A horizontal tail structure of an electric aircraft

Abstract

The present invention relates to the technical field of electric aircraft structures, and in particular to a horizontal tail structure for an electric aircraft, comprising: a horizontal stabilizer structure, the horizontal stabilizer structure including an upper skin, a lower skin disposed above the upper skin, a front beam and a rear beam being provided through the inner cavities of the upper and lower skins, and a plurality of foam sandwich ribs being provided between the front beam and the rear beam. The present invention has the advantages of an integrated horizontal stabilizer structure, multifunctional motor supports, and cooling and elevator shaft designs. In actual use, firstly, the horizontal tail adopts the innovative concept of an integrated design, which reduces the number of parts, thereby significantly reducing manufacturing costs and shortening the production cycle. The integrated design simplifies the docking process between the horizontal tail and the fuselage structure, reduces assembly errors, and improves the overall structural rigidity and aerodynamic efficiency. This not only optimizes the production process, but also ensures the stability and safety of the aircraft during flight.

Description

Technical Field

[0001] The present invention relates to the technical field of electric aircraft structures, and in particular to a horizontal tail structure of an electric aircraft. Background Art

[0002] The horizontal stabilizer is the abbreviation of the horizontal tail, which is one of the main components of the aircraft. It is generally installed in a horizontal state at the tail of the fuselage. The front half of it is immovable and is the horizontal stabilizer. Its pitch stabilization function is guaranteed. The rear half is the elevator, which controls the ascent and descent of the aircraft. It is connected to the horizontal stabilizer by a hinge.

[0003] The horizontal tail structure of electric aircraft currently generally adopts a segmented design, which is specifically divided into two parts: the left horizontal tail and the right horizontal tail. During assembly, this design needs to be installed at the trailing edge of the fuselage based on its structural characteristics. However, the horizontal tail of an electric aircraft is not only an aerodynamic surface that provides lift and stability, but also needs to be used to install the motor.

[0004] Due to the introduction of electric motors, the structural form of the horizontal tail of electric aircraft has undergone significant changes compared to the traditional horizontal tail profile. The installation position, weight distribution and required connection structure of the motor have made the design of the horizontal tail more complicated. This complexity is not only reflected in the manufacturing and assembly of the structure, but also in the aerodynamic impact it brings to the horizontal tail. The presence of the motor often increases the air resistance of the horizontal tail, which not only reduces the flight efficiency of the aircraft, but may also have an adverse effect on the flight performance of the aircraft.

[0005] In addition, the installation of the motor also directly affects the structural form and movement mechanism of the elevator. Traditional elevator designs are usually arranged directly on the horizontal tail surface and connected to the aircraft's control system through mechanisms such as connecting rods. However, in electric aircraft, due to the presence of the motor, the motor support often becomes the support point for the installation and movement of the elevator. This change not only requires the design of the elevator to take into account the influence of the motor support, but may also cause changes in the elevator's motion trajectory and response characteristics.

[0006] Therefore, there is an urgent need for a horizontal tail structure for an electric aircraft to solve the above problems. Summary of the Invention

[0007] The purpose of the present invention is to provide a horizontal tail structure for an electric aircraft, which has the advantages of an integrated horizontal stabilizer, multifunctional motor supports, cooling and elevator shaft design, and solves the problems raised by the above-mentioned background technology.

[0008] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: A horizontal tail structure for an electric aircraft, comprising: a horizontal stabilizer structure, the horizontal stabilizer structure including an upper skin, a lower skin arranged above the upper skin, a front beam and a rear beam being provided through the inner cavities of the upper and lower skins, a plurality of foam sandwich ribs being provided between the front and rear beams, a plurality of metal joints being provided on the front side of the rear beam, and two motor supports being provided on one side of the upper and lower skins.

[0009] Two elevator assemblies are commonly provided on the front sides of the horizontal stabilizer structure and the elevator assembly.

