Horizontal tail and vertical tail butt joint structure of electric aircraft

Abstract

The utility model relates to the technical field of electric aircrafts, in particular to a butt joint structure of a horizontal tail and a vertical tail of an electric aircraft, which comprises a horizontal tail wing, and a vertical tail wing is arranged on one side of the horizontal tail wing. The horizontal empennage comprises an upper skin, a lower skin is arranged below the upper skin, and an empennage rear beam and an empennage front beam are arranged between the upper skin and the lower skin. The tail wing has the advantages that the horizontal tails are integrally designed, the vertical tails and the tail section of the fuselage are integrally designed, the connection mode of the horizontal tails and the vertical tails is simple, and the tail wing is convenient to disassemble and assemble, in the actual use process, different from the traditional concept of left and right horizontal tails, the horizontal tails are integrally designed, and the vertical tails and the tail section of the fuselage form a vertical tail tail wing; the structure layout of an aircraft is simplified, the horizontal empennage and the vertical empennage are firmly connected together through mechanical connection, a stable and efficient flight control system is formed, the manufacturing difficulty is greatly reduced, and much convenience is brought to disassembly, assembly and maintenance.

Description

Technical Field

[0001] This utility model relates to the field of electric aircraft technology, specifically to a docking structure for the horizontal and vertical tail of an electric aircraft. Background Technology

[0002] Electric aircraft are aircraft that are powered by electric motors rather than internal combustion engines. Power sources include fuel cells, solar cells, supercapacitors, wireless power transfer, or other types of batteries.

[0003] As disclosed in patent CN105197225A, an assembled UAV tail fin consists of a tail fin frame, a semi-tail fin stabilizer, an elevator tail fin, a tail fin rudder, a fuselage, a tail section of the fuselage, fixed rail pin holes, and positioning rail pin holes. The semi-tail fin stabilizer is aligned with the connector at the tail section of the fuselage, ensuring that the fixed pins align with the pin holes, the slots align with the stabilizing square walls, and the bosses align with the connectors. Then, the fixed shaft pin holes align with the positioning shaft pin holes. Finally, the fixed shaft pin holes and positioning shaft pin holes are locked together using fixed shaft pins. In this way, the horizontal tail fin stabilizer and the tail section of the fuselage are connected and fixed as a single structure. Its function and purpose are the same as those of traditionally integrated UAV tail fins. Its advantages include: the horizontal tail fin stabilizer is manufactured separately from the fuselage, significantly reducing the need for molds and greatly saving manufacturing costs and difficulty; facilitating product packaging and transportation; and being convenient for installation, disassembly, maintenance, and repair.

[0004] Although the aforementioned patent uses a connector at the tail of the fuselage to connect with the horizontal stabilizer and then locks it in place with a pivot pin, this structural design, while simple, is not suitable for larger drones or large electric aircraft. Large, heavy drones or large electric aircraft require greater structural stability and load-bearing capacity. The connector and pivot pin fixing method in the patent cannot guarantee sufficient strength and stability when subjected to the enormous wind resistance, vibration, and potential impact loads generated by large aircraft during flight. Over time, this structure may loosen, wear down, or even fail, posing a serious threat to flight safety.

[0005] Therefore, there is an urgent need for a horizontal and vertical tail docking structure for electric aircraft to solve the above problems. Utility Model Content

[0006] The purpose of this utility model is to provide a horizontal and vertical tail docking structure for an electric aircraft, which has the advantages of integrated horizontal tail design, integrated vertical tail and fuselage tail section design, simple connection form between horizontal and vertical tail, and convenient disassembly and installation, thus solving the problems mentioned in the background art.

[0007] To achieve the above objectives, this utility model provides the following technical solution: a horizontal tail and vertical tail docking structure for an electric aircraft, including a horizontal tail fin, wherein a vertical tail fin is provided on one side of the horizontal tail fin.

[0008] The horizontal tail fin includes an upper skin, and a lower skin is provided below the upper skin. A tail fin rear spars and a tail fin front spars are provided between the upper skin and the lower skin. Several horizontal tail ribs are provided between the tail fin rear spars and the tail fin front spars. The front side of the horizontal tail ribs extends to the front side of the tail fin front spars. Two symmetrically arranged motor reinforcing frame assemblies are provided through one side of the tail fin rear spars and the tail fin front spars.

