An eVTOL aircraft vertical tail and fuselage connection structure

Abstract

The utility model discloses a kind of eVTOL aircraft vertical tail and fuselage connecting structure, by the skin of outside and the skeleton of inside, skin is overall structure, is divided into vertical tail part and fuselage part. Skeleton is composed of vertical tail beam, fuselage frame, root rib, its combination area is as the connecting structure of skeleton, vertical tail beam is composed of front beam and rear beam, fuselage frame is composed of front frame, rear frame, front joint, rear joint, root rib is composed of front rib, middle rib, rear rib, front frame, vertical tail front beam are connected together by front joint, rear frame, vertical tail rear beam are connected together by rear joint, form the mechanism of vertical and horizontal interlaced stereo with root rib, vertical tail and fuselage are connected in skin inside, with easily assembled, low in cost, product quality is high Characteristics.

Description

Technical Field

[0001] This utility model relates to the field of electric aircraft technology, specifically to a connection structure between the vertical tail and fuselage of an eVTOL aircraft. Background Technology

[0002] eVTOL (Electric Vertical Takeoff and Landing) aircraft can take off and land vertically, eliminating the need for long runways and enabling takeoff and landing operations within limited spaces. This significantly improves the flexibility and accessibility of air transport, making them suitable for scenarios such as urban air mobility. Powered by electricity, they produce no pollutants such as carbon dioxide and nitrogen oxides during operation, meeting the zero-carbon vision and environmental requirements. They also significantly reduce noise, enhancing the passenger experience and comfort. The overall configuration allows for various innovative aerodynamic-propulsion integrated designs and unconventional aerodynamic layouts, including multi-rotor, compound, and vector propulsion types, to meet diverse travel needs. Their structure is relatively simple, maintenance requirements are low, and electricity costs are typically lower than fuel costs, suggesting the potential for lower operating costs after large-scale commercial operation.

[0003] Compared to traditional aircraft, eVTOL aircraft have a larger order volume. One leading domestic eVTOL manufacturer has orders exceeding 1000 aircraft. To meet the demands of rapid production, these requirements must be considered in the design, ensuring both the quality and flight safety of the eVTOL aircraft. The area where the vertical tail connects to the fuselage has significant shape changes, with a large curvature in the transition zone. The skin and internal frame are prone to deformation after molding, leading to substantial repair and rework work during assembly due to component deformation, slowing down the assembly process. Excessive filing can also affect the strength of components, impacting the safety of the eVTOL aircraft. Therefore, the design must pre-plan for potential interference and filing areas, or segment large components for adjustment in stages.

[0004] Reference 1: Chinese patent document with publication number CN114906313A.

[0005] Reference 1 discloses a connection structure between an aircraft tail and fuselage, including a tail, fuselage, and a connection box. The tail includes a vertical stabilizer and two horizontal stabilizers. The fuselage includes a fuselage frame and fuselage panels. The connection box is fixedly connected to the horizontal fuselage panel above the tail of the fuselage. The connection box includes a support frame, a horizontal stabilizer connection frame, and a vertical stabilizer connection frame. The support beam includes a longitudinal beam parallel to the fuselage axis. Crossbeams symmetrically distributed with the fuselage axis are fixedly connected to both sides of the longitudinal beam. The crossbeams are perpendicular to the longitudinal beams and coplanar. The front end of the longitudinal beam and the two ends of the crossbeams are connected to diagonal beams, respectively. The two ends of the crossbeams are connected to the horizontal stabilizer connection frames, and the vertical stabilizer is detachably connected to the vertical stabilizer connection frame. This application provides a safe and reliable connection between the tail and fuselage, and the load on the tail can be evenly distributed to the fuselage, reducing the fuselage weight.

[0006] In the above-mentioned connection structure, the fuselage is connected to the horizontal and vertical stabilizers through a connection box. There are many connection areas. In order to ensure the accuracy of the aircraft connection, complex assembly tooling is required for assembly. The assembly process is complicated, the cost is high, and the production efficiency is low. Utility Model Content

[0007] The purpose of this invention is to solve the aforementioned technical problems in the prior art and to provide a connection structure between the vertical tail and fuselage of an eVTOL aircraft.