[0010] The elevator assembly includes an elevator main structure, an elevator servo is provided on one side of the inner cavity of the lower skin, an elevator connecting rod is provided on one side of the elevator servo, one side of the elevator connecting rod is rotatably connected to the elevator fixed joint, one side of the elevator fixed joint is detachably connected to the upper skin and the lower skin by bolts, three elevator rotation axis connecting rods are rotatably connected to the inner cavity of the elevator main structure, and the three elevator rotation axis connecting rods are detachably connected to each other by bolts, one side of the elevator connecting rod is fixedly connected to the elevator rotation axis connecting rods on both sides, one end of the elevator rotation axis connecting rods on both sides is rotatably connected to the elevator rotation axis joint, one side of the elevator rotation axis joint is fixedly connected to the rear beam, and one end of the middle elevator rotation axis connecting rod extends through one side of the motor support.

[0011] The inner cavity of the motor support is provided with a motor, and one side of the motor extends to the outside of the motor support.

[0012] Furthermore, as a preferred embodiment of the present invention, the motor support includes a support body, both sides of the support body are provided with rib features, the rear side of the support body is provided with a plurality of mounting holes 1, the support body is connected to the rear beam bolts through the mounting holes 1, and the front side of the support body is provided with four mounting holes 2, the mounting holes 2 are fixedly connected to the motor by bolts.

[0013] Furthermore, as a preferred embodiment of the present invention, a structure lightening hole is opened on the surface of the support body, and the structure lightening hole is used in conjunction with the motor.

[0014] Furthermore, as a preferred embodiment of the present invention, an elevator axis hole is opened on one side of the rib characteristic inner cavity, and one end of the elevator rotating shaft connecting rod passes through the inner cavity of the elevator axis hole.

[0015] Furthermore, as a preferred embodiment of the present invention, a cooling hole is provided on the rear side of the support body, and the cooling hole is used in conjunction with the motor.

[0016] Furthermore, as a preferred embodiment of the present invention, the front beam and the rear beam are bonded to the foam sandwich ribs by structural adhesive and bolts.

[0017] Furthermore, as a preferred embodiment of the present invention, an action cylinder is provided on one side of the foam sandwich rib.

[0018] Furthermore, as a preferred embodiment of the present invention, two observation windows are provided through the top of the lower skin.

[0019] Beneficial effects: The technical solution of the present application has the following technical effects: the present invention has the advantages of an integrated horizontal stabilizer structure, multifunctional motor supports, and cooling and elevator shaft design. In actual use, first of all, the horizontal tail adopts the innovative concept of integrated design, which reduces the number of parts, thereby greatly reducing manufacturing costs and shortening production cycles. The integrated design simplifies the docking process between the horizontal tail and the fuselage structure, reduces assembly errors, and improves the overall structural rigidity and aerodynamic efficiency, which not only optimizes the production process, but also ensures the stability and safety of the aircraft during flight.

[0020] Secondly, the motor support and the horizontal stabilizer structure adopt an ingenious fusion design, which not only conforms to the principles of aerodynamics, can significantly reduce the resistance generated by the aircraft during flight and improve flight efficiency, but also cleverly forms a cooling airflow channel, providing the necessary cooling effect for the motor when working, effectively extending the service life of the motor, while reducing the potential failure risk caused by overheating.

[0021] Furthermore, the motor support is endowed with multiple functions in the design. It is not only closely connected to the motor, playing a role of stable support, ensuring the stability and reliability of the motor at high-speed rotation, but the motor support also forms a structural connection with the horizontal tail beam, enhancing the bearing capacity of the horizontal stabilizer, not only optimizing the structural layout, but also improving the overall structural efficiency and safety.

[0022] Finally, the elevator axis holes on the motor mount enable the two elevator main structural surfaces to move simultaneously, which not only simplifies the control system but also reduces the need for a set of servo equipment and motion systems, thereby reducing the overall weight of the horizontal tail structure and the number of moving parts, thereby reducing movement risks and maintenance costs. It not only improves the aircraft's maneuverability but also enhances its ability to cope with complex flight environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0024] Figure 1It is a schematic diagram of the structure of the present invention;

[0025] Figure 2 It is a partial three-dimensional schematic diagram of the horizontal stabilizer structure of the present invention;

[0026] Figure 3 A partial three-dimensional diagram of the motor support of the present invention Figure 1 ;

[0027] Figure 4 A partial three-dimensional diagram of the motor support of the present invention Figure 2 ;

[0028] Figure 5 A partial three-dimensional diagram of the motor support of the present invention Figure 3 ;

[0029] Figure 6 It is a three-dimensional schematic diagram of the local structure of the present invention;

[0030] Figure 7 It is a three-dimensional schematic diagram of the local structure of the elevator assembly of the present invention.