[0009] The vertical tail fin includes a left skin disposed on the surface of the horizontal tail fin, and a right skin disposed on one side of the left skin. The left and right skins are provided with a front vertical tail spar and a rear vertical tail spar. Several vertical tail ribs are disposed between the front and rear vertical tail spars. From front to back, a tail end reinforcing frame one, a tail end reinforcing frame two, and a tail end reinforcing frame three are disposed between the left and right skins.

[0010] Furthermore, as a preferred embodiment of this utility model, a plurality of horizontal and vertical tail connecting joints are provided through the middle position on one side of the rear beam and the front beam of the tail wing. A plurality of connecting holes are provided on the surface of the second and third tail end reinforcing frames, and the connecting holes are adapted to the horizontal and vertical tail connecting joints.

[0011] Furthermore, as a preferred embodiment of this utility model, the bottom of the left and right skins are sequentially and bolted together to be fixedly connected to the front maintenance port cover and the horizontal and vertical tail fairings.

[0012] Furthermore, as a preferred embodiment of this invention, the rear sides of the left and right skins are jointly fixedly connected to a tail cone cap by bolts.

[0013] Furthermore, as a preferred embodiment of this invention, an opening is formed between the second and third tail end reinforcing frames for inserting the horizontal tail fin at its middle position.

[0014] Beneficial effects: The technical solution of this application has the following technical effects: This utility model has an integrated horizontal tail design, an integrated vertical tail and fuselage tail section design, and a simple connection between the horizontal tail and the vertical tail, which has the advantages of being easy to disassemble and install. In actual use, it is different from the traditional concept of left and right horizontal tails. The horizontal tail adopts an integrated design, and the vertical tail and fuselage tail section form the vertical tail fin, which simplifies the structural layout of the aircraft. Through mechanical connection, the horizontal tail fin and the vertical tail fin are firmly connected together, forming a stable and efficient flight control system, which greatly reduces the manufacturing difficulty, brings many conveniences to disassembly, assembly and maintenance, and also reduces the cost and operating expenses of the aircraft.

[0015] It should be understood that all combinations of the foregoing concepts and the additional concepts described in more detail below can be considered as part of the utility model subject matter of this disclosure, provided that such concepts do not contradict each other. Attached Figure Description

[0016] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0017] Figure 1 This is a schematic diagram of the structure of this utility model;

[0018] Figure 2 This is a three-dimensional schematic diagram of a partially disassembled horizontal tail fin of the present invention;

[0019] Figure 3 This is a bottom view of the present invention;

[0020] Figure 4 This is a three-dimensional schematic diagram of a partially disassembled structure of the vertical tail fin of this utility model;

[0021] Figure 5 This is a three-dimensional schematic diagram showing the partial disassembled structure of the horizontal tail fin and vertical tail fin of this utility model.

[0022] The meanings of the reference numerals in the figures are as follows: 1. Horizontal tail fin; 11. Upper skin; 12. Lower skin; 13. Tail fin rear spars; 14. Tail fin front spars; 15. Horizontal tail rib; 16. Motor reinforcement frame assembly; 17. Horizontal and vertical tail connection joint; 2. Vertical tail fin; 21. Left skin; 22. Right skin; 23. Vertical tail front spars; 24. Vertical tail rear spars; 25. Possible rib; 26. Tail end reinforcement frame one; 27. Tail end reinforcement frame two; 28. Tail end reinforcement frame three; 29. ​​Connection hole; 3. Front maintenance hatch cover; 4. Horizontal and vertical tail fairings; 5. Tail cone hatch cover. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. To better understand the technical content of the present utility model, specific embodiments are provided and described in conjunction with the accompanying drawings. Various aspects of the present utility model are described in this disclosure with reference to the accompanying drawings, which show many illustrative embodiments. It should be understood that the various concepts and embodiments described above, as well as those described in more detail below, can be implemented in any of many ways. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0024] As attached Figure 1 To be continued Figure 5 As shown: This embodiment provides a horizontal and vertical tail docking structure for an electric aircraft, including a horizontal tail 1, and a vertical tail 2 disposed on one side of the horizontal tail 1.

