Wing section connecting end rib and manufacturing method thereof

Abstract

The invention provides a wing section connecting end rib and a manufacturing method thereof, and relates to the technical field of end ribs of aircrafts, the wing section connecting end rib is used for connecting a first wing section and a second wing section which are adjacent, each of the first wing section and the second wing section comprises at least one wing spar, the end rib comprises two sub-end ribs, the two sub-end ribs are of a detachable symmetrical structure, and the two sub-end ribs are arranged in parallel. Each sub-end rib comprises an upper wing surface, a lower wing surface and a vertical surface, the two ends of the upper wing surface are connected with the two ends of the lower wing surface respectively, a cavity is formed between the upper wing surface and the lower wing surface, the vertical surface is arranged in the cavity and connected with one end surface of the upper wing surface and one end surface of the lower wing surface, and a connecting hole used for being connected with a spar is formed in the vertical surface; the sub-end ribs are made of carbon fiber foam sandwich plates; the problems that a traditional end rib is large in weight and inconvenient to assemble are solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft end ribs, and more specifically, relates to a wing section connecting end rib and a manufacturing method thereof. Background Art

[0002] The end rib of the drone's wing is located at the end of the wing segment, where the spanwise load of the wing is gathered. Therefore, it needs to have strong mechanical properties and is a special type of reinforced wing rib. In addition, the end rib is located at the connection between adjacent wing segments of the wing, and needs to have good connection performance.

[0003] The traditional end rib uses a wing box structure composed of an integral wall panel and upper and lower skins, which has the disadvantages of heavy weight and complicated assembly process. In addition, due to the need to avoid the connection structure of the spar in the wing section, the end ribs between two adjacent wing sections need to be connected through an additional fairing structure, which adds unnecessary weight. Summary of the invention

[0004] The purpose of the present invention is to provide a wing section connecting end rib in view of the deficiencies in the prior art, so as to solve the problem that the traditional end rib is heavy and inconvenient to assemble.

[0005] In order to achieve the above object, the present invention provides a wing segment connecting end rib, which is used for connecting adjacent first wing segments and second wing segments, wherein the first wing segment and the second wing segment respectively include at least one wing spar, and the end rib includes:

[0006] Two sub-end ribs, the two sub-end ribs are detachable symmetrical structures, the sub-end ribs include an upper wing surface, a lower wing surface and a vertical surface, the two ends of the upper wing surface are respectively connected to the two ends of the lower wing surface, a cavity is formed between the upper wing surface and the lower wing surface, the vertical surface is arranged in the cavity and connected to one end surface of the upper wing surface and the lower wing surface, and a connection hole for connecting with the spar is opened on the vertical surface;

[0007] The material of the sub-end ribs is a carbon fiber foam sandwich panel.

[0008] Optionally, the vertical surface is provided with a protrusion protruding toward the other end surface of the upper wing surface and the lower wing surface, and the connecting hole is opened on the protrusion.

[0009] Optionally, at least one of the upper wing surface and the lower wing surface is provided with a notch portion, and the notch portion is connected to an end surface of the protrusion portion. When the two sub-end ribs are connected, the two notches are connected to form an operation port.

[0010] Optionally, the wing beam includes a main beam and a rear beam arranged in sequence from front to rear, and two protrusions are arranged in sequence from front to rear on each of the facades.

[0011] Optionally, a plurality of through holes are provided on the facade, and the two sub-end ribs are fastened to each other through fasteners and the through holes.

[0012] Optionally, weight-reducing holes are provided on the facade.

[0013] Optionally, the carbon fiber foam sandwich panel comprises a first carbon fiber layer, a foam layer and a second carbon fiber layer which are arranged in sequence.

[0014] The present invention also provides a method for manufacturing a wing segment connecting end rib, which is used to manufacture the above-mentioned wing segment connecting end rib, and the method comprises:

[0015] Determine the shape and size of each sub-end rib according to the aerodynamic shape, spar and load requirements of the wing section;

[0016] The sub-end ribs of the carbon fiber foam sandwich panel material are formed by a molding process.