[0031] In the figure, the meanings of the various reference numerals are as follows: 1. horizontal stabilizer structure; 11. upper skin; 12. lower skin; 13. front beam; 14. rear beam; 15. foam sandwich rib; 16. metal joint; 17. motor support; 171. rib feature; 172. mounting hole one; 173. mounting hole two; 174. structural lightening hole; 175. elevator axis hole; 176. cooling hole; 177. support body; 18. actuator; 2. elevator assembly; 21. elevator main structure; 22. elevator fixed joint; 23. elevator connecting rod; 24. elevator servo; 25. elevator rotating shaft connecting rod; 26. elevator rotating shaft joint; 3. motor; 4. observation window. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. In order to better understand the technical content of the present invention, specific embodiments are cited and explained in conjunction with the drawings as follows. Various aspects of the present invention are described in this disclosure with reference to the drawings, which show many illustrative embodiments. It should be understood that the various concepts and embodiments introduced above, as well as those described in more detail below, can be implemented in any of many ways. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0033] As attached Figure 1 To the attached Figure 7As shown: This embodiment provides a horizontal tail structure of an electric aircraft, including: a horizontal stabilizer structure 1, the horizontal stabilizer structure 1 includes an upper skin 11, a lower skin 12 is arranged above the upper skin 11, a front beam 13 and a rear beam 14 are provided through the inner cavity of the upper skin 11 and the lower skin 12, a plurality of foam sandwich ribs 15 are provided between the front beam 13 and the rear beam 14, the front beam 13 and the rear beam 14 are bonded to the foam sandwich ribs 15 by structural adhesive and bolts, a plurality of metal joints 16 are provided on the front side of the rear beam 14, and two motor supports 17 are provided on one side of the upper skin 11 and the lower skin 12.

[0034] Two elevator assemblies 2 are commonly provided on the front sides of the horizontal stabilizer 1 and the elevator assemblies 2 .

[0035] The elevator assembly 2 includes an elevator main structure 21. An elevator servo 24 is provided on one side of the interior of the lower skin 12. An elevator link 23 is provided on one side of the elevator servo 24. An elevator fixed joint 22 is rotatably connected to one side of the elevator link 23. One side of the elevator fixed joint 22 is detachably connected to the upper skin 11 and the lower skin 12 by bolts. Three elevator rotation axis links 25 are rotatably connected to the interior of the elevator main structure 21. The three elevator rotation axis links 25 are detachably connected to each other by bolts. One side of the elevator link 23 is fixedly connected to the elevator rotation axis links 25 on both sides. One end of the elevator rotation axis links 25 on both sides is rotatably connected to an elevator rotation axis joint 26. One side of the elevator rotation axis joint 26 is fixedly connected to the rear beam 14. One end of the middle elevator rotation axis link 25 extends through one side of the motor support 17.

[0036] The motor 3 is disposed in the inner cavity of the motor support 17 , and one side of the motor 3 extends to the outside of the motor support 17 .

[0037] Specifically, the motor support 17 includes a support body 177, and rib features 171 are provided on both sides of the support body 177. A plurality of mounting holes 172 are provided on the rear side of the support body 177, and the support body 177 is bolted to the rear beam 14 through the mounting holes 172. Four mounting holes 173 are provided on the front side of the support body 177, and the mounting holes 173 are fixedly connected to the motor 3 by bolts.

[0038] In this embodiment: through the setting of the motor support 17, the motor support 17 has a structure with rib features 171, which can fit tightly with the upper skin 11 and the lower skin 12, reduce air resistance and improve structural strength, and the horizontal stabilizer structure 1 is connected to the rear beam 14 by bolts, becoming a part of the horizontal stabilizer structure skeleton. The motor support 17 also provides an elevator axis hole 175 through which the elevator rotating shaft connecting rod 25 passes, and is bolted to the rear beam 14 through the mounting hole 172, and is fixed to the motor 3 through the connecting part mounting hole 2 173, thereby fixing the motor 3.

