An eVTOL aircraft tail push motor connecting structure

Abstract

The utility model discloses an eVTOL airplane tail push motor connection structure, and the motor support includes the motor seat of annular structure, is provided with motor on the motor seat, is provided with the propeller on the motor, the motor seat includes the first step, the front end of first step has the second step, and the thickness of first step is greater than the thickness of second table, and the rear end of first step is provided with the motor connection edge of being connected with motor, the inner wall of motor seat has two avoidance grooves, and the outer wall of motor seat is provided with a plurality of connection webs of being connected with first step and second step simultaneously, and the rear half of each connection long web is set up with each connection web one to one and is connected with connection web and second step simultaneously, and the front half of each connection long web is connected with the tail plane on the aircraft body. The utility model has the beneficial effect of improving the broken safety, ensuring the thrust line stability, reducing the flight attitude fluctuation, reducing the maintenance cost, reducing the motor power loss, improving the endurance, reducing the stress of the connecting part and prolonging the service life of the structure.

Description

Technical Field

[0001] This utility model relates to a connection structure, and more specifically, to a connection structure for an eVTOL aircraft tail thruster motor. Background Technology

[0002] eVTOL (electric vertical takeoff and landing) aircraft, with their vertical takeoff and landing capabilities, have freed them from the dependence on long runways and can complete takeoff and landing in limited spaces, significantly improving the flexibility and accessibility of air transport. They are suitable for scenarios such as urban air traffic. They are powered by electricity and emit no pollutants such as carbon dioxide and nitrogen oxides during operation, which is in line with the vision of zero carbon and environmental protection. They are also low in noise, relatively simple in structure, and controllable in operating costs, and have the potential for large-scale commercial application.

[0003] In the power system of eVTOL aircraft, the tail thruster motor provides level flight cruise power by driving the propeller. The reliability of its connection structure directly determines flight safety. If the connection structure fails and thrust is lost, it will lead to power loss. At the same time, the tail thruster motor is affected by the incoming airflow and will be subjected to complex loads such as torque, vibration, and asymmetric bending moment generated by the propeller rotation. This places extremely high demands on the strength, stiffness, and fatigue resistance of the connection structure. In addition, the tail thruster motor connection structure usually uses fasteners. In high-vibration environments, it is necessary to prevent the fasteners from loosening and to carry out inspections and maintenance at fixed intervals (usually 20 flight hours) to ensure timely detection and handling of fastener loosening issues. However, in the existing eVTOL aircraft tail thruster motor connection structure, the fasteners are mostly hidden inside the structure. Inspection requires disassembly of the internal structure, which is cumbersome, difficult to maintain, and makes it difficult to efficiently complete periodic inspections, identify safety hazards in a timely manner, and meet the comprehensive requirements of eVTOL aircraft for connection structure reliability, lightweight, and ease of maintenance.

[0004] Therefore, those skilled in the art are dedicated to providing a connection structure for the tail thruster motor of an eVTOL aircraft that can effectively solve the above-mentioned technical problems. Utility Model Content

[0005] To achieve the above objectives, this utility model provides a connection structure for the tail thrust motor of an eVTOL aircraft, including a motor bracket;

[0006] The motor bracket includes a motor base with a ring structure, on which a motor is mounted, and on which a propeller is mounted;

[0007] The motor base includes a first step, the front end of the first step has a second step, the thickness of the first step is greater than the thickness of the second step, and the rear end of the first step is provided with a motor connection edge for connecting to the motor.

[0008] The inner wall of the motor base has two clearance grooves, and the outer wall of the motor base is provided with a number of connecting ribs that are simultaneously connected to the first step and the second step. The rear half of each connecting girder is provided in correspondence with each of the connecting ribs and is simultaneously connected to the connecting ribs and the second step. The front half of each connecting girder is connected to the flat tail on the machine body.