[0025] The horizontal tail fin 1 includes an upper skin 11, a lower skin 12 is provided below the upper skin 11, a tail fin rear spars 13 and a tail fin front spars 14 are provided between the upper skin 11 and the lower skin 12, and a number of horizontal tail ribs 15 are provided between the tail fin rear spars 13 and the tail fin front spars 14. The front side of the horizontal tail ribs 15 extends to the front side of the tail fin front spars 14. Two symmetrically arranged motor reinforcing frame assemblies 16 are provided through one side of the tail fin rear spars 13 and the tail fin front spars 14. The tail fin rear spars 13, the tail fin front spars 14 and the horizontal tail ribs 15 are all fixedly connected by bolts. The motor reinforcing frame assemblies 16 are fixedly connected to the tail fin rear spars 13 and the tail fin front spars 14 by bolts. The tail fin rear spars 13 and the tail fin front spars 14 are fixedly connected to the upper skin 11 and the lower skin 12 by bolts and adhesive.

[0026] The vertical tail fin 2 includes a left skin 21 disposed on the surface of the horizontal tail fin 1. A right skin 22 is disposed on one side of the left skin 21. The left skin 21 and the right skin 22 are provided with a front vertical tail beam 23 and a rear vertical tail beam 24. Several vertical tail ribs 25 are disposed between the front vertical tail beam 23 and the rear vertical tail beam 24. A tail end reinforcing frame 1 26, a tail end reinforcing frame 27, and a tail end reinforcing frame 3 28 are disposed between the left skin 21 and the right skin 22 from front to back. The front vertical tail beam 23 and the rear vertical tail beam 24 are fixedly connected to the tail end reinforcing frame 27 and the tail end reinforcing frame 3 28 by bolts. The front vertical tail beam 23 and the rear vertical tail beam 24 are fixedly connected to the left skin 21 and the right skin 22 by bolts and adhesive. The tail end reinforcing frame 1 26 is fixedly connected to the left skin 21 and the right skin 22 by bolts.

[0027] Specifically, several horizontal and vertical tail connection joints 17 are provided through the middle of one side of the tail wing rear beam 13 and tail wing front beam 14. Several connection holes 29 are opened on the surface of the tail end reinforcing frame 27 and tail end reinforcing frame 3. The connection holes 29 are compatible with the horizontal and vertical tail connection joints 17.

[0028] In this embodiment, the horizontal tail fin 1 and the vertical tail fin 2 can be quickly installed and fixed by using the horizontal tail and vertical tail connecting joint 17 and connecting hole 29, thus facilitating disassembly and assembly.

[0029] Specifically, the bottom of the left skin 21 and the right skin 22 are connected to the front maintenance port cover 3 and the horizontal and vertical tail fairings 4 by bolts from front to back.

[0030] In this embodiment: through the combined use of the front maintenance access cover 3 and the horizontal and vertical tail fairings 4, the front maintenance access cover 3 allows maintenance personnel to quickly enter the aircraft, which helps to discover and repair potential safety hazards in a timely manner, thereby improving flight safety. The horizontal and vertical tail fairings 4 are used to cover and protect the horizontal tail 1, reduce aerodynamic drag, and improve flight efficiency.

[0031] Specifically, the rear sides of the left skin 21 and the right skin 22 are jointly fixedly connected to the tailbone cap 5 by bolts.

[0032] In this embodiment, the tailbone cap 5 effectively protects the tailbone from external environmental erosion and damage, extending its service life.

[0033] Specifically, an opening is formed between the tail end reinforcing frame 27 and the tail end reinforcing frame 3, which is used to insert the horizontal tail fin 1 into the middle position.

[0034] In this embodiment, the opening between the tail end reinforcing frame 27 and the tail end reinforcing frame 3 allows the vertical tail fin 2 to be inserted into the middle position of the horizontal tail fin 1, thereby improving the connection tightness between the horizontal tail fin 1 and the vertical tail fin 2 and thus improving the overall structural integrity.