[0008] The technical solution adopted in this utility model is: a connection structure between the vertical tail and fuselage of an eVTOL aircraft, comprising:

[0009] The skin, which includes the vertical tail section and the fuselage section; and

[0010] The frame includes the tail boom, fuselage frame, and root ribs;

[0011] The vertical tail beam consists of a front beam and a rear beam, the fuselage frame consists of a front frame, a rear frame, a front joint and a rear joint, and the root rib consists of a front rib, a middle rib and a rear rib.

[0012] The lower ends of both the front beam and the rear beam are provided with central rib slots. The central rib is located between the front beam and the rear beam, with its two ends placed in the central rib slots of the front beam and the rear beam, respectively.

[0013] The front connector and the rear connector are respectively located at the bottom of the front beam and the rear beam. The front beam, the middle rib and the front connector are connected together by fasteners. The rear beam, the middle rib and the rear connector are connected together by fasteners.

[0014] The front frame is connected to the front connector by fasteners. The upper end of the front frame is provided with a front rib slot, and one end of the front rib is placed in the front rib slot. The rear frame is connected to the rear connector by fasteners. The upper end of the rear frame is provided with a rear rib slot, and one end of the rear rib is placed in the rear rib slot.

[0015] As a further optimization of the connection structure between the vertical tail and fuselage of an eVTOL aircraft according to this utility model: the front connector includes a beam connecting edge, a skin connecting edge and a frame connecting edge. The frame connecting edge is a plate similar to a trapezoid. The beam connecting edge and the skin connecting edge are both perpendicular to each other with the frame connecting edge. The two skin connecting edges are set along the two sides of the frame connecting edge, and the beam connecting edge is set along the top edge of the frame connecting edge.

[0016] As a further optimization of the connection structure between the vertical tail and fuselage of an eVTOL aircraft according to this utility model: the lower end of the front beam is provided with a beam connecting web and a beam sealing edge, the beam connecting web is connected to the front part of the middle rib, and the beam sealing edge is connected to the beam connecting edge of the front joint by fasteners.

[0017] As a further optimization of the connection structure between the vertical tail and fuselage of an eVTOL aircraft according to this utility model: there are gaps between the front beam and the front frame and between the rear beam and the rear frame.

[0018] As a further optimization of the connection structure between the vertical tail and fuselage of an eVTOL aircraft according to this utility model, the gap is 2-3mm.

[0019] As a further optimization of the connection structure between the vertical tail and fuselage of an eVTOL aircraft according to this utility model: the front beam and the front frame are integrated components, and the rear beam and the rear frame are integrated components.

[0020] As a further optimization of the connection structure between the vertical tail and fuselage of an eVTOL aircraft according to this utility model: the front connector and the rear connector are made of 7050 aluminum alloy.

[0021] As a further optimization of the connection structure between the vertical tail and fuselage of an eVTOL aircraft according to this utility model: the materials of the front beam, rear beam, front rib, middle rib, rear rib, front frame and rear frame are all carbon fiber composite materials.

[0022] As a further optimization of the connection structure between the vertical tail and fuselage of an eVTOL aircraft according to this utility model, the fastener is a countersunk blind rivet.

[0023] As a further optimization of the connection structure between the vertical tail and fuselage of an eVTOL aircraft according to this utility model: the skin and the frame are bonded together with structural adhesive.

[0024] This utility model has the following beneficial effects:

[0025] 1. In the connection structure of this utility model, the front and rear beams of the vertical tail are left with assembly gaps when assembled with the front and rear frames of the fuselage. They are connected by front and rear joints, which can avoid interference problems caused by manufacturing tolerances and reduce the amount of grinding during assembly.

