An eVTOL aircraft motor arm structure and an eVTOL aircraft

Abstract

An eVTOL aircraft motor arm structure and an eVTOL aircraft relate to the technical field of aircraft, and the motor arm structure comprises a framework and a skin. The upper part of the front part of the framework is provided with a wing butt joint groove, and the part of the framework close to the rear end is used for connecting a tail wing. The skin is provided with a corresponding wing butt joint groove opening and a tail wing butt joint. The cavity surrounded by the framework and the skin comprises a battery cabin, a lift motor cavity and a thrust motor cavity. The battery cabin is a lower opening structure, the lower surface of the skin is provided with a corresponding battery cabin opening, and the upper surface and the lower surface of the skin corresponding to the lift motor cavity are respectively provided with a lift motor mounting port and a heat dissipation hole. The framework and the skin constitute a double transmission path, which improves the carrying capacity, load transmission efficiency and safety and reliability of the motor arm structure. The lower opening battery cabin can be directly operated from the outside of the motor arm when the battery pack is loaded and unloaded, improving the operation convenience. The downwash airflow of the lift propeller is used for heat dissipation of the lift motor, and no additional heat dissipation device is needed, reducing the weight.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, specifically to an eVTOL (Electric Vertical Take Off and Landing) aircraft motor arm structure and an eVTOL aircraft. Background Technology

[0002] Currently, eVTOL aircraft motor arm structures are mainly divided into rigid shell structures and skeleton structures. Rigid shell structures rely primarily on the outer shell to bear the load, while skeleton structures bear the main load through the frame, with the outer skin serving aerodynamic shaping purposes. The motors for the lift unit are installed on the motor arm, and some motor arm structures also integrate battery packs to shorten the length of the power harness. Existing motor arm structures have several shortcomings: the motor arm lacks redundant force transmission paths, resulting in low load transfer efficiency, and damage to any part can easily lead to overall structural failure; battery pack installations often use enclosed structures, making maintenance and operation inconvenient; motor cooling requires additional cooling devices, increasing structural weight; existing motor arms are mostly structures that only connect to the wing, with few designs capable of simultaneously connecting to both the wing and tail. Because the motor arm must withstand the tension, bending moment, and vibration generated by the lift unit, the stress is complex. Structural failure can cause the eVTOL aircraft to lose lift during vertical takeoff and landing, leading to a crash. Therefore, the design of the motor arm structure is crucial for flight safety. Utility Model Content

[0003] In view of this, the purpose of this application is to provide an eVTOL aircraft motor arm structure and an eVTOL aircraft to solve at least one of the above-mentioned technical problems.

[0004] In a first aspect, this application provides an eVTOL aircraft motor arm structure, including a frame and a skin; along the length of the motor arm, the upper front part of the frame is provided with a wing docking groove for connecting the wing, the part of the frame near the rear end is used to connect the tail fin, the skin is provided with a wing docking groove opening corresponding to the wing docking groove, and both sides of the skin near the rear end are provided with tail fin docking interfaces; the frame and the skin form a cavity, the cavity including at least one battery compartment, at least two lift motor cavities, and one thrust motor cavity along the length of the motor arm, the battery compartment having a bottom opening structure, at least one lift motor cavity being provided on the front and rear sides of the wing docking groove, the thrust motor cavity being located at the rear part along the length of the motor arm and having a rear opening structure, the surface of the skin having a battery compartment opening corresponding to the battery compartment, the upper and lower surfaces of the skin corresponding to each lift motor cavity having lift motor mounting ports and heat dissipation holes respectively, and the rear end face of the skin having a thrust motor mounting port corresponding to the thrust motor cavity.

[0005] In conjunction with the first aspect, in some optional embodiments, the frame includes a battery compartment segment, a lift motor cavity segment, and a thrust motor cavity segment corresponding to the battery compartment, the lift motor cavity, and the thrust motor cavity in the length direction of the motor arm.

[0006] In conjunction with the first aspect, in some optional embodiments, the battery compartment includes a plurality of first reinforcing frames, a plurality of first ordinary frames, a plurality of longitudinal beams, a plurality of first stringers, and a plurality of battery pack connecting seats. The plurality of first reinforcing frames are arranged at intervals along the length direction of the motor arm. The space between each pair of adjacent first reinforcing frames corresponds to a battery compartment and is provided with at least one first ordinary frame. The plurality of longitudinal beams are arranged on the left and right sides of the battery compartment section. Each longitudinal beam extends along the length direction of the motor arm and is connected to each of the first reinforcing frames and each of the first ordinary frames. At least one first stringer is provided on each of the left and right sides of each battery compartment. Each first stringer extends along the length direction of the motor arm and is connected to the first reinforcing frame and the first ordinary frame of the corresponding battery compartment. The plurality of battery pack connecting seats are arranged at intervals on the longitudinal beams along the extension direction of the longitudinal beams. The battery pack connecting seats are used to connect battery packs.