[0009] Furthermore, there are four connecting ribs and four connecting stringers, each of which is arranged around the center line of the motor base. The motor base is embedded in the flat tail, and there is a gap between the motor base and the flat tail. Structural adhesive is applied to the gap.

[0010] The connecting girder includes a first connecting section and a second connecting section made of an integral molding structure. The first connecting section is connected to the second step and the flat tail simultaneously by a number of fasteners. The rear half of the second connecting section is connected to the connecting rib by a number of fasteners.

[0011] Furthermore, the horizontal tail includes a frame, on which a skin is provided, the skin being made of carbon fiber composite material;

[0012] The frame includes a flat-tail front beam and a flat-tail rear beam. Two second longitudinal beams are respectively provided with a third longitudinal beam and a first longitudinal beam at both ends. The rear ends of each first longitudinal beam are connected by a ring frame. The second longitudinal beam located on the same side is integrally formed with the first longitudinal beam and the third longitudinal beam and passes through the flat-tail front beam and the flat-tail rear beam. The second longitudinal beam is located in the middle section of the frame. The first longitudinal beam and the third longitudinal beam both extend out of the frame. The first connecting section in the connecting girder is connected to both the frame and the first longitudinal beam.

[0013] Furthermore, a plurality of motor connection holes are provided around the motor connection edge, and each bolt is respectively set at each of the motor connection holes and connected to the positioning seat set on the motor.

[0014] Furthermore, the thickness of the first step is 4 mm, and the thickness of the second step is 3 mm.

[0015] Furthermore, the motor connection edge includes a first thickness and a second thickness; the motor connection edge body has the first thickness, and each motor connection hole is respectively opened at the second thickness, the first thickness is 5mm, and the second thickness is 10mm.

[0016] Furthermore, the outer wall of the motor base is provided with a number of reinforcing ribs, and each of the reinforcing ribs is simultaneously connected to the first step, the second step and the motor connecting edge.

[0017] Furthermore, a wire harness clearance hole is provided on the first longitudinal beam.

[0018] Furthermore, both sides of the first longitudinal beam have longitudinal beam connecting edges, and the extension direction of each longitudinal beam connecting edge is consistent with the length direction of the connecting girder, and is simultaneously connected to the skin and the connecting girder.

[0019] Furthermore, the first step, the second step, and the motor connection edge are integrally formed.

[0020] This utility model has the following beneficial effects:

[0021] 1. The utility model adopts four circumferentially arranged connecting trusses to form four independent force transmission paths. Even if a single path is damaged, the remaining paths can still bear the load, meet the structural integrity requirements under limited load, and improve the safety of damage.

[0022] 2. The motor mount uses a stepped transition structure (4mm for the first step and 3mm for the second step) to gradually distribute the load. It is reinforced with connecting ribs and reinforcing ribs to enhance rigidity and avoid local stress concentration. At the same time, the connecting stringer extends to the horizontal tail longitudinal beam to evenly transfer complex loads such as torque and vibration to the horizontal tail frame, ensuring the stability of the thrust line and reducing flight attitude fluctuations.

[0023] 3. Fasteners are exposed on the outside of the connecting stringer, allowing for direct visual inspection without disassembling the internal structure. This enables the rapid detection of potential problems such as loose bolts and cracks, significantly reducing the time and difficulty of routine inspections during 20 flight hours. The motor bracket and horizontal stabilizer are connected with detachable fasteners. A 0.3mm gap is reserved between the motor mount and the horizontal stabilizer and coated with structural adhesive, which eliminates the influence of machining tolerances and facilitates the replacement and repair of the motor and connecting stringer in the future, reducing maintenance costs.

[0024] 4. The non-hole area of ​​the motor connection edge is 5mm thick, and the area around the hole is 10mm thick. This reduces redundant weight while meeting the stress requirements of the hole edge. The connecting stringer and the motor base work together to improve the overall rigidity, reduce the thickness requirement of the motor base, and further reduce weight.