[0026] 2. In the connection structure of this utility model, the shape of the skin integrates the fuselage and the tail section together. There is a certain deformation in the area where the curvature changes. The frame is designed as multiple parts at the junction of the tail and the fuselage. This can effectively reduce the gap or interference between the frame and the skin, so that the curvature changes can fit better and improve the bonding quality in this area. Attached Figure Description

[0027] Figure 1 This is an isometric view of the connection structure between the vertical tail and fuselage of the eVTOL aircraft of this utility model;

[0028] Figure 2 This is an exploded view of the connection structure between the vertical tail and fuselage of the eVTOL aircraft of this utility model;

[0029] Figure 3 This is an axonometric view of the skeleton in the connection structure of this utility model;

[0030] Figure 4 This is an exploded view of the skeleton in the connection structure of this utility model;

[0031] Figure 5 This is a side view of the connection between the front beam and the front frame in the connection structure of this utility model;

[0032] Figure 6 This is a side view of the connection between the rear beam and the rear frame in the connection structure of this utility model;

[0033] Figure 7 This is a transverse sectional view of the connection area between the front beam and the front rib in the connection structure of this utility model;

[0034] Figure 8 This is a longitudinal sectional view of the connection area between the front beam and the front connector in the connection structure of this utility model;

[0035] Figure 9 This is an isometric view of the front connector in the connection structure of this utility model;

[0036] Figure 10 This is an axonometric view of the front beam in the connection structure of this utility model;

[0037] Numbered in the diagram: 1. Skin; 11. Vertical tail section; 12. Fuselage section; 2. Frame; 21. Vertical tail beam; 211. Front beam; 2111. Beam connecting web; 2112. Beam edge sealing; 212. Rear beam; 22. Fuselage frame; 221. Front frame; 222. Rear frame; 223. Front joint; 2231. Beam connecting edge; 2232. Skin connecting edge; 2233. Frame connecting edge; 224. Rear joint; 23. Root rib; 231. Front rib; 232. Middle rib; 233. Rear rib. Detailed Implementation

[0038] To better understand this utility model, the following embodiments further illustrate the content of this utility model, but the content of this utility model is not limited to the following embodiments.

[0039] like Figure 1 and Figure 2 As shown, an eVTOL aircraft's vertical tail and fuselage connection structure consists of a skin 1 and an internal frame 2. The skin 1 and frame 2 are bonded together with structural adhesive, and fasteners are added locally at the connection surfaces for mechanical connection; these fasteners are not shown in the figure. The skin 1 is a monolithic structure, divided into a vertical tail section 11 and a fuselage section 12. Because eVTOL aircraft have a relatively small takeoff weight of only 2-3 tons, the skin 1 is relatively thin and is generally made of carbon fiber composite material. After molding, the parts are prone to deformation, especially in the transition area between the vertical tail section 11 and the fuselage section 12. To ensure the safety of the eVTOL aircraft, the frame 2 and skin 1 need to be precisely assembled. Therefore, the frame 2 needs to be divided into multiple sections. During assembly, the frame parts are adjusted section by section to ensure a good and precise fit with the skin 1. The frame 2 consists of a vertical tail beam 21, a fuselage frame 22, and a root rib 23. The vertical tail beam 21 and the fuselage frame 22 are connected at the root rib 23 to form a longitudinal and transverse frame structure, connecting the vertical tail 11 and the fuselage 12 to ensure the connection strength.

[0040] like Figure 3 and Figure 4 As shown, the vertical tail beam 21 consists of a front beam 211 and a rear beam 212, and the fuselage frame 22 consists of a front frame 221, a rear frame 222, a front joint 223, and a rear joint 224. Because the front beam 211 and rear beam 212 bear significant stress, the root rib 23 is divided into three parts: a front rib 231, a middle rib 232, and a rear rib 233. The front beam 211 and rear beam 212 are the vertical tail sections supporting the skin, while the front frame 221 and rear frame 222 are the fuselage sections supporting the skin. In part, the front rib 231, middle rib 232, and rear rib 233 of the root rib 23 are located in the transition area between the vertical tail and the fuselage. The front beam 211 and rear beam 212 of the vertical tail are connected to the front frame 221 and rear frame 222 of the fuselage at the root rib 23 position. The front rib 231 is arranged in front of the front beam 211 and the front frame 231, the middle rib 232 is arranged between the front beam 211 and the front frame 231 and the rear beam 212 and the rear frame 222, and the rear rib 233 is arranged behind the rear beam 212 and the rear frame 222.