[0007] In conjunction with the first aspect, in some optional embodiments, the space between two adjacent first reinforcing frames is divided into an upper part and a lower part, the upper part being a wing docking slot and the lower part being a battery compartment. Multiple wing connection joints are provided on the adjacent surfaces of the two first reinforcing frames, and the wing connection joints are used to connect with the wing.

[0008] In conjunction with the first aspect, in some optional embodiments, three wing connection joints are provided on each of the adjacent surfaces of the two first reinforcing frames. The three wing connection joints are arranged in an isosceles triangle. The wing connection joints located at the two base angles of the isosceles triangle are provided with a first connection hole whose axis is arranged along the width direction of the motor arm. The other wing connection joint located at the apex angle of the isosceles triangle is provided with a second connection hole whose axis is arranged along the height direction of the motor arm.

[0009] In conjunction with the first aspect, in some optional embodiments, the lift motor cavity section is provided with at least one on the front side and the rear side of the battery compartment section. The lift motor cavity section includes a second reinforcing frame, a plurality of reinforcing half-frames, a plurality of second stringers, and a lift motor mount. The second reinforcing frame is arranged at intervals with the battery compartment section along the length direction of the motor arm. The plurality of reinforcing half-frames are arranged at intervals between the second reinforcing frame and the battery compartment section along the length direction of the motor arm. The plurality of second stringers are arranged corresponding to the left and right sides of the lift motor cavity section. Each second stringer extends along the length direction of the motor arm and is connected to the second reinforcing frame, the plurality of reinforcing half-frames, and the battery compartment section. The lift motor mount is installed on the upper end of the plurality of reinforcing half-frames and connected between the second reinforcing frame and the battery compartment section. The lift motor mount is used to install the lift motor.

[0010] In conjunction with the first aspect, in some optional embodiments, the lifting motor base is provided with a motor mounting port and a plurality of third connecting holes arranged around the motor mounting port, the third connecting holes being used to connect with the lifting motor using fasteners.

[0011] In conjunction with the first aspect, in some optional embodiments, the thrust motor cavity segment includes a thrust motor mount, a plurality of second ordinary frames, and a plurality of third stringers. The thrust motor mount is arranged at intervals with adjacent lift motor cavity segments along the length of the motor arm and is used to mount the thrust motor. The plurality of second ordinary frames are arranged at intervals between the thrust motor mount and adjacent lift motor cavity segments along the length of the motor arm. The plurality of third stringers are arranged around the periphery of the thrust motor cavity segment, and each third stringer extends along the length of the motor arm. At least two third stringers are connected to the thrust motor mount, the plurality of second ordinary frames, and adjacent lift motor cavity segments.

[0012] In conjunction with the first aspect, in some optional embodiments, the thrust motor base has an annular structure and is arranged coaxially with the motor arm. The thrust motor base is provided with a plurality of fourth connecting holes evenly distributed along the circumference. The fourth connecting holes are used to connect with the thrust motor by fasteners.

[0013] Secondly, this application provides an eVTOL aircraft, including the eVTOL aircraft motor arm structure in any of the embodiments of the first aspect described above.

[0014] Based on the above technical solutions, the eVTOL aircraft motor arm structure and eVTOL aircraft provided in this application have the following beneficial effects: The motor arm structure is designed with wing docking slots and tail docking interfaces for connection with the wings and tail; the frame and skin of the motor arm structure form a dual force transmission path, and when one force transmission path is damaged, the remaining structure still has high structural strength to ensure safety. This structural design improves the load-bearing performance, load transfer efficiency, and safety reliability of the motor arm structure; the motor arm structure is designed with a battery compartment for battery pack installation, which can reduce the length of the eVTOL aircraft's power supply line and reduce the weight of the eVTOL aircraft. Furthermore, when the battery compartment has a bottom-opening structure, the battery pack can be directly operated from the outside of the motor arm during loading and unloading, improving operational convenience; the lower surface of the skin is provided with heat dissipation holes corresponding to the lift motor cavity, utilizing the downwash airflow of the lift propeller to dissipate heat from the lift motor, eliminating the need for additional heat dissipation devices and reducing the weight of the motor arm structure. Attached Figure Description

[0015] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram showing the position of an eVTOL aircraft motor arm structure on an eVTOL aircraft, as provided in an embodiment of this application.