[0017] Optionally, according to the aerodynamic shape, spar and load requirements of the wing section, determining the shape and size of each sub-end rib includes:

[0018] Determine the shapes of the upper and lower wing surfaces according to the aerodynamic shape of the wing section;

[0019] Determine the shape and size of the connection hole according to the shape and size of the spar;

[0020] The layup design of the carbon fiber foam sandwich panel is determined according to the load requirements of the wing section.

[0021] Optionally, forming the sub-end ribs of the carbon fiber foam sandwich panel material by a molding process comprises:

[0022] The foam layer of the one-piece carbon fiber foam sandwich panel;

[0023] Obtaining a mold, wherein the mold comprises a bottom mold and a cover mold;

[0024] The first carbon fiber layer, the glue layer and the foam layer of the carbon fiber foam sandwich panel are sequentially laid in the bottom mold, and the second carbon fiber layer and the glue layer are sequentially laid in the cover mold;

[0025] The mold is tightened and cured using a press.

[0026] The present invention provides a wing section connecting end rib and a manufacturing method thereof, and the beneficial effects are: the wing section connecting end rib has two sub-end ribs of symmetrical structure, which are detachably connected to facilitate the connection of two wing sections, each sub-end rib includes an upper wing surface, a lower wing surface and a vertical surface connected in an integral manner, the structure is simple, the structural strength is good, and the wing spar can be avoided and connected to the wing spar by means of a connection hole on the vertical surface in a manner of being sleeved on the wing spar, and the sub-end rib is made of a carbon fiber foam sandwich panel material, which can achieve a good weight reduction effect while ensuring the material strength.

[0027] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0029] Figure 1 A schematic diagram of an overall connection structure of a wing section connected to a wing rib according to an embodiment of the present invention is shown.

[0030] Figure 2 Shows Figure 1 Schematic diagram of the top view structure.

[0031] Figure 3 A schematic diagram of the three-dimensional structure of a sub-end rib of a wing section connecting ribs according to an embodiment of the present invention is shown.

[0032] Figure 4 A schematic plan view of the structure of a sub-end rib of a wing section connecting ribs according to an embodiment of the present invention is shown.

[0033] Figure 5 A schematic cross-sectional view of a material for connecting a wing section to a rib according to an embodiment of the present invention is shown.

[0034] Figure 6 A flow chart of a method for manufacturing a wing section connecting a wing rib according to an embodiment of the present invention is shown.

[0035] Description of reference numerals:

[0036] 1. Sub-end rib; 2. Main beam; 3. Rear beam; 4. Upper wing surface; 5. Lower wing surface; 6. Vertical surface; 7. Connection hole; 8. Raised part; 9. Notch part; 10. Operation port; 11. Through hole; 12. Weight reduction hole; 13. First carbon fiber layer; 14. Foam layer; 15. Second carbon fiber layer. DETAILED DESCRIPTION

[0037] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0038] like Figure 1As shown, the present invention provides a wing segment connecting end rib, which is used for connecting adjacent first wing segments and second wing segments, wherein the first wing segment and the second wing segment respectively include at least one wing spar, and the end rib includes:

[0039] Two sub-end ribs 1, the two sub-end ribs 1 are detachable symmetrical structures, the sub-end rib 1 comprises an upper wing surface 4, a lower wing surface 5 and a vertical surface 6, the two ends of the upper wing surface 4 are respectively connected to the two ends of the lower wing surface 5, a cavity is formed between the upper wing surface 4 and the lower wing surface 5, the vertical surface 6 is arranged in the cavity and connected to one end surface of the upper wing surface 4 and the lower wing surface 5, and a connecting hole 7 for connecting with the spar is opened on the vertical surface 6;

[0040] The material of the sub-end rib 1 is a carbon fiber foam sandwich panel.