[0039] Specifically, a structure lightening hole 174 is opened on the surface of the support body 177 , and the structure lightening hole 174 is used in conjunction with the motor 3 .

[0040] In this embodiment, the overall weight of the motor support 17 is reduced and the structural strength is improved by providing the structural lightening holes 174 .

[0041] Specifically, an elevator axis hole 175 is defined on one side of the inner cavity of the rib feature 171 , and one end of the elevator rotation shaft connecting rod 25 passes through the inner cavity of the elevator axis hole 175 .

[0042] In this embodiment, the provision of the elevator axis hole 175 provides space for the elevator rotation shaft connecting rod 25 to rotate, and enables the elevator rotation shaft connecting rod 25 to rotate with the center of the elevator axis hole 175 as the axis point.

[0043] Specifically, a cooling hole 176 is opened on the rear side of the support body 177 , and the cooling hole 176 is used in conjunction with the motor 3 .

[0044] In this embodiment, through the provision of the cooling holes 176 , when the aircraft flies forward, airflow will enter the inner cavity of the motor support 17 through the cooling holes 176 and eventually flow to the motor 3 , thereby achieving the purpose of cooling the motor 3 .

[0045] Specifically, an operating cylinder 18 is provided on one side of the foam core rib 15 .

[0046] In this embodiment, the setting of the operating cylinder 18 provides space for the movement of the elevator link 23 and the elevator servo 24.

[0047] Specifically, two observation windows 4 are provided through the top of the lower skin 12 .

[0048] In this embodiment, the observation window 4 is provided to facilitate the user to observe the interior of the horizontal stabilizer 1 through the actuating cylinder 18 , thereby facilitating the user to understand the internal conditions of the horizontal stabilizer 1 .

[0049] The working principle and use process of the present invention:

[0050] Step 1: The upper skin 11 and the lower skin 12 are bonded together with structural adhesive, and the front beam 13, the rear beam 14 and the foam sandwich ribs 15 are bonded together with structural adhesive and bolted together to form the horizontal stabilizer skeleton. The motor support 17 is connected to the rear beam 14 and connected to the horizontal stabilizer structure 1 and the elevator assembly 2 with rivets and structural adhesive. These structures are tightly connected together to form the skeleton and overall structure of the horizontal stabilizer.

[0051] Step 2: The motor support 17 has a ribbed structure 171 that can fit tightly with the upper and lower skins 11, 12, reducing air resistance and increasing structural strength. The horizontal stabilizer structure 1 is connected to the rear beam 14 via bolts, becoming part of the horizontal stabilizer structure skeleton. The motor support 17 also provides an elevator axis hole 175 for the elevator shaft connecting rod 25 to pass through. The motor support 17 is bolted to the rear beam 14 via mounting hole 172 and is fixed to the motor 3 via mounting hole 2 173 of the connecting portion.

[0052] Step 3: A cooling hole 176 is opened on one side of the support body 177. When the aircraft flies forward, air flows through the cooling hole 176 into the inner cavity of the motor support 17 and eventually flows to the motor 3, thereby cooling the motor 3.

[0053] Step 4: An elevator servo 24 is installed inside the lower skin 12. The elevator servo 24 is connected to the elevator main structure 21 via the elevator connecting rod 23 and the elevator fixed joint 22. The elevator rotation axis is formed by three elevator rotation shaft connecting rods 25. The elevator rotation shaft connecting rods 25 are connected by bolts and fixed to the elevator rotation shaft joint 26. The middle elevator rotation shaft connecting rod 25 passes through the elevator axis hole 175 on the motor support 17 and is then connected to the elevator rotation shaft joint 26 to form a complete elevator rotation system. When the aircraft needs to adjust its flight attitude, the elevator servo 24 receives a control signal and drives the elevator link 23 to move. The elevator link 23 drives the elevator fixed joint 22 to swing. The elevator fixed joint 22 drives the elevator main structure 21 to rotate about the center of the elevator rotating shaft link 25, thereby driving the entire elevator main structure 21 to rotate around the rotation axis of the elevator rotating shaft link 25. This rotation changes the direction and magnitude of the lift generated by the horizontal stabilizer, thereby achieving control of the aircraft's ascent and descent.