[0017] Figure 2 This is a top-view structural diagram of an eVTOL aircraft motor arm structure provided in an embodiment of this application.

[0018] Figure 3 This is a bottom view structural diagram of an eVTOL aircraft motor arm provided in an embodiment of this application.

[0019] Figure 4 This is a cross-sectional schematic diagram of the motor arm of an eVTOL aircraft at the battery compartment, provided as an embodiment of this application.

[0020] Figure 5 This is a schematic diagram of a skeleton provided in an embodiment of this application.

[0021] Figure 6 This is a structural schematic diagram of a longitudinal beam and a battery pack connector provided in an embodiment of this application.

[0022] Figure 7 This is a structural schematic diagram of a first reinforcing frame and a wing connection joint provided in an embodiment of this application.

[0023] Figure 8 This is a schematic diagram of the structure of a lift motor cavity provided in an embodiment of this application.

[0024] Figure 9 This is a partial structural diagram of a thrust motor cavity section provided in an embodiment of this application.

[0025] Figure 10 This is a schematic diagram of the structure of a second general frame provided in an embodiment of this application.

[0026] Figure 11 This is a cross-sectional schematic diagram of a skin provided in an embodiment of this application.

[0027] Reference numerals: 100, eVTOL aircraft motor arm structure; 10, frame; 11, battery compartment section; 111, first reinforcing frame; 112, first ordinary frame; 113, longitudinal beam; 114, first stringer; 115, battery pack connector; 116, wing connector; 1161, first connecting hole; 1162, second connecting hole; 12, lift motor cavity section; 121, second reinforcing frame; 122, reinforcing half-frame; 123, second stringer; 124, lift motor mount; 1241, motor mounting port; 1242, third connecting hole; 13, thrust motor cavity section; 131 1311 Thrust motor mount; 132 Second ordinary frame; 1321 Long stringer bayonet; 133 Third long stringer; 14 Wing docking slot; 15 Battery compartment; 16 Lift motor cavity; 17 Thrust motor cavity; 20 Skin; 21 Wing docking slot opening; 22 Tail fin docking interface; 23 Battery compartment opening; 24 Lift motor mounting port; 25 Heat dissipation hole; 26 Thrust motor mounting port; 27 Skin body; 28 Lift motor port cover; 29 Thrust motor port cover; 200 Wing; 300 Tail fin; 1000 eVTOL aircraft. Detailed Implementation

[0028] The specific embodiments of this application will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely some, and not all, of the embodiments of this application. Based on the description of this application, various other embodiments obtained by those skilled in the art without inventive effort are all within the scope of protection of this application.

[0029] In the description of this application, unless otherwise expressly specified and limited, the terms "connection," "setup," "installation," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0030] The terms “upper,” “lower,” “left,” “right,” “front,” “back,” “center,” “top,” “bottom,” “inner,” “outer,” “vertical,” “horizontal,” “clockwise,” “counterclockwise,” “axial,” “radial,” and “circumferential” indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product is in use. They are used only for the convenience of description and simplification, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0031] The terms “first,” “second,” “third,” etc., are used only to distinguish elements with similar properties, and do not indicate or imply relative importance or a specific order, unless otherwise explicitly stated or limited.

[0032] The terms “comprising,” “including,” “having,” or any other variations thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase “comprising one…” does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0033] The term "multiple" means two or more (including two).

[0034] The term "and / or" describes the relationship between related objects, indicating that there can be three relationships. For example, A and / or B can represent three cases: A exists alone, A and B exist simultaneously, and B exists alone.

[0035] The terms "an embodiment," "as an example," and "in one implementation" refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which may be included in at least one embodiment or example of this application. These illustrative expressions do not necessarily refer to the same embodiment, nor are they independent or alternative embodiments mutually exclusive with other embodiments. Where there is no conflict, the embodiments and features described in these embodiments can be combined in a suitable manner.

[0036] The following is combined with Figures 1 to 11 This paper provides a detailed description of the motor arm structure of an eVTOL aircraft and the eVTOL aircraft itself. It should be noted that the "front" and "rear" markings in the diagram correspond to the length direction of the motor arm, "left" and "right" correspond to the width direction, and "up" and "down" correspond to the height direction.