[0025] 5. The motor mount and connecting stringer are made of 2024-T351 aluminum alloy (high fatigue performance). While ensuring strength, it significantly reduces weight compared to traditional metal structures, reduces motor power loss, and improves range.

[0026] 6. The inner wall of the motor base is designed with a clearance groove to avoid the raised structure of the flat tail and avoid assembly interference; the first longitudinal beam has a wire harness clearance hole to meet the bending radius requirements of the wire harness, ensuring that the wire harness is arranged in an orderly manner inside the flat tail and preventing friction damage between the structure and the cable; the motor base and the flat tail are connected by structural adhesive and fasteners to improve sealing and connection stability; the fasteners adopt a double gasket design to prevent scratches on the structural surface during installation, while increasing the contact area, reducing stress at the connection points, and extending the service life of the structure. Attached Figure Description

[0027] Figure 1 This is a structural schematic diagram of a specific embodiment of the present invention.

[0028] Figure 2 yes Figure 1 A magnified schematic diagram of the structure at point A in the middle.

[0029] Figure 3 This is an exploded structural diagram of the tail thruster motor connection structure in this utility model.

[0030] Figure 4 yes Figure 3 A magnified schematic diagram of the structure at point B in the middle.

[0031] Figure 5 This is a schematic diagram of the skeleton structure in this utility model.

[0032] Figure 6 This is a schematic diagram of the structure in this utility model where the motor is connected to the flat tail via a motor mount.

[0033] Figure 7 yes Figure 6 A magnified schematic diagram of the structure at point C.

[0034] Figure 8 This is an exploded structural diagram of the motor bracket of this utility model.

[0035] Figure 9 This is a three-dimensional structural diagram of the motor bracket of this utility model.

[0036] Figure 10 This is a three-dimensional structural diagram of the motor base in this utility model.

[0037] Figure 11 This is a schematic diagram of the structure of the first longitudinal beam in this utility model.

[0038] Figure 12 This is a structural diagram showing the use of the frame and motor bracket and other components.

[0039] Figure 13 yes Figure 12 A magnified schematic diagram of the structure at point D.

[0040] Figure 14 yes Figure 12 A structural diagram showing the skin is provided.

[0041] Figure 15 yes Figure 14 A magnified schematic diagram of the structure at point E in the middle.

[0042] Figure 16 This is a cross-sectional view of the fastener connection between the motor base and the connecting stringer in this utility model.

[0043] Figure 17 This is a schematic cross-sectional view of the connection structure of the connecting truss at the rear beam of the flat tail in this utility model.

[0044] The attached diagram lists the components represented by each number as follows:

[0045] 11. Motor bracket; 12. Flat tail; 13. Motor; 52. Motor connection hole; 53. Bolt; 55. Positioning seat; 111. Motor base; 112. Connecting stringer; 113. Fastener; 121. Skin; 122. Frame; 1111. Motor connection edge; 1112. Connecting rib; 1113. Reinforcing rib; 1114. First step; 1115. Second step; 1116. Clearance groove; 112a. First connecting section; 112b. Second... Connecting section; 1131, Bolt; 1132, Nut; 1133, Washer; 1221, First longitudinal beam; 1222, Second longitudinal beam; 1223, Third longitudinal beam; 1224, Front beam of the tail section; 1226, Ring frame; 1288, Rear beam of the tail section; 13a, Propeller; 100, Fuselage; 530, Protruding structure; 800, Tail thruster motor connection structure; 12211, Wiring harness clearance hole; 12212, Longitudinal beam connecting edge; 1115a, Connecting hole. Detailed Implementation

[0046] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0047] In the description of this utility model, it should be noted that the terms "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this utility model and simplifying the description, 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 utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0048] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "setting," and "connection" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0049] This utility model discloses a tail thrust motor connection structure for an eVTOL aircraft, which is arranged at the tail of the eVTOL aircraft and connected to the horizontal stabilizer 12. A propeller 13a is mounted at the rear of the motor 13. In actual use, tail thrust motor connection structures 800 are arranged on both sides of the eVTOL aircraft (see [reference]). Figure 1 As shown in the diagram, the structure is symmetrical. This utility model is described using only one example, while the other structure is similar. The tail thrust motor connection structure 800 installs the motor 13 to the tail of the eVTOL. The vibration, thrust, and asymmetric bending moment generated by the propeller 13a and the motor 13 are transmitted to the eVTOL aircraft, enabling the eVTOL aircraft to cruise during level flight.