[0041] Specifically, in order to solve the problem that traditional end ribs are heavy and inconvenient to assemble, the wing segment connecting end rib provided by the present invention has two sub-end ribs 1 with a symmetrical structure, which can be detachably connected to facilitate the connection between the two wing segments. Each sub-end rib 1 includes an upper wing surface 4, a lower wing surface 5 and a vertical surface 6 that are connected in an integral manner. The structure is simple and the structural strength is good. The connection hole 7 on the vertical surface 6 is used to sleeve on the wing beam to achieve avoidance of the wing beam and connection with the wing beam. The sub-end rib 1 is made of carbon fiber foam sandwich panel material, which can achieve a good weight reduction effect while ensuring the strength of the material.

[0042] Furthermore, the shapes of the upper wing surface 4 and the lower wing surface 5 are determined by the aerodynamic shape of the wing section, and the outer sides of the upper wing surface 4 and the lower wing surface 5 are connected to the skin of the wing section.

[0043] Optionally, the vertical surface 6 is provided with a protrusion 8 protruding toward the other end surface of the upper wing surface 4 and the lower wing surface 5 , and the connecting hole 7 is opened on the protrusion 8 .

[0044] Specifically, the raised portion 8 on the vertical surface 6 of each sub-end rib 1 is raised from one end surface of the upper wing surface 4 and the lower wing surface 5 toward the other end surface of the upper wing surface 4 and the lower wing surface 5, so that when the two sub-end ribs 1 are connected to each other, the two vertical surfaces 6 are not in contact with each other at the position of the raised portion 8, and an operating space is formed between the two raised portions 8. The operating space can facilitate the connection of the wing beams in adjacent wing sections at this point. The operating space provided for the connection of the wing beams enables the end rib to omit the rectification structure in the traditional end rib, thereby reducing the structural weight.

[0045] Optionally, at least one of the upper wing surface 4 and the lower wing surface 5 is provided with a notch portion 9 , and the notch portion 9 is connected to one end surface of the protrusion 8 . When the two sub-end ribs 1 are connected, the two notches 9 are connected to form an operation port 10 .

[0046] Specifically, Figure 2As shown, the notch portion 9 is in a shape that is recessed from one end surface of the upper wing surface 4 and / or the lower wing surface 5 to the other end surface thereof, one edge of the notch portion 9 is open, and the other edge is connected to the end surface of the raised portion 8, and the operating port 10 formed by the two notch portions 9 forms an opening of the operating space.

[0047] Further, such as Figure 3 As shown, the number of the protrusions 8 is the same as the number of the spars in the wing section, each spar passes through a connecting hole 7, and each connecting hole 7 is arranged on a protrusion 8.

[0048] Optionally, the wing beam includes a main beam 2 and a rear beam 3 which are arranged in sequence from front to back, and two protrusions 8 are arranged in sequence from front to back on each facade 6 .

[0049] Specifically, the main beam 2 and the rear beam 3 respectively pass through a connecting hole 7 on a raised portion 8 and can be connected to the facade 6 by bonding.

[0050] Optionally, a plurality of through holes 11 are provided on the facade 6 , and the two sub-end ribs 1 are fastened and connected via fasteners and the through holes 11 .

[0051] Specifically, a plurality of through holes 11 are provided on the facade 6 of each sub-end rib 1. When two sub-end ribs 1 are connected, the two facades 6 of the two symmetrically structured sub-end ribs 1 fit in contact with each other, and fasteners are passed through the through holes 11 to achieve a fastened connection between the two sub-end ribs 1.

[0052] In this embodiment, if Figure 4 As shown, each facade 6 is provided with six through holes 11, and the fasteners include M8 bolts.

[0053] Optionally, weight-reducing holes 12 are provided on the facade 6 .

[0054] Specifically, the provision of the weight-reducing holes 12 can further reduce the weight of the end rib, thereby achieving lightweight.

[0055] Optionally, the carbon fiber foam sandwich panel includes a first carbon fiber layer 13, a foam layer 14 and a second carbon fiber layer 15 which are arranged in sequence.