[0037] like Figure 1As shown in the illustration, this application provides an eVTOL aircraft motor arm structure 100 (hereinafter referred to as "motor arm"), which is an inwardly located motor arm in the wingspan direction of the eVTOL aircraft 1000, used to connect the wing 200 and the tail 300, and to mount the battery pack, lift unit, and thrust unit. Specifically, the motor arm can support the tail 300, bear the load transmitted by the tail 300 and the loads of the lift unit and thrust unit, and transmit these loads to the wing 200. At the same time, the motor arm serves as a mounting frame for the battery pack, the lift motor of the lift unit, and the thrust motor of the thrust unit, ensuring that the components are installed firmly and reliably.

[0038] like Figure 2 and Figure 3 As shown, the motor arm includes a frame 10 and a skin 20. The frame 10 has a wing docking groove 14 for connecting the wing 200 on the upper part of the front section in the length direction of the motor arm, and the skin 20 has a wing docking groove opening 21 corresponding to the wing docking groove 14. The frame 10 has left and right (in the width direction) sides near the rear end in the length direction of the motor arm for connecting the tail fin 300, and the skin 20 has a tail fin docking interface 22 on each of the left and right sides near the rear end in the length direction of the motor arm. The frame 10 and the skin 20 form a cavity, which includes at least one battery compartment 15, at least two lift motor cavities 16, and one thrust motor cavity 17 in the length direction of the motor arm.

[0039] Among them, such as Figure 3 and Figure 4 As shown, the battery compartment 15 has a bottom-opening structure, and the surface of the skin 20 has a battery compartment opening 23 corresponding to the battery compartment 15. The lower surface of the battery pack adopts a pneumatic design. When the battery pack is installed in the battery compartment 15, the lower surface of the battery pack and the skin 20 together form a pneumatic surface. Since there is no need to install a battery compartment cover, the battery pack can be loaded and unloaded directly from the outside of the motor arm, improving operational convenience.

[0040] At least one lift motor cavity 16 is provided on both the front and rear sides of the wing docking slot 14. Each lift motor cavity 16 has an open structure at both the top and bottom. The upper surface of the skin 20 has a lift motor mounting port 24 corresponding to the lift motor cavity 16, and the lower surface of the skin 20 has heat dissipation holes 25 corresponding to the lift motor cavity 16. The lift motor is an air-cooled motor. Compared with liquid-cooled motors, air-cooled motors can effectively reduce weight. When the lift propeller rotates, the downwash airflow generated by the lift propeller flows over the surface of the lift motor and then flows out through the heat dissipation holes 25, thereby achieving heat dissipation for the lift motor.

[0041] The thrust motor cavity 17 is located at the rear of the motor arm along its length. The thrust motor cavity 17 has a rear-opening structure. The rear end face of the skin 20 is provided with a thrust motor mounting port 26 corresponding to the thrust motor cavity 17.

[0042] Regarding the number and location of the battery compartment 15 and the lift motor cavity 16, as an example, such as Figure 3 As shown, there are three battery compartments 15, which are arranged sequentially along the length of the motor arm. The middle battery compartment 15 is located below the wing docking slot 14 and its height is about half the height of the motor arm. The other two battery compartments 15 are located on the front and rear sides of the wing docking slot 14 respectively along the length of the motor arm and their heights are similar to the height of the motor arm. There are two lift motor cavities 16, which are located on the front and rear sides of the three battery compartments 15 respectively along the length of the motor arm.

[0043] The structure of the skeleton 10 will be described in detail below.

[0044] like Figure 5 As shown, the frame 10 includes a battery compartment section 11, a lift motor cavity section 12, and a thrust motor cavity section 13 in the length direction of the motor arm, which correspond to the battery compartment 15, the lift motor cavity 16, and the thrust motor cavity 17.