[0050] like Figures 1 to 17 As shown, an eVTOL aircraft tail thruster motor connection structure includes a motor bracket 11;

[0051] The motor bracket 11 includes a motor base 111 with an annular structure, on which a motor 13 is mounted, and on which a propeller 13a is mounted. In this utility model, as a further preferred embodiment, the outer ring of the motor 13 is not larger than the root of the heat dissipation fins of the motor 13. With the above arrangement, the airflow at the front of the heat dissipation fins of the motor 13 can be prevented from being blocked, thereby improving the heat dissipation effect of the motor 13.

[0052] The motor mount 111 includes a first step 1114, the front end of the first step 1114 has a second step 1115, the thickness of the first step 1114 is greater than the thickness of the second step 1115, and the rear end of the first step 1114 is provided with a motor connection edge 1111 for connecting to the motor 13; the motor connection edge 1111 is a surface for connecting to the motor 13. In this utility model, the first step 1114 and the second step 1115 are a transition area for load transfer. Through the connection hole 1115a of the second step 1115, the load is transferred to the flat tail skin 121 and the ring frame 1226 using fasteners 113.

[0053] The inner wall of the motor mount 111 has two clearance grooves 1116. The clearance grooves 1116 avoid the protruding structures 530 on both sides of the flat tail 12 to prevent interference with the flat tail 12, which would prevent the motor mount 111 from being installed.

[0054] The outer wall of the motor base 111 is provided with a plurality of connecting ribs 1112 that simultaneously connect to the first step 1114 and the second step 1115. The rear half of each connecting girder 112 is correspondingly provided with each connecting rib 1112 and simultaneously connected to the connecting rib 1112 and the second step 1115. The front half of each connecting girder 112 is connected to the flat tail 12 on the body 100. In this utility model, the connecting rib 1112 serves two purposes: strengthening and connecting to the connecting girder 112. It is designed with holes for fasteners 113 to transfer part of the load of the motor 13 to the connecting girder 112.

[0055] There are four connecting ribs 1112 and four connecting girder 112. Each connecting girder 112 is arranged around the center line of the motor base 111. This utility model has four connecting girder 112, thus providing four force transmission paths and a certain degree of safety backup. At the same time, the opposing connecting girder 112 can effectively balance the asymmetric bending moment load transmitted by the motor 13, increase the longitudinal stiffness of the motor base 111, and help reduce the thickness of the motor base 111 and reduce the structural weight.

[0056] The motor mount 111 is embedded in the flat tail 12, and there is a gap between the motor mount 111 and the flat tail 12. Structural adhesive is applied to the gap. Specifically, the motor mount 111 is embedded in the flat tail. In order to eliminate the influence of tolerance on assembly, a small gap is designed between the inside of the motor mount 111 and the flat tail 12. In this embodiment, the gap is 0.3mm to absorb machining tolerance. Structural adhesive is applied to the gap, and the motor mount 111 is connected to the flat tail through structural adhesive and fasteners 113. Through the above design, even if the size of the flat tail 12 increases and the inner diameter of the motor mount 111 decreases after the actual product is manufactured, the motor mount 111 can still be fitted onto the outside of the flat tail.

[0057] The connecting girder 112 includes a first connecting section 112a and a second connecting section 112b made of an integral molding structure. The first connecting section 112a is connected to the second step 1115 and the flat tail 12 simultaneously by a number of fasteners 113. The rear half of the second connecting section 112b is connected to the connecting rib 1112 by a number of fasteners 113.