[0054] It should be noted that, in this document, relational terms such as first and second, etc. are merely used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations.

[0055] While the present invention has been disclosed above with reference to preferred embodiments, this is not intended to limit the present invention. Persons skilled in the art will readily appreciate that various modifications and variations can be made without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention shall be determined by the claims.

Claims

1. A horizontal tail structure for an electric aircraft, characterized by: include: A horizontal stabilizing structure (1), the horizontal stabilizing structure (1) comprising an upper skin (11), a lower skin (12) being provided above the upper skin (11), a front beam (13) and a rear beam (14) being provided through the inner cavities of the upper skin (11) and the lower skin (12), a plurality of foam sandwich ribs (15) being provided between the front beam (13) and the rear beam (14), a plurality of metal joints (16) being provided on the front side of the rear beam (14), and two motor supports (17) being provided on one side of the upper skin (11) and the lower skin (12); Two elevator assemblies (2) are commonly provided on the front sides of the horizontal stabilizer structure (1) and the elevator assembly (2); The elevator assembly (2) includes an elevator main structure (21), an elevator servo (24) is provided on one side of the inner cavity of the lower skin (12), an elevator connecting rod (23) is provided on one side of the elevator servo (24), one side of the elevator connecting rod (23) is rotatably connected to an elevator fixed joint (22), one side of the elevator fixed joint (22) is detachably connected to the upper skin (11) and the lower skin (12) through bolts, and the inner cavity of the elevator main structure (21) is rotatably connected to three elevators. A rudder rotation shaft connecting rod (25), wherein the three elevator rotation shaft connecting rods (25) are detachably connected by bolts, one side of the elevator rotation shaft connecting rod (23) is fixedly connected to the elevator rotation shaft connecting rods (25) on both sides, one end of the elevator rotation shaft connecting rods (25) on both sides is rotatably connected to an elevator rotation shaft joint (26), one side of the elevator rotation shaft joint (26) is fixedly connected to the rear beam (14), and one end of the middle elevator rotation shaft connecting rod (25) passes through one side of the motor support (17); The inner cavity of the motor support (17) is provided with a motor (3), and one side of the motor (3) extends to the outside of the motor support (17).

2. The horizontal tail structure of an electric aircraft according to claim 1, characterized in that: The motor support (17) includes a support body (177), both sides of the support body (177) are provided with rib features (171), the rear side of the support body (177) is provided with a plurality of mounting holes (172), the support body (177) is bolted to the rear beam (14) through the mounting holes (172), and the front side of the support body (177) is provided with four mounting holes (173), the mounting holes (173) are fixedly connected to the motor (3) through bolts.

3. The horizontal tail structure of an electric aircraft according to claim 2, characterized in that: A structural lightening hole (174) is provided on the surface of the support body (177), and the structural lightening hole (174) is used in conjunction with the motor (3).

4. The horizontal tail structure of an electric aircraft according to claim 2, characterized in that: An elevator axis hole (175) is provided on one side of the inner cavity of the rib feature (171), and one end of the elevator rotation shaft connecting rod (25) passes through the inner cavity of the elevator axis hole (175).

5. The horizontal tail structure of an electric aircraft according to claim 2, characterized in that: A cooling hole (176) is provided on the rear side of the support body (177), and the cooling hole (176) is used in conjunction with the motor (3).

6. The horizontal tail structure of an electric aircraft according to claim 1, characterized in that: The front beam (13) and the rear beam (14) are bonded to the foam sandwich ribs (15) through structural adhesive and bolts.

7. The horizontal tail structure of an electric aircraft according to claim 1, characterized in that: An actuating cylinder (18) is provided on one side of the foam sandwich rib (15).

8. The horizontal tail structure of an electric aircraft according to claim 1, characterized in that: Two observation windows (4) are provided through the top of the lower skin (12).

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