[0035] The working principle and usage process of this utility model are as follows: During installation, the rear beam 13 and front beam 14 of the tail wing are installed to the horizontal tail rib 15 and the motor reinforcing frame assembly 16 by bolts. Then, the rear beam 13 and front beam 14 of the tail wing are connected to the upper skin 11 and the lower skin 12 by bolts and adhesive to form a whole, thereby forming the horizontal tail wing 1. Next, the front beam 23 and rear beam 24 of the vertical tail are connected to the vertical tail rib 25, the tail end reinforcing frame 27, and the tail end reinforcing frame 3 28 by bolts. Then, the front beam 23 and rear beam 24 of the vertical tail are connected to the left skin 21 and the right skin 22 by bolts and adhesive. The tail end reinforcing frame 1 26 is connected to the left skin by bolts. Connect the 21 and right skin 22 to form a whole, thus forming the vertical tail fin 2; finally, place the horizontal tail fin 1 stably, then align the opening formed between the tail end reinforcing frame 27 and the tail end reinforcing frame 28 on the vertical tail fin 2 with the middle of the horizontal tail fin 1, and at the same time, ensure that the horizontal and vertical tail connecting joint 17 and the connecting hole 29 are aligned and press down. Then, use the horizontal and vertical tail connecting joint 17 to fix the horizontal tail fin 1 and the vertical tail fin 2. Connect bolts from the positions of the front maintenance cover 3, the horizontal and vertical tail fairings 4, and the tail cone cover 5 to fix the front maintenance cover 3, the horizontal and vertical tail fairings 4, and the tail cone cover 5 to the left skin 21 and the right skin 22.

[0036] It should be noted that in this paper, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

[0037] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Those skilled in the art to which this invention pertains can make various modifications and refinements without departing from the spirit and scope of the present invention. Therefore, the scope of protection of this invention shall be determined by the claims.

Claims

1. A horizontal and vertical tail docking structure for an electric aircraft, comprising a horizontal tail (1), characterized in that: A vertical tail fin (2) is provided on one side of the horizontal tail fin (1); The horizontal tail fin (1) includes an upper skin (11), and a lower skin (12) is provided below the upper skin (11). A tail fin rear spars (13) and a tail fin front spars (14) are provided between the upper skin (11) and the lower skin (12). A plurality of horizontal tail ribs (15) are provided between the tail fin rear spars (13) and the tail fin front spars (14). The front side of the horizontal tail ribs (15) extends to the front side of the tail fin front spars (14). Two symmetrically arranged motor reinforcing frame assemblies (16) are provided through one side of the tail fin rear spars (13) and the tail fin front spars (14). The vertical tail fin (2) includes a left skin (21) disposed on the surface of the horizontal tail fin (1). A right skin (22) is disposed on one side of the left skin (21). A vertical tail front spar (23) and a vertical tail rear spar (24) are disposed inside the left skin (21) and the right skin (22). A number of vertical tail ribs (25) are disposed between the vertical tail front spar (23) and the vertical tail rear spar (24). A tail end reinforcing frame one (26), a tail end reinforcing frame two (27) and a tail end reinforcing frame three (28) are disposed sequentially from front to back between the left skin (21) and the right skin (22).

2. The horizontal and vertical tail docking structure of an electric aircraft according to claim 1, characterized in that: Several horizontal and vertical tail connection joints (17) are provided through the middle of one side of the tail wing rear beam (13) and tail wing front beam (14). Several connection holes (29) are provided on the surface of the tail end reinforcing frame two (27) and tail end reinforcing frame three (28). The connection holes (29) are adapted to the horizontal and vertical tail connection joints (17).

3. The horizontal and vertical tail docking structure of an electric aircraft according to claim 1, characterized in that: The bottom of the left skin (21) and the right skin (22) are connected to the front maintenance port cover (3) and the horizontal and vertical tail fairings (4) by bolts from front to back.

4. The horizontal and vertical tail docking structure of an electric aircraft according to claim 1, characterized in that: The left skin (21) and the right skin (22) are connected together by bolts to the tailbone cap (5).

5. The horizontal and vertical tail docking structure of an electric aircraft according to claim 1, characterized in that: An opening is formed between the tail end reinforcing frame two (27) and the tail end reinforcing frame three (28) for inserting the horizontal tail fin (1) into the middle position.

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