[0045] The battery compartment section 11 includes multiple first reinforcing frames 111, multiple first ordinary frames 112, multiple longitudinal beams 113, multiple first stringers 114, multiple battery pack connectors 115, and multiple wing connectors 116. Specifically, the multiple first reinforcing frames 111 are arranged at intervals along the length of the motor arm, and the space between each two adjacent first reinforcing frames 111 corresponds to a battery compartment 15 and is provided with at least one first ordinary frame 112; the multiple longitudinal beams 113 are arranged on the left and right sides of the battery compartment section 11, each longitudinal beam 113 extends along the length of the motor arm and is connected to each of the first reinforcing frames 111 and each of the first ordinary frames 112; at least one first stringer 114 is provided on each of the left and right sides of each battery compartment 15, each first stringer 114 extends along the length of the motor arm and is connected to the first reinforcing frame 111 and the first ordinary frame 112 of the corresponding battery compartment 15, and the corresponding first stringers 114 of adjacent battery compartments 15 can be connected as one unit (or, replaced by a longer first stringer 114). The space between two adjacent first reinforcing frames 111 is divided into an upper and a lower part. The upper part is the wing docking slot 14, and the lower part is the battery compartment 15. Multiple wing connection joints 116 are provided on adjacent surfaces of these two first reinforcing frames 111. The wing connection joints 116 are used to connect with the motor arm connection joints on the wing 200 to achieve the connection between the motor arm and the wing 200. The load on the motor arm is also transferred to the wing 200 through the wing connection joints 116. Figure 6 As shown, multiple battery pack connectors 115 are arranged at intervals on the inner surface of the longitudinal beam 113 along the extending direction of the longitudinal beam 113, and the battery pack connectors 115 are used to connect the battery pack.

[0046] As an example, such as Figure 5 As shown, there are four first reinforcing frames 111, which are spaced apart along the length of the motor arm. The three spaces between the four first reinforcing frames 111 correspond to three battery compartments 15. The middle space is divided into upper and lower parts: the upper part is the wing docking slot 14, and the lower part is the battery compartment 15. The lower battery compartment 15 contains a first ordinary frame 112 with a ring-shaped semi-frame structure. The other two spaces each contain two first ordinary frames 112 with a downward-facing U-shaped structure, which are spaced apart along the length of the motor arm. There are two longitudinal beams 113, which are arranged on the left and right sides of the battery compartment section 11. The inner surface of each longitudinal beam 113 is provided with... There are multiple battery pack connectors 115; there are six first stringers 114, two of which are longer and are arranged on the left and right sides of the battery compartment section 11, connecting to each of the first reinforcing frames 111 and each of the first ordinary frames 112. The other four first stringers 114 are shorter, with one on each side of the two battery compartments 15 on the front and rear sides of the wing docking slot 14. These four first stringers 114 are connected to the corresponding first reinforcing frames 111 and first ordinary frames 112. Among the four first reinforcing frames 111, the two middle first reinforcing frames 111 each have three wing connection joints 116 on their adjacent surfaces, such as... Figure 7 As shown, the three wing connection joints 116 are arranged in an isosceles triangle. The wing connection joints 116 located at the two base corners of the isosceles triangle are provided with first connection holes 1161 with their axes arranged along the width direction of the motor arm. The other wing connection joint 116 located at the apex of the isosceles triangle is provided with a second connection hole 1162 with its axis arranged along the height direction of the motor arm. That is to say, the axis of each first connection hole 1161 is perpendicular to or perpendicular to the axis of the second connection hole 1162. This arrangement can play a role in resisting torsion. Specifically, the load of the tail fin 300, the load of the lift unit, and the load of the thrust unit on the motor arm are mainly transmitted to the wing 200 through the wing connection joints 116 located at the two base corners of the isosceles triangle. When the motor arm generates torsional force due to the failure of the lift propeller of a certain lift unit, the torsional force is mainly transmitted to the wing 200 through the wing connection joint 116 located at the apex of the isosceles triangle.

[0047] Regarding the materials of the components of the battery compartment section 11: the first reinforcing frame 111, the battery pack connector 115, and the wing connector 116, which are the main force transmission components, can be made of metal materials. Metal materials have good load-bearing capacity and processing performance, and can effectively improve the service life of these components. Since the longitudinal beam 113 is relatively long and bears the main load in the length direction of the motor arm, in order to reduce weight while ensuring load-bearing capacity, the longitudinal beam 113 can be made of carbon fiber composite material. Carbon fiber composite material has good molding performance and lightweight performance. The first ordinary frame 112 and the first stringer 114, which are the secondary force transmission components, can be made of metal materials or carbon fiber composite materials.

[0048] As an example, the first reinforcing frame 111 and the wing connecting joint 116 are made of Ti6Al4V titanium alloy, which has good fatigue performance and corrosion resistance and can withstand harsh vibration environments; the battery pack connecting seat 115 is made of aluminum alloy and is fitted with a steel bushing, which takes into account lightweight, durability and ease of maintenance, and can meet the needs of frequent maintenance and replacement of battery packs; the first ordinary frame 112 and the first stringer 114 are both made of aluminum alloy, which has good formability and low cost.