[0056] Specifically, Figure 5 As shown, the first carbon fiber layer 13, the foam layer 14 and the second carbon fiber layer 15 are stacked in sequence to form a carbon fiber foam sandwich panel, the foam layer 14 is a 10 mm thick PMI foam, the first carbon fiber layer 13 and the second carbon fiber layer 15 are 1 mm thick carbon fiber fabric materials, which are laid alternately at 0° / 45°.

[0057] In summary, when the wing segment connecting end rib provided by the present invention is used:

[0058] 1) When assembling two adjacent wing sections, the two sub-end ribs 1 of the end rib are respectively bonded to the corresponding main beam 2 and rear beam 3. Tooling is required to ensure the relative position of the sub-end rib 1, the main beam 2 and the rear beam 3, so as to ensure that the wing surface and the wing beam are continuous when the two adjacent wing sections are connected;

[0059] 2) When two adjacent wing sections are assembled, the vertical surfaces 6 of the two sub-end ribs 1 are fitted together and connected and fastened using six fasteners.

[0060] 3) The joints between the main beam 2 and the rear beam 3 can be bonded and sealed with a film to prevent airflow from entering the interior of the drone during flight.

[0061] 4) When disassembling the wing section, remove the film bonding part and remove the six fasteners on the vertical surface 6 of the sub-end rib 1.

[0062] like Figure 6 As shown, the present invention also provides a method for manufacturing a wing segment connecting end rib, which is used to manufacture the above-mentioned wing segment connecting end rib, and the method comprises:

[0063] Determine the shape and size of each sub-end rib 1 according to the aerodynamic shape, spar and load requirements of the wing section;

[0064] The sub-end rib 1 of the carbon fiber foam sandwich panel material is formed by a molding process.

[0065] Optionally, according to the aerodynamic shape, spar and load requirements of the wing section, determining the shape and size of each sub-end rib 1 includes:

[0066] The shapes of the upper wing surface 4 and the lower wing surface 5 are determined according to the aerodynamic shape of the wing section;

[0067] Determine the shape and size of the connection hole 7 according to the shape and size of the spar;

[0068] The layup design of the carbon fiber foam sandwich panel is determined according to the load requirements of the wing section.

[0069] Specifically, the structural form of the upper wing surface 4 and the lower wing surface 5 of the end rib is determined according to the aerodynamic shape of the wing section of the UAV; the structural size of each protrusion 8 is determined according to the connection method and required space of the main beam 2 and the rear beam 3 between the wing sections; the structural size of the connection hole 7 on the protrusion 8 of the end rib is determined according to the shape of the main beam 2 and the rear beam 3 of the wing section; the size and distribution of the through hole 11 between the two sub-end ribs 1 are determined according to the size of the end rib and the load requirements; the ply design of each sub-end rib 1 is determined according to the load requirements of the wing section of the UAV. The sub-end rib 1 adopts carbon fiber foam sandwich panel material, and the typical ply structure is the first carbon fiber layer 13, the foam layer 14 and the second carbon fiber layer 15 arranged in sequence, the foam layer 14 adopts PMI foam, the first carbon fiber layer 13 and the second carbon fiber layer 15 adopt carbon fiber fabric material, and they are laid alternately at 0° / 45°.

[0070] Optionally, the sub-end rib 1 of the carbon fiber foam sandwich panel material is formed by a molding process and includes:

[0071] A foam layer 14 of an integrally formed carbon fiber foam sandwich panel;

[0072] Obtaining a mold, the mold comprising a bottom mold and a cover mold;

[0073] The first carbon fiber layer 13, the glue layer and the foam layer 14 of the carbon fiber foam sandwich panel are sequentially laid in the bottom mold, and the second carbon fiber layer 15 and the glue layer are sequentially laid in the cover mold;

[0074] The mold is tightened and cured using a press.

