaped holes cooperate with the positioning pins.

6. The aircraft skin forming tool as claimed in claim 1, characterized in that: The left and right sides of the support frame are both provided with hanging parts, and the hanging parts are provided with through holes, and the hanging parts are used for hanging the support frame.

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