[0058] The fastener 113 in this invention is a detachable structure, which facilitates subsequent maintenance, replacement of the motor 13, and connection of the stringer 112. One end of the fastener 113 is exposed, allowing for direct visual inspection, which greatly facilitates the inspection of the tail thrust motor connection structure and prevents the fastener 113 from failing. The rear of the motor 13 is connected to the propeller 13a, which is driven by electricity to rotate the propeller 13a and generate thrust. At the same time, the rotation of the propeller 13a also generates a large torque, vibration, and asymmetric bending moment load, all of which are transmitted to the motor bracket 11 through the motor 13. The motor bracket 11 is connected to the horizontal tail 12 and is arranged outside the horizontal tail 12 for easy assembly and subsequent inspection.

[0059] The horizontal tail 12 includes a frame 122, on which a skin 121 is provided, and the skin 121 is made of carbon fiber composite material;

[0060] The frame 122 includes a front flat-tail beam 1224 and a rear flat-tail beam 1288. Two second longitudinal beams 1222 are respectively provided with a third longitudinal beam 1223 and a first longitudinal beam 1221 at both ends. The rear ends of each first longitudinal beam 1221 are connected by a ring frame 1226. The second longitudinal beam 1222 located on the same side is integrally formed with the first longitudinal beam 1221 and the third longitudinal beam 1223, and passes through the front flat-tail beam 1224 and the rear flat-tail beam 1288. The second longitudinal beam 1222 is located in the middle section of the frame 122. The first longitudinal beam 1221 and the third longitudinal beam 1223 both extend out of the frame 122. The first connecting section 112a in the connecting girder 112 is connected to both the frame 122 and the first longitudinal beam 1221.

[0061] Specifically, in this utility model, the structure of the tailstock frame 122 in the motor 13 connection area consists of a first longitudinal beam 1221, a second longitudinal beam 1222, a third longitudinal beam 1223, a tailstock front beam 1224, a tailstock rear beam 1288, and a ring frame 1226, forming a three-dimensional cage-like frame structure with high stability, rigidity, and strength. The outer side is connected to the tailstock skin 121 with structural adhesive and reinforced with pull-rivets. The frame 122 bracket is connected using fasteners 113. The first longitudinal beam 1221, second longitudinal beam 1222, third longitudinal beam 1223, and tailstock front beam 1288 are also connected. 24. The rear beam 1288 and the ring frame 1226 are both made of carbon fiber composite material, which ensures strength while reducing structural weight. The first longitudinal beam 1221, the second longitudinal beam 1222, and the third longitudinal beam 1223 each have two locations, maintaining the force transmission path with the connecting stringer 112 from top to bottom. Even if one part is damaged, the other part can still withstand a large load, ensuring the safety margin of the motor 13 connection. The first longitudinal beam 1221, the second longitudinal beam 1222, and the third longitudinal beam 1223 are a continuous structure from front to back, forming a closed cavity with the skin 121, effectively bearing the torque of the motor 13.

[0062] The connecting girder 112 of the motor bracket 11 extends to the front of the horizontal tail beam 1288 and connects with the second longitudinal beam 1222. The load is transferred to the horizontal tail beam 12 through multiple fasteners 113 on the connecting girder 112. The first longitudinal beam 1221 is located at the rear of the horizontal tail beam 1288, overlaps with the connecting girder 112 on the outside, and is shorter than the connecting girder 112. It is connected to the horizontal tail beam 1221 through fasteners 113.

