EVTOL airplane vertical fin butt joint rib
By designing the vertical tail docking rib of the eVTOL aircraft, the problems of complex connection and high accuracy requirements in the prior art are solved, and the effects of high-precision installation, simplification of tooling, reducing costs and improving connection reliability are achieved.
Patent Information
- Application Number
- CN202422442350.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-10
- Publication Date
- 2025-07-29
- Estimated Expiration
- 2034-10-10
AI Technical Summary
The vertical tail connection structure of existing eVTOL aircraft is complex, with high accuracy requirements and complex tooling, making it difficult to achieve efficient installation and disassembly.
A vertical tail docking rib of an eVTOL aircraft is designed, including a docking rib body, with a servo connection groove in the middle, and docking holes on both sides. The front and rear ends on the inner side are connected to the front and rear beams. The rudder surface connection ears are provided on the rear beam connection side, and a local thickening structure is designed around the docking holes, so that high-precision connection is achieved through CNC machining.
It realizes high-precision installation, simplifies work installation, reduces costs, improves connection reliability and rigidity of connection points, reduces structural weight, and facilitates disassembly and installation.
Smart Images
Figure CN223161970U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of unmanned aerial vehicles, and particularly relates to a vertical tail docking rib of an eVTOL aircraft. Background Art
[0002] The development of eVTOL (Electric Vertical Takeoff and Landing) electric vertical takeoff and landing aircraft has attracted extensive attention from aerospace enterprises, the automotive industry, the transportation industry, governments, the military, and academia. The potential future applications of eVTOL involve various scenario modes such as urban passenger transportation, regional passenger transportation, freight transportation, personal aircraft, and emergency medical services. The vertical tail generally consists of two parts: a fixed stabilizer and a movable rudder. The fixed stabilizer is mainly responsible for the stability of the aircraft, while the movable rudder is used to control the yaw flight attitude of the aircraft. The vertical tail needs to be installed on the aircraft to transfer the load of the vertical tail to the aircraft. At the same time, when meeting the maintainability requirements, replacement, disassembly, etc. are required. The vertical tail is connected to the aircraft through fasteners, mainly through the connection of the front and rear beams to transfer the load of the vertical tail. It is necessary to design a connection structure on two components to connect with the mating parts, which requires high product precision and complex tooling. Summary of the Utility Model
[0003] The purpose of the utility model is to provide a vertical tail docking rib of an eVTOL aircraft to solve the problems mentioned in the background art. To achieve the above purpose, the utility model provides the following technical solution: a vertical tail docking rib of an eVTOL aircraft, including a docking rib body. A servo connection groove is opened in the middle of the docking rib body. Docking holes are opened on both sides of the servo connection groove. The front and rear ends of the inner side of the docking rib body are respectively connected with a front beam connection edge and a rear beam connection edge. A rudder surface connection lug is arranged on one side of the rear beam connection edge. The rudder surface connection lug is connected to the docking rib body. A local thickening structure is arranged around the inner side of the docking hole.
[0004] Preferably, the servo connection groove is recessed inward, and mounting holes are opened on the outer side of the servo connection groove.
[0005] Preferably, a relief hole one is opened at the front end of the docking rib body.
[0006] Preferably, there are two rudder surface connection lugs, which are horizontally distributed. Relief holes two are arranged on the upper and lower sides of the rudder surface connection lugs, and the relief holes two are opened on the docking rib body.
[0007] Preferably, a tool groove is opened at the rear side of the docking rib body, and the tool groove is located on one side of the rudder surface connection lug.
[0008] Technical effects and advantages of the present utility model: The docking rib has high installation accuracy: all the docking holes for connecting the vertical tail to the eVTOL aircraft are on the plane of the docking rib, and the docking rib is machined by a CNC machine with high precision;
[0009] High integration: The rudder installation joint is integrated on the docking rib, saving parts. The hole positions on the rudder surface connecting lugs have high precision and light weight;
[0010] Simple tooling and low cost: The docking holes of the docking rib are machined by a CNC machine with high precision, and installation with the eVTOL aircraft can be achieved without additional tooling;
[0011] Reliable connection: For the docking holes connecting to the eVTOL aircraft, local thickening is designed around the holes to increase the stiffness of the connection points, effectively reducing the stress and deformation of the connection points. Description of the drawings
[0012] Figure 1 Isometric view of the present utility model installed on the vertical tail;
[0013] Figure 2 Exploded view of the present utility model and the vertical tail;
[0014] Figure 3 Isometric view of the outer side of the present utility model;
[0015] Figure 4 Isometric view of the inner side of the present utility model;
[0016] Figure 5 Partial rear view of the present utility model;
[0017] Figure 6 Cross-sectional view of the present utility model in the horizontal direction at the position of the relief hole two.
[0018] In the figure, 1. Docking rib; 11. Servo connection groove; 12. Relief hole one; 13. Docking hole; 14. Front beam connection edge; 15. Rear beam connection edge; 16. Local thickening; 17. Relief hole two; 18. Tool groove; 19. Rudder surface connecting lug; 111. Mounting hole; 2. Vertical tail. Detailed implementation manners
[0019] In order to make the implementation means, creative features, achieved purposes and effects of the present utility model easy to understand, the present utility model will be further described below with reference to specific drawings. In the description of the present utility model, it should be noted that unless otherwise clearly specified and limited, the terms "installation", "connection", and "linkage" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection or a mechanical connection, or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and the interiors of two components can be in communication.