[0041] The front beam 211, rear beam 212, front rib 231, middle rib 232, rear rib 233, front frame 221, and rear frame 222 are all made of carbon fiber composite material to reduce structural weight. The front beam 211 and front frame 231 can be integrated into one part, as can the rear beam 212 and rear frame 222. However, because the front beams 211 and 212 are relatively narrow, while the front frames 221 and 222 are wider, integrating them into a single part would require a larger amount of raw material and machining, resulting in higher costs. Furthermore, a single-piece molded part cannot be adjusted, which could lead to larger gaps or interference when fitting with the skin in the transition area between the tail and fuselage, compromising product quality.

[0042] The front connector 223 and the rear connector 224 are machined aluminum alloy parts, preferably made of 7050 aluminum alloy, and preferably heat treated in T7451 heat. The front connector 223 connects the front beam 211 to the front frame 221, and the rear connector 224 connects the rear beam 212 to the rear frame 222. During assembly, the positions of the parts can be adjusted so that the assembled frame 2 fits well with the skin 1.

[0043] The frame is divided into multiple parts for assembly. Considering tolerances, skin deformation, and part adjustment, the connection and fit between the frame and the skin are satisfied. This helps to reduce filing and repair, reduce assembly time, improve assembly efficiency, and meet the requirements of mass production of eVTOL aircraft.

[0044] like Figure 5 and 6 As shown, the front part of the middle rib 232 is inserted into the end box of the front beam 211, and the rear part is inserted into the end box of the rear beam 212. The front rib 231 is inserted into the end opening of the front frame 221. A design gap is left between the front beam 211 and the front frame 221. During assembly, considering the tolerance of the parts, even if the middle part is made large and positioned forward, it can still be easily assembled. A design gap is left between the rear beam 212 and the rear frame 222. During assembly, considering the tolerance of the parts, even if the middle part is made large and positioned backward, it can still be easily assembled. The preferred gap is 2mm, which can still be well absorbed by the gap under the tolerance of part assembly positioning and manufacturing.

[0045] like Figure 7 and Figure 8As shown, the connection structure of the rear beam 212 is similar to that of the front beam 211. This example only describes the area of ​​the front beam 211. At the connection between the front connector 223 and the front beam 211, the fastener passes through three layers of parts: the beam connection edge 2231 of the front connector 223, the beam sealing edge 2112 of the front beam 211, and the front web of the middle rib 232. The connection form of the rear connector 224 is similar to that of the front connector 223. The front rib 231 is installed into the opening of the front frame 221, and the front part of the middle rib 232 is installed into the end box of the front beam. A gap is designed between the front beam and the front frame to absorb tolerances during assembly. If there is still a gap, it is filled with structural adhesive to ensure that the gap area can still transmit force through the structural adhesive.

[0046] like Figure 9 As shown, the front joint 223 and the rear joint 224 have similar structures, so only the front joint 223 will be described. The front joint 223 consists of three parts: a beam connecting edge 2231, a skin connecting edge 2232, and a frame connecting edge 2233. The beam connecting edge 2231 is tightly attached to the beam sealing edge 2112 of the front beam 211 and is connected by fasteners. At the same time, the fasteners also connect to the central rib 232 inside the front beam sealing edge. The skin connecting edge is bonded to the skin with structural adhesive. In addition to its connecting function, the structural adhesive also absorbs tolerances. After bonding, it is mechanically connected by fasteners. The frame connecting edge 2233 is tightly attached to the web of the front frame 221 and is connected by fasteners.

[0047] like Figure 10 As shown, the front beam 211 is designed with a beam connecting web 2111 and a beam sealing edge 2112 at the end. The beam connecting web 2111 is connected to the front of the middle rib 232, and the beam sealing edge 2112 is connected to the beam connecting edge 2231 of the front joint 223 by fasteners.