[0063] A plurality of motor connection holes 52 are provided around the motor connection edge 1111. Each bolt 53 is respectively set at each of the motor connection holes 52 and connected to the positioning seat 55 on the motor 13. Specifically, the positioning seat 55 of the motor 13 is designed with threads. The threads of the bolts 53 are engaged with the threads in the connection holes on the motor 13, and a certain tightening torque is applied to securely connect the motor 13. Since the asymmetric bending moment has a cyclic load generated by the propeller rotation, which is a high-cycle fatigue load, the connecting stringer 112 and the motor seat 111 are both machined aluminum alloy parts. The preferred material is 2024, and the preferred heat treatment state is T351, because 2024 aluminum alloy has good fatigue performance to meet the fatigue performance requirements of asymmetric bending moment.

[0064] The thickness of the first step 1114 is 4mm, and the thickness of the second step 1115 is 3mm. The load on the motor 13 is gradually distributed through the motor connection edge 1111, the first step 1114, and the second step 1115. Therefore, the thickness of the first step 1114 is greater than that of the second step 1115 to ensure the smooth transition of force transmission.

[0065] The motor connection edge 1111 includes a first thickness and a second thickness; the main body of the motor connection edge 1111 has the first thickness, and each motor connection hole 52 is respectively opened at the second thickness. The first thickness is 5mm, and the second thickness is 10mm. By setting different thicknesses on the motor connection edge 1111, the requirement of stress concentration at the hole edge is met, thereby reducing the stress at the hole edge.

[0066] The outer wall of the motor mount 111 is provided with a plurality of reinforcing ribs 1113, each of which is simultaneously connected to the first step 1114, the second step 1115, and the motor connecting edge 1111. In this invention, by providing reinforcing ribs 1113 to strengthen the motor connecting edge 1111, the motor connecting edge 1111 is given higher rigidity, thus resulting in less deformation when subjected to the load of the motor 13, and ensuring minimal change in the thrust line of the eVTOL aircraft 2.

[0067] A wire harness clearance hole 12211 is provided on the first longitudinal beam 1221. In this embodiment, the wire harness clearance hole 12211 is located at the rear of the first longitudinal beam 1221. Since the wire harness of the motor 13 is arranged relatively far outward and in a circumferential manner, the wire harness clearance hole 12211 is designed to allow the wire harness to be arranged inside the flat tail 12. The location of the wire harness clearance hole 12211 provides a certain clearance length to meet the bending radius requirements of the wire harness, allowing the wire harness to be gathered inward. The longitudinal beam connecting edges 12212 on the upper and lower sides of the first longitudinal beam 1221 are connected to the skin 121 and the connecting girder 112, and their direction is consistent with that of the connecting girder 112, maintaining the continuity and directness of force transmission. Both sides of the first longitudinal beam 1221 have longitudinal beam connecting edges 12212, and the extension direction of each longitudinal beam connecting edge 12212 is consistent with the length direction of the connecting girder 112, and they are simultaneously connected to the skin 121 and the connecting girder 112. The first step 1114, the second step 1115 and the motor connecting edge 1111 are integrally formed structures.

[0068] The fastener 113 in this utility model is used to connect and position various components. This utility model does not limit the specific structure of the fastener 113 itself. The fastener 113 itself is prior art. When positioning various components, the structure of the fastener 113 in this application is not limited to bolts or screws. Any structure that can meet the positioning of various components is acceptable.

[0069] In practical use, the appropriate fasteners can be selected according to actual needs. For example, in this embodiment, the fasteners at the connection between the motor base and the connecting stringer are bolts 1131, nuts 1132, and washers 1133 (e.g., ...). Figure 16 As shown), or, for example, because the connecting surface is a circular curved surface (such as...). Figure 17As shown, to ensure the reliability of the connection, washers 1133 are designed under the head of bolt 1131 and under nut 1132 to prevent scratching the mounting surface during installation. At the same time, it can effectively increase the contact area with the connecting parts and reduce the stress at the connection. The foremost part of the connecting girder 112 is connected to the flat-tail rear beam and the second longitudinal beam 1222. The connecting parts here, from the outside to the inside, are the connecting girder 112, skin 121, flat-tail rear beam, and second longitudinal beam 1222. This can effectively distribute the load to the skin 121, flat-tail rear beam, and second longitudinal beam 1222 through multiple force transmission paths.