[0020] Embodiment
[0021] As Figure 1 And Figure 2 As shown, the docking rib 1 is installed at the root of the vertical tail 2 and connected to the eVTOL aircraft. The docking rib 1 is connected to the beam and skin of the vertical tail 2 to form a whole, transferring the load of the vertical tail 2 to the eVTOL aircraft to ensure the connection safety of the eVTOL aircraft. At the same time, after the docking rib 1 is connected to the vertical tail 2, an integral structure is formed. The docking rib 1 and the eVTOL aircraft are connected by fasteners, and the vertical tail 2 can be disassembled by removing the fasteners.
[0022] As Figure 3, as shown in Figures 4, 5, and 6, the docking rib 1 is an integral metal machined part. The preferred material is 7050 aluminum alloy, and the preferred heat treatment state is T7351. The docking rib 1 integrates the joints connected to the rudder and installs the servo motor at the same time to provide support for the servo motor. The docking rib 1 includes a docking rib body 10, a servo motor connection groove 11, a relief hole 12, a docking hole 13, a front beam connection edge 14, a rear beam connection edge 15, a local thickening structure 16, a relief hole 17, a tool groove 18, and a rudder surface connection lug 19. The servo motor connection groove 11 is opened in the middle of the docking rib body 10. Docking holes 13 are opened on both sides of the servo motor connection groove 11. The front and rear ends of the inner side of the docking rib body 10 are respectively connected to the front beam connection edge 14 and the rear beam connection edge 15. A rudder surface connection lug 19 is provided on one side of the rear beam connection edge 15, and the rudder surface connection lug 19 is connected to the docking rib body 10; the servo motor connection groove 11 is connected to the servo motor. Since the installation plane of the servo motor and the docking plane of the docking rib 1 are not coplanar, the servo motor connection groove 11 is recessed into the docking rib body 10. The inner square hole allows the servo motor to pass through, and the mounting holes 111 outside the square hole are connected to the mounting points of the servo motor to fix the servo motor. The relief hole 12 is opened at the front end of the docking rib body 10 to remove the part with low strength requirements and reduce the structural weight. The docking holes 13 are in the same plane, which is convenient for positioning. At the same time, the number of docking holes 13 is large. Even if some are damaged, the other holes can still bear the load, and the damage tolerance characteristics are relatively good. When docking with the eVTOL aircraft, it also uses plane docking, which is convenient for connection and does not require additional tooling. The front beam connection edge 14 and the rear beam connection edge 15 are connected to the front and rear beams to transfer the main load of the vertical tail 2. Fastener holes for connecting to the front and rear beams are designed on the front beam connection edge 14 and the rear beam connection edge 15. At the same time, the length is relatively long, and two rows of fastener holes can be installed, with high connection strength. The local thickening structure 16 is around the inner side of the docking hole 13. When the docking hole 13 is connected to the eVTOL aircraft, it is subjected to external surface forces, and it is necessary to minimize deformation and the stress level around the hole. Therefore, the thickness is increased to improve the stiffness of the connection area and reduce the stress level. The rudder surface connection lug 19 is formed by integrating two parallel distributed lugs after integrating the rudder surface connection joints and connecting to the joints on the rudder surface. Its processing direction is the front-rear direction. Therefore, after machining the lugs, a relatively thick solid area is formed in the rear area of the lugs, and there is a lot of surplus material. In order to reduce the weight, relief holes 17 are designed in the up-down direction to reduce the weight of the structure. The docking holes 13 at the rear of the docking rib 1 are connected to the eVTOL aircraft by fasteners. In order to facilitate the fastening of the fasteners, a tool groove 18 is designed on the rear side of the docking rib body 10 for the tool to pass through, and the tool groove 18 is located on one side of the rudder surface connection lug 19. In this example, the docking rib and the eVTOL aircraft are connected by bolts and nuts, and the tool groove allows the wrench to pass through to tighten the nut.
[0023] Finally, it should be noted that the above are only the preferred embodiments of the present utility model and are not intended to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions recorded in the foregoing embodiments or perform equivalent replacements on some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.
Claims
1. An eVTOL aircraft vertical tail docking rib, comprising a docking rib body, characterized in that: A servo connection groove is formed in the middle of the docking rib body. Docking holes are formed on both sides of the servo connection groove. A front beam connection edge and a rear beam connection edge are respectively connected to the front and rear ends of the inner side of the docking rib body. A rudder surface connection lug is provided on one side of the rear beam connection edge. The rudder surface connection lug is connected to the docking rib body. A locally thickened structure is provided around the inner periphery of the docking hole.
2. The vertical tail docking rib of an eVTOL aircraft according to claim 1, characterized in that: The servo connection groove is recessed inward, and mounting holes are formed outside the servo connection groove.
3. The vertical tail docking rib of an eVTOL aircraft according to claim 1, characterized in that: A relief hole 1 is formed at the front end of the docking rib body.
4. The vertical tail docking rib of an eVTOL aircraft according to claim 1, characterized in that: There are two rudder surface connection lugs, which are horizontally distributed. Relief holes 2 are provided on the upper and lower sides of the rudder surface connection lugs, and the relief holes 2 are formed on the docking rib body.
5. An eVTOL aircraft vertical tail docking rib according to claim 1, characterized in that: A tool groove is formed at the rear side of the docking rib body, and the tool groove is located on one side of the rudder surface connection lug.