[0049] like Figure 5 and Figure 8 As shown, the lift motor cavity section 12 is provided on the front side and the rear side of the battery compartment section 11. Each lift motor cavity section 12 includes a second reinforcing frame 121, a plurality of reinforcing half-frames 122, a plurality of second stringers 123, and a lift motor base 124. Specifically, the second reinforcing frame 121 is spaced apart from the adjacent first reinforcing frame 111 along the length of the motor arm; multiple reinforcing half-frames 122 are spaced apart between the second reinforcing frame 121 and the adjacent first reinforcing frame 111 along the length of the motor arm, each reinforcing half-frame 122 having an upward-opening U-shaped structure with multiple reinforcing ribs distributed thereon; multiple second stringers 123 are arranged corresponding to the left and right sides of the lifting motor cavity section 12, each second stringer 123 having an arc shape and extending along the length of the motor arm, each second stringer 123 being connected to the second reinforcing frame 121, the multiple reinforcing half-frames 122, and the adjacent first reinforcing frame 111; the lifting motor base 124 is installed on the upper end of the multiple reinforcing half-frames 122 and connected between the second reinforcing frame 121 and the adjacent first reinforcing frame 111, the lifting motor base 124 having a motor mounting port 1241 and multiple third connecting holes 1242 arranged around the motor mounting port 1241, the third connecting holes 1242 being used to connect with the lifting motor using fasteners.

[0050] As an example, such as Figure 5 As shown, the number of lifting motor cavity sections 12 is two; as Figure 8As shown, in each lift motor cavity section 12, there are two reinforcing half-frames 122 and two second stringers 123.

[0051] Regarding the materials of the components of the lift motor cavity section 12: the second reinforcing frame 121, the reinforcing half-frame 122, and the lift motor base 124 may be made of metal; the second stringer 123 may be made of metal or carbon fiber composite material. As an example, the second reinforcing frame 121, the reinforcing half-frame 122, and the lift motor base 124 are made of Ti6Al4V titanium alloy; the second stringer 123 is made of aluminum alloy.

[0052] like Figure 5 As shown, the thrust motor cavity section 13 is located behind the rearmost lift motor cavity section 12 along the length of the motor arm. The thrust motor cavity section 13 includes a thrust motor mount 131, multiple second general frames 132, and multiple third stringers 133. Specifically, the thrust motor mount 131 is spaced apart from the adjacent second reinforcing frames 121 along the length of the motor arm, as shown... Figure 9 As shown, the thrust motor base 131 has a circular structure and is arranged coaxially with the motor arm. The thrust motor base 131 has multiple fourth connecting holes 1311 evenly distributed circumferentially. These fourth connecting holes 1311 are used to connect with the thrust motor using fasteners. Multiple second ordinary frames 132 are arranged at intervals along the length of the motor arm between the thrust motor base 131 and adjacent second reinforcing frames 121. Figure 10 As shown, each second ordinary frame 132 has a rounded rectangular frame structure; multiple third stringers 133 are arranged around the thrust motor cavity section 13, each third stringer 133 extends along the length of the motor arm, and at least two third stringers 133 are connected to the thrust motor base 131, multiple second ordinary frames 132 and adjacent second reinforcing frames 121.

[0053] As an example, such as Figure 5 As shown, there are four second ordinary frames 132. The cross-sectional dimensions of the four second ordinary frames 132 gradually decrease from front to back along the length of the motor arm, as shown in the figure. Figure 10As shown, each of the second ordinary frames 132 has two stringer slots 1321 on its left and right sides for connecting with the third stringer 133. The lower side of the second ordinary frame 132 has a stringer slot 1321 in the center for connecting with the third stringer 133. There are five third stringers 133, three of which are longer and are arranged on the left, right and lower sides of the thrust motor cavity section 13, respectively, and are connected to the thrust motor mount 131, the four second ordinary frames 132, and the adjacent second reinforcing frame 121. The other two third stringers 133 are shorter and are arranged on the left and right sides of the thrust motor cavity section 13, respectively, and are connected to the first three second ordinary frames 132 and the adjacent second reinforcing frame 121. The left and right sides of these two third stringers 133 and the last second ordinary frame 132 are used to connect to the tail fin 300. The curvature of the five third stringers 133 is small, which can effectively transfer the load of the tail fin 300.