[0070] The optimal working principle of this utility model is as follows:

[0071] The core of this eVTOL aircraft tail thruster motor connection structure is to securely connect the motor to the horizontal stabilizer via a motor bracket, achieving load transfer and functional synergy. Specifically:

[0072] After the motor 13 starts, it drives the propeller 13a mounted on its outside to rotate. The rotation of the propeller 13a generates the thrust required for the aircraft to cruise in level flight. At the same time, the rotation of the propeller 13a will generate additional loads such as torque, vibration and asymmetric bending moment. These loads are directly transmitted to the motor 13 body.

[0073] Motor 13 is connected to motor base 111 of motor bracket 11 via positioning seat 55. Bolt 53 passes through motor connection hole 52 on motor connection edge 1111 to fasten motor 13 to motor base 111. The thrust, torque and other loads borne by motor 13 are first transmitted to motor connection edge 1111, and then distributed through integrally formed first step 1114 and second step 1115. Connecting rib 1112 on the outer wall of motor base 111 is simultaneously connected to first step 1114 and second step 1115, connecting stringer 112. The second connecting section 112b is fixed to the connecting rib 1112 by fasteners 113, and the load is transferred from the motor base 111 to the connecting stringer 112; the first connecting section 112a of the connecting stringer 112 is connected to the second step 1115 and the frame 122 of the horizontal tail 12 and the first longitudinal beam 1221 by fasteners 113; and the connecting stringer 112 extends to the front of the rear beam 1288 of the horizontal tail and connects to the second longitudinal beam 1222, and finally transfers all the loads to the horizontal tail 12, and then from the horizontal tail 12 to the body 100;

[0074] A small gap of approximately 0.3mm is reserved between the motor base 111 and the horizontal tail 12. Structural adhesive is applied to the gap to eliminate the influence of machining tolerances on assembly and enhance the sealing and stability of the connection between the two. The reinforcing ribs 1113 on the outer wall of the motor base 111 connect the first step 1114, the second step 1115 and the motor connection edge 1111, improving the rigidity of the motor connection edge 1111, reducing deformation under load, and ensuring the stability of the thrust line. The frame 122 of the horizontal tail 12 consists of the first longitudinal beam 1221, the second longitudinal beam 1222, and the... The three longitudinal beams 1223, the front flat-tail beam 1224, the rear flat-tail beam 1288, and the ring frame 1226 form a three-dimensional cage frame, which enhances the overall rigidity and strength. The wire harness clearance hole 12211 on the first longitudinal beam 1221 provides installation space for the motor 13 wire harness, meets the wire harness bending radius requirements, and facilitates the wire harness to be gathered and arranged inside the flat-tail 12. The longitudinal beam connecting edges 12212 on both sides of the first longitudinal beam 1221 are connected to the skin 121 and the connecting girder 112, and the extension direction is consistent with the connecting girder 112 to ensure the continuity of force transmission.

[0075] The preferred embodiments of this utility model have been described in detail above. It should be understood that those skilled in the art can make numerous modifications and variations based on the concept of this utility model without creative effort. Therefore, all technical solutions that can be obtained by those skilled in the art based on the concept of this utility model through logical analysis, reasoning, or limited experimentation on the basis of existing technology should be within the scope of protection defined by the claims.

Claims

1. A connection structure for the tail thruster motor of an eVTOL aircraft, characterized in that: Including motor bracket (11); The motor bracket (11) includes a motor base (111) with a ring structure, a motor (13) is provided on the motor base (111), and a propeller (13a) is provided on the motor (13); The motor base (111) includes a first step (1114), the front end of the first step (1114) has a second step (1115), the thickness of the first step (1114) is greater than the thickness of the second step (1115), and the rear end of the first step (1114) is provided with a motor connection edge (1111) connected to the motor (13). The inner wall of the motor base (111) has two clearance grooves (1116), and the outer wall of the motor base (111) is provided with a plurality of connecting ribs (1112) that are simultaneously connected to the first step (1114) and the second step (1115). The rear half of each connecting girder (112) is provided in a one-to-one correspondence with each connecting rib (1112) and is simultaneously connected to the connecting rib (1112) and the second step (1115). The front half of each connecting girder (112) is connected to the flat tail (12) on the body (100).