[0075] Specifically, each sub-end rib 1 adopts a molding process, and the foam layer 14 is integrally formed according to the shape and size design results of each sub-end rib 1, and then the mold is designed according to the shape and size design results of each sub-end rib 1 to obtain a mold including a bottom mold and a cover mold, and then the first carbon fiber layer 13, the glue layer and the foam layer 14 of the carbon fiber foam sandwich panel are laid in sequence in the bottom mold, and the second carbon fiber layer 15 and the glue layer are laid in sequence in the cover mold, and then the mold is closed and tightened, and then a press is used for curing. After demolding, a plurality of through holes 11 for fastening two sub-end ribs 1 can be formed on the sub-end rib 1 by machining.

[0076] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A wing segment connecting end rib, used for connecting a first wing segment and a second wing segment adjacent to each other, wherein the first wing segment and the second wing segment respectively include at least one wing spar, characterized in that: The end ribs include: Two sub-end ribs, the two sub-end ribs are detachable symmetrical structures, the sub-end ribs include an upper wing surface, a lower wing surface and a vertical surface, the two ends of the upper wing surface are respectively connected to the two ends of the lower wing surface, a cavity is formed between the upper wing surface and the lower wing surface, the vertical surface is arranged in the cavity and connected to one end surface of the upper wing surface and the lower wing surface, and a connection hole for connecting with the spar is opened on the vertical surface; The material of the sub-end ribs is a carbon fiber foam sandwich panel.

2. The wing section connecting end rib according to claim 1, characterized in that: The vertical surface is provided with a protruding portion protruding toward the other end surface of the upper wing surface and the lower wing surface, and the connecting hole is opened on the protruding portion.

3. The wing section connecting end rib according to claim 2, characterized in that: At least one of the upper wing surface and the lower wing surface is provided with a notch portion, and the notch portion is connected to an end surface of the protrusion portion. When the two sub-end ribs are connected, the two notches are connected to form an operation port.

4. The wing section connecting end rib according to claim 3, characterized in that: The wing beam includes a main beam and a rear beam which are arranged in sequence from front to back, and two protrusions are arranged in sequence from front to back on each of the facades.

5. The wing section connecting end rib according to claim 1, characterized in that: A plurality of through holes are provided on the facade, and the two sub-end ribs are fastened and connected to the through holes through fasteners.

6. The wing section connecting end rib according to claim 1, characterized in that: The facade is provided with weight-reducing holes.

7. The wing segment connecting end rib according to claim 1, characterized in that: The carbon fiber foam sandwich panel comprises a first carbon fiber layer, a foam layer and a second carbon fiber layer which are arranged in sequence.

8. A method for manufacturing a wing segment connecting end rib, used for manufacturing the wing segment connecting end rib according to any one of claims 1 to 7, characterized in that: The method includes: Determine the shape and size of each sub-end rib according to the aerodynamic shape, spar and load requirements of the wing section; The sub-end ribs of the carbon fiber foam sandwich panel material are formed by a molding process.

9. The method for manufacturing the wing section connecting end rib according to claim 8, characterized in that: According to the aerodynamic shape, spar and load requirements of the wing section, the shape and size of each sub-end rib are determined, including: Determine the shapes of the upper and lower wing surfaces according to the aerodynamic shape of the wing section; Determine the shape and size of the connection hole according to the shape and size of the spar; The layup design of the carbon fiber foam sandwich panel is determined according to the load requirements of the wing section.

10. The method for manufacturing the wing segment connecting end rib according to claim 8, characterized in that: The sub-end ribs of the carbon fiber foam sandwich panel material formed by the molding process include: The foam layer of the one-piece carbon fiber foam sandwich panel; Obtaining a mold, wherein the mold comprises a bottom mold and a cover mold; The first carbon fiber layer, the glue layer and the foam layer of the carbon fiber foam sandwich panel are sequentially laid in the bottom mold, and the second carbon fiber layer and the glue layer are sequentially laid in the cover mold; The mold is tightened and cured using a press.

Images