[0054] like Figure 2 and Figure 3 As shown, the skin 20 covers the frame 10 and is fixedly connected to the frame 10. The skin 20 includes a skin body 27, at least two lift motor port covers 28, and one thrust motor port cover 29. Specifically, combined with Figure 5 and Figure 11 The skin body 27 is integrally formed with the first stringer 114, the second stringer 123, and the third stringer 133 of the frame 10 through co-curing or co-gelling molding, and is connected to the first reinforcing frame 111, the longitudinal beam 113, the second reinforcing frame 121, the reinforcing half-frame 122, the lift motor mount 124, and the thrust motor mount 131 of the frame 10. The first ordinary frame 112 and the second ordinary frame 132 of the frame 10 provide support for the skin body 27 to prevent instability. The lift motor port cover 28 corresponds one-to-one with the lift motor cavity 16. Each lift motor port cover 28 has a lift motor mounting port 24. The lift motor port cover 28 adopts a modular structure for easy disassembly for daily maintenance of the lift motor. For example, Figure 2 As shown, each lifting motor port cover 28 is divided into front and rear sections along the length of the motor arm; the thrust motor port cover 29 is arranged corresponding to the thrust motor cavity 17.

[0055] The skin body 27 also adopts a segmented structure to meet the differentiated needs of different areas of the motor arm in terms of stress characteristics, material formability, and connection structure. For example, Figure 2 and Figure 3 As shown, combined with Figure 5The skin body 27 is divided into multiple sections corresponding to the battery compartment section 11, lift motor cavity section 12, and thrust motor cavity section 13 of the frame 10. Anti-peeling studs (not shown in the figure) can be installed at locations where the skin body 27 is prone to detachment from the first stringer 114, second stringer 123, and third stringer 133 to ensure a secure connection between the skin body 27 and these stringers. The skin 20 can be made of carbon fiber composite material, which has good molding performance, lightweight performance, and force transmission performance. Fairings (not shown in the figure) can also be installed at locations such as the wing docking slot opening 21 and the tail fin docking interface 22 of the skin 20 to improve aerodynamic performance.

[0056] This application also provides an eVTOL aircraft 1000, such as... Figure 1 As shown, the eVTOL aircraft 1000 includes a fuselage, wings 200, tail 300, and the aforementioned eVTOL aircraft motor arm structure 100, which is connected to the wings 200 and tail 300.

[0057] In summary, the eVTOL aircraft motor arm structure and eVTOL aircraft provided in this application embodiment have the following beneficial effects: the motor arm structure is designed with wing docking slots and tail docking interfaces for connection with the wings and tail; the frame and skin of the motor arm structure form a dual force transmission path, so that when one force transmission path is damaged, the remaining structure still has high structural strength to ensure safety. This structural design improves the load-bearing capacity, load transfer efficiency, and safety reliability of the motor arm structure; the motor arm structure is designed with a battery compartment for battery pack installation, which can reduce the length of the eVTOL aircraft's power supply line and reduce the weight of the eVTOL aircraft. Furthermore, when the battery compartment has a bottom-opening structure, the battery pack can be installed and removed directly from the outside of the motor arm, improving operational convenience; the lower surface of the skin is provided with heat dissipation holes corresponding to the lift motor cavity, using the downwash airflow of the lift propeller to dissipate heat from the lift motor, eliminating the need for additional heat dissipation devices and reducing the weight of the motor arm structure.

[0058] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any person skilled in the art can easily conceive of various variations or substitutions within the technical scope disclosed in this application, and these should all be included within the scope of protection of this application.

Claims

1. A motor arm structure for an eVTOL aircraft, characterized in that, Including the skeleton and skin; Along the length of the motor arm, the upper part of the front section of the frame is provided with a wing docking groove for connecting the wing, the part of the frame near the rear end is used to connect the tail fin, the skin is provided with a wing docking groove opening corresponding to the wing docking groove, and the skin is provided with tail fin docking interfaces on both sides near the rear end. The frame and the skin form a cavity, which includes at least one battery compartment, at least two lift motor cavities, and one thrust motor cavity along the length of the motor arm. The battery compartment has a bottom opening structure. At least one lift motor cavity is provided on the front and rear sides of the wing docking slot. The thrust motor cavity is located at the rear of the motor arm and has a rear opening structure. The surface of the skin has a battery compartment opening corresponding to the battery compartment. The upper and lower surfaces of the skin corresponding to each lift motor cavity have lift motor mounting ports and heat dissipation holes, respectively. The rear end face of the skin has a thrust motor mounting port corresponding to the thrust motor cavity.