2. The eVTOL aircraft tail thruster connection structure as described in claim 1, characterized in that: There are four connecting ribs (1112) and four connecting girder (112). Each connecting girder (112) is arranged around the center line of the motor base (111). The motor base (111) is embedded in the flat tail (12). There is a gap between the motor base (111) and the flat tail (12). Structural adhesive is applied to the gap. The connecting girder (112) includes a first connecting section (112a) and a second connecting section (112b) made of an integral molding structure. The first connecting section (112a) is connected to the second step (1115) and the flat tail (12) simultaneously by a number of fasteners. The rear half of the second connecting section (112b) is connected to the connecting rib (1112) by a number of fasteners.

3. The eVTOL aircraft tail thruster connection structure as described in claim 2, characterized in that: The horizontal tail (12) includes a frame (122), on which a skin (121) is provided, the skin (121) being made of carbon fiber composite material; The frame (122) includes a front flat-tail beam (1224) and a rear flat-tail beam (1288). Two second longitudinal beams (1222) are respectively provided with a third longitudinal beam (1223) and a first longitudinal beam (1221) at both ends. The rear ends of each first longitudinal beam (1221) are connected by a ring frame (1226). The second longitudinal beam (1222) located on the same side is integrally formed with the first longitudinal beam (1221) and the third longitudinal beam (1223) and passes through the front flat-tail beam (1224) and the rear flat-tail beam (1288). The second longitudinal beam (1222) is located in the middle section of the frame (122). The first longitudinal beam (1221) and the third longitudinal beam (1223) both extend out of the frame (122). The first connecting section (112a) in the connecting girder (112) is connected to both the frame (122) and the first longitudinal beam (1221).

4. The eVTOL aircraft tail thruster motor connection structure as described in claim 3, characterized in that: A plurality of motor connection holes (52) are provided around the motor connection edge (1111), and each bolt (53) is respectively provided at each of the motor connection holes (52) and connected to the positioning seat (55) provided on the motor (13).

5. The eVTOL aircraft tail thruster connection structure as described in claim 4, characterized in that: The thickness of the first step (1114) is 4 mm, and the thickness of the second step (1115) is 3 mm.

6. The eVTOL aircraft tail thruster connection structure as described in claim 5, characterized in that: The motor connection edge (1111) includes a first thickness and a second thickness; the motor connection edge (1111) body has the first thickness, and each motor connection hole (52) is opened at each of the second thicknesses. The first thickness is 5mm and the second thickness is 10mm.

7. The eVTOL aircraft tail thruster connection structure as described in claim 6, characterized in that: The outer wall of the motor base (111) is provided with a plurality of reinforcing ribs (1113), and each of the reinforcing ribs (1113) is simultaneously connected to the first step (1114), the second step (1115) and the motor connecting edge (1111).

8. The eVTOL aircraft tail thruster connection structure as described in claim 7, characterized in that: The first longitudinal beam (1221) has a wire harness clearance hole (12211).

9. The eVTOL aircraft tail thruster connection structure as described in claim 8, characterized in that: The first longitudinal beam (1221) has longitudinal beam connecting edges (12212) on both sides. The extension direction of each longitudinal beam connecting edge (12212) is consistent with the length direction of the connecting girder (112), and it is connected to the skin (121) and the connecting girder (112) at the same time.

10. The eVTOL aircraft tail thruster connection structure as described in claim 9, characterized in that: The first step (1114), the second step (1115), and the motor connection edge (1111) are integrally formed structures.

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