[0048] The specific embodiments of this utility model have been described above. It should be understood that this utility model is not limited to the specific embodiments described above, and those skilled in the art can make various modifications or variations within the scope of the claims, which do not affect the substantive content of this utility model.

Claims

1. A connection structure between the vertical tail and fuselage of an eVTOL aircraft, characterized in that, include: Skin (1), which includes a vertical tail section (11) and a fuselage section (12); as well as The frame (2) includes a vertical tail beam (21), a fuselage frame (22), and root ribs (23); The vertical tail beam (21) is composed of a front beam (211) and a rear beam (212), the fuselage frame (22) is composed of a front frame (221), a rear frame (222), a front connector (223) and a rear connector (224), and the root rib (23) is composed of a front rib (231), a middle rib (232) and a rear rib (233). The lower ends of the front beam (211) and the rear beam (212) are provided with a central rib slot. The central rib (232) is located between the front beam (211) and the rear beam (212), with its two ends placed in the central rib slots of the front beam (211) and the rear beam (212) respectively. The front connector (223) and the rear connector (224) are respectively located at the bottom of the front beam (211) and the rear beam (212). The front beam (211), the middle rib (232) and the front connector (223) are connected together by fasteners. The rear beam (212), the middle rib (232) and the rear connector (224) are connected together by fasteners. The front frame (221) is connected to the front connector (223) by fasteners. The upper end of the front frame (221) is provided with a front rib (231) slot, and one end of the front rib (231) is placed in the front rib (231) slot. The rear frame (222) is connected to the rear connector (224) by fasteners. The upper end of the rear frame (222) is provided with a rear rib (233) slot, and one end of the rear rib (233) is placed in the rear rib (233) slot.

2. The connection structure between the vertical tail and fuselage of an eVTOL aircraft as described in claim 1, characterized in that, The front connector (223) includes a beam connecting edge (2231), a skin connecting edge (2232), and a frame connecting edge (2233). The frame connecting edge (2233) is a trapezoidal plate. The beam connecting edge (2231) and the skin connecting edge (2232) are both perpendicular to the frame connecting edge (2233). The two skin connecting edges (2232) are set along the two sides of the frame connecting edge (2233), and the beam connecting edge (2231) is set along the top edge of the frame connecting edge (2233).

3. The connection structure between the vertical tail and fuselage of an eVTOL aircraft as described in claim 2, characterized in that, The lower end of the front beam (211) is provided with a beam connecting web (2111) and a beam sealing edge (2112). The beam connecting web (2111) is connected to the front part of the middle rib (232), and the beam sealing edge (2112) is connected to the beam connecting edge (2231) of the front joint (223) by fasteners.

4. The connection structure between the vertical tail and fuselage of an eVTOL aircraft as described in claim 1, characterized in that, There are gaps between the front beam (211) and the front frame (221) and between the rear beam (212) and the rear frame (222).

5. The eVTOL aircraft vertical tail and fuselage connection structure as described in claim 4, characterized in that, The gap is 2-3mm.

6. The connection structure between the vertical tail and fuselage of an eVTOL aircraft as described in claim 1, characterized in that, The front beam (211) and the front frame (221) are integrated components, and the rear beam (212) and the rear frame (222) are integrated components.

7. The connection structure between the vertical tail and fuselage of an eVTOL aircraft as described in claim 1, characterized in that, The front connector (223) and the rear connector (224) are made of 7050 aluminum alloy.

8. The connection structure between the vertical tail and fuselage of an eVTOL aircraft as described in claim 1, characterized in that, The front beam (211), rear beam (212), front rib (231), middle rib (232), rear rib (233), front frame (221), and rear frame (222) are all made of carbon fiber composite material.

9. The connection structure between the vertical tail and fuselage of an eVTOL aircraft as described in claim 1, characterized in that, The fastener is a countersunk blind rivet.

10. The connection structure between the vertical tail and fuselage of an eVTOL aircraft as described in claim 1, characterized in that, The skin (1) and the skeleton (2) are bonded together with structural adhesive.

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