2. The eVTOL aircraft motor arm structure according to claim 1, characterized in that, The frame includes a battery compartment segment, a lift motor cavity segment, and a thrust motor cavity segment corresponding to the battery compartment, the lift motor cavity, and the thrust motor cavity in the length direction of the motor arm.

3. The eVTOL aircraft motor arm structure according to claim 2, characterized in that, The battery compartment includes multiple first reinforcing frames, multiple first ordinary frames, multiple longitudinal beams, multiple first stringers, and multiple battery pack connecting seats. The multiple first reinforcing frames are arranged at intervals along the length of the motor arm. The space between each pair of adjacent first reinforcing frames corresponds to one battery compartment and is provided with at least one first ordinary frame. The multiple longitudinal beams are arranged on the left and right sides of the battery compartment section. Each longitudinal beam extends along the length of the motor arm and is connected to each of the first reinforcing frames and each of the first ordinary frames. At least one first stringer is provided on each of the left and right sides of each battery compartment. Each first stringer extends along the length of the motor arm and is connected to the first reinforcing frame and the first ordinary frame corresponding to the battery compartment. The multiple battery pack connecting seats are arranged at intervals on the longitudinal beams along the extension direction of the longitudinal beams. The battery pack connecting seats are used to connect battery packs.

4. The eVTOL aircraft motor arm structure according to claim 3, characterized in that, The space between two adjacent first reinforcing frames is divided into an upper part and a lower part. The upper part is the wing docking slot and the lower part is the battery compartment. Multiple wing connection joints are provided on the adjacent surfaces of the two first reinforcing frames. The wing connection joints are used to connect with the wing.

5. The eVTOL aircraft motor arm structure according to claim 4, characterized in that, Each of the two first reinforcing frames has three wing connection joints on adjacent surfaces. The three wing connection joints are arranged in an isosceles triangle. The wing connection joints located at the two base angles of the isosceles triangle have a first connection hole with an axis arranged along the width direction of the motor arm. The other wing connection joint located at the apex angle of the isosceles triangle has a second connection hole with an axis arranged along the height direction of the motor arm.

6. The eVTOL aircraft motor arm structure according to claim 2, characterized in that, The lift motor cavity section is provided at least one on the front side and the rear side of the battery compartment section. The lift motor cavity section includes a second reinforcing frame, a plurality of reinforcing half-frames, a plurality of second stringers, and a lift motor base. The second reinforcing frame is arranged at intervals with the battery compartment section along the length direction of the motor arm. The plurality of reinforcing half-frames are arranged at intervals between the second reinforcing frame and the battery compartment section along the length direction of the motor arm. The plurality of second stringers are arranged corresponding to the left and right sides of the lift motor cavity section. Each second stringer extends along the length direction of the motor arm and is connected to the second reinforcing frame, the plurality of reinforcing half-frames, and the battery compartment section. The lift motor base is installed on the upper end of the plurality of reinforcing half-frames and connected between the second reinforcing frame and the battery compartment section. The lift motor base is used to install the lift motor.

7. The eVTOL aircraft motor arm structure according to claim 6, characterized in that, The lifting motor base is provided with a motor mounting port and a plurality of third connecting holes arranged around the motor mounting port. The third connecting holes are used to connect with the lifting motor by fasteners.

8. The eVTOL aircraft motor arm structure according to claim 2, characterized in that, The thrust motor cavity includes a thrust motor mount, multiple second ordinary frames, and multiple third stringers. The thrust motor mount is spaced apart from the adjacent lift motor cavity along the length of the motor arm and is used to mount the thrust motor. The multiple second ordinary frames are spaced apart between the thrust motor mount and the adjacent lift motor cavity along the length of the motor arm. The multiple third stringers are arranged around the periphery of the thrust motor cavity, and each third stringer extends along the length of the motor arm. At least two third stringers are connected to the thrust motor mount, the multiple second ordinary frames, and the adjacent lift motor cavity.

9. The eVTOL aircraft motor arm structure according to claim 8, characterized in that, The thrust motor base has a circular structure and is arranged coaxially with the motor arm. The thrust motor base is provided with a plurality of fourth connecting holes evenly distributed along the circumference. The fourth connecting holes are used to connect with the thrust motor by fasteners.

10. An eVTOL aircraft, characterized in that, Includes the eVTOL aircraft motor arm structure as described in any one of claims 1-9.

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