EVTOL aircraft outer wing structure

Abstract

The eVTOL aircraft outer wing structure comprises a framework, the framework is covered with a skin, ailerons are installed on one side of the framework, the framework comprises a plurality of stringers, the stringers are distributed in parallel, the two ends of each stringer are connected with a reinforcing frame, an intersection area structure is installed in the middle of each stringer, and the intersection area structure is connected with the skin. A plurality of ribs are installed on the intersection area structure, the side edge of the intersection area structure is connected with an aileron through an aileron connector, a plurality of supporting frames are installed among the stringers, and one side of the reinforcing frame is connected with a motor connecting base. The outer wing structure is light in weight, the outer wing and the motor arm on the outer side are integrally designed into a section, blocks are reduced, and the connecting weight is saved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to an outer wing structure of an eVTOL aircraft. Background Art

[0002] The development of eVTOL (Electric Vertical Takeoff and Landing) electric vertical takeoff and landing aircraft has attracted widespread attention from aerospace companies, the automotive industry, the transportation industry, the government, the military and academia. The potential future applications of eVTOL involve a variety of scenarios such as urban passenger transport, regional passenger transport, freight, personal aircraft, and emergency medical services. The American Vertical Flight Association believes that eVTOL technology is one of the most important technological changes in the aviation industry since the birth of the helicopter 75 years ago, and may be more revolutionary than the emergence of turbine engines. According to the "World Electric Vertical Takeoff and Landing (eVTOL) Aircraft Directory" published online by the association, there are currently more than 260 projects engaged in eVTOL development around the world. The use of electric propulsion systems instead of internal combustion engine power has gained many advantages and unique qualities. The most prominent advantages are energy saving and environmental protection, high efficiency and low energy consumption, while achieving near-zero emissions, low noise and vibration levels, and good ride comfort. It is a truly environmentally friendly aircraft. In addition, it is also safe and reliable (no explosion and fuel leakage), simple structure, easy operation and use, good maintainability / low cost, and good economy. There are also many advantages in design: the overall layout is flexible, and both optimal layout and unconventional / innovative layout can be adopted; aircraft with extraordinary performance can be designed to meet special purpose requirements, etc.

[0003] The wing is the most important part of the eVTOL aircraft. It generates lift during level flight and bears the entire load of the eVTOL aircraft during maneuvering flight. Therefore, it is crucial to ensure the safety and load-bearing capacity of the wing structure. Compared with traditional fixed-wing aircraft, the wings of eVTOL aircraft are connected to motor arms, and the tension generated by the motors is also transmitted to the wings. In addition to bearing its own aerodynamic force, the wings also need to bear the tension generated by the propellers on the motor arms. Summary of the invention

[0004] The object of the present invention is to provide an outer wing structure of an eVTOL aircraft to solve the problems mentioned in the background technology. To achieve the above object, the present invention provides the following technical solutions: an outer wing structure of an eVTOL aircraft, comprising a frame, the frame is covered with a skin, an aileron is installed on one side of the frame, the frame comprises a long stringer, the long stringer is provided with a plurality of parallel distributions, the two ends of the long stringer are connected to a reinforcement frame, the middle part of the long stringer is installed with an intersection area structure, the intersection area structure is installed with a plurality of ribs, the side of the intersection area structure is connected to the aileron through an aileron joint, a plurality of support frames are installed between the plurality of the long stringers, and a motor connection seat is connected to one side of the reinforcement frame.

[0005] Preferably, the skin includes a longitudinal lower skin, which is installed below the long stringer and the motor connection seat, the long stringer is covered with a longitudinal upper skin, the upper end of the motor connection seat is covered with a motor cover, the longitudinal lower skin, the longitudinal upper skin and the motor cover are connected to each other at the edge, the span-up skin and the span-down skin are installed above and below the intersection structure respectively, the end of the intersection structure is installed with a wingtip winglet, the span-up skin, the span-down skin and the wingtip winglet are connected to each other at the edges.

[0006] Preferably, the intersection structure includes a butt joint, with beams connected at both ends of the butt joint, a butt rib installed between the two beams, a reinforcing half frame installed between the butt joint and adjacent butt ribs, and a butt frame installed on the outside of the beam.

[0007] Preferably, widened edge strips are provided at both ends of the long stringer, and the reinforcement frame is provided with long stringer connecting edges along the periphery, and the long stringer connecting edges are connected to the widened edge strips through corner pieces.

[0008] Preferably, beam connection areas are provided at both ends of the butt joint, ears are installed on the outer side of the beam connection area, and the beam connection area connects the beams.

[0009] Preferably, the support frame is provided with a long girder notch for the long girder to pass through, and the support frame is provided with a depression at the overlap with the longitudinal lower skin and the longitudinal upper skin.

[0010] Preferably, a butt edge is integrated in the middle of the longitudinal upper skin.

[0011] Preferably, the long stringer is a T-shaped long stringer.

[0012] Preferably, the butt joint edge of the longitudinal upper skin and the spanwise upward skin are connected at the butt joint ribs by using structural adhesive.

[0013] The technical effects and advantages of the present invention are as follows: The outer wing structure is light in weight: the outer wing and the outer motor arm are integrated into one section, which reduces the number of blocks and saves the connection weight;

[0014] Good force bearing: the main frame is arranged along the longitudinal direction in the direction of the motor arm and along the span direction in the direction of the outer wing. The lift of the lift unit is borne by the longitudinal parts, and the aerodynamic force generated by the wing is borne by the span parts;

[0015] Easy to disassemble: Both ears of the butt joint are integrally machined with high precision. When disassembling, just remove the fasteners of the butt ears.

[0016] The wiring harness is easy to install: the thicker power wiring harness is arranged along the longitudinal direction of the motor arm, and there is more space at the separation surface, which is convenient for installation.

[0017] Good manufacturability: The skin is separated at the butt ribs, which reduces the difficulty of forming the skin and has good manufacturability. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is an axonometric view of the present invention in the position of an eVTOL aircraft;

[0019] Figure 2 is an axonometric view of the present invention;

[0020] Figure 3 An exploded view of the present invention;

[0021] Figure 4 It is an axonometric view of the skeleton of the present invention;

[0022] Figure 5 It is an axonometric view of the intersection structure of the present invention;

[0023] Figure 6 It is an axonometric diagram of the connection between the long girder and the reinforcement frame of the present invention;

[0024] Figure 7 It is an axonometric view of the reinforcement frame of the present invention;

[0025] Figure 8 is an axonometric view of the long girder of the present invention;

[0026] Fig. 9 is an axonometric view of a butt joint of the present invention;

[0027] Fig.10 is an axonometric view of the support frame of the present invention;

[0028] Fig.11 It is an axonometric view of the longitudinal upper skin of the present invention;

[0029] Fig.12 It is a cross-sectional view of the present invention in the long stringer area;

[0030] Fig.13 It is a cross-sectional view of the spanwise and longitudinal skins of the present invention at the butt ribs.

[0031] In the figure, 1. outer wing structure; 11. frame; 111. intersection area structure; 1111. butt joint; 11111. ear piece; 11112. beam connection area; 1112. butt frame; 1113. reinforced half frame; 1114. beam; 1115. butt rib; 112. support frame; 1121. depression; 1122. long stringer notch; 113. reinforced frame; 1131. long stringer connection edge; 114. Long stringer; 1141. Corner piece; 1142. Widened edge strip; 115. Motor connector; 116. Rib; 117. Aileron joint; 12. Skin; 121. Longitudinal lower skin; 122. Longitudinal upper skin; 1221. Butt edge 123. Spread-up skin; 124. Spread-down skin; 125. Wing tip winglet; 126. Motor cover; 13. Aileron; 2. eVTOL aircraft. DETAILED DESCRIPTION

[0032] In order to make the technical means for realizing the present invention, the creative features, the objectives and effects to be achieved easy to understand, the present invention is further explained below in conjunction with specific diagrams. In the description of the present invention, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, an integral connection or a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two components.

[0033] Example

[0034] like Figure 1 As shown, the present invention is an outer wing structure 1 of an eVTOL aircraft 2, which integrates an outer motor arm as a section, connected to both sides of the eVTOL aircraft 2, and meets the lift of the motor arm lift unit and the aerodynamic force generated by the outer wing. As a section, the size also meets the requirements of road container transportation, without considering large-scale transportation, and is integrated together, reducing the separation surface of the structure and effectively reducing the weight of the structure.

[0035] like Figure 2 , 3 As shown, the outer wing structure 1 includes a skeleton 11, a skin 12 and an aileron 13. The skeleton 11 and the skin 12 are mainly arranged along the longitudinal direction and the span direction. The skin 12 covers the skeleton 11. The skeleton 11 and the skin 12 are mainly connected by structural adhesive. In some locations with a small connection area, fasteners are added to improve the reliability of the connection. The skeleton 11 and the skin 12 are subjected to force together and transmit part of the load respectively, forming a double force transmission path to improve the residual strength of the structure. The aileron 13 is connected to the outer wing structure 1 through the aileron joint 117, and the magnitude of the lift is changed by deflection, generating a rolling moment, and changing the roll state of the eVTOL.

[0036] The skin 12 includes a longitudinal lower skin 121, a longitudinal upper skin 122, a span-up skin 123, a span-down skin 124, a wingtip winglet 125, and a motor cover 126, all of which are made of carbon fiber composite materials to reduce the structural weight. The span-up skin 123, the span-down skin 124, and the wingtip winglet 125 are connected to each other at the edges. The longitudinal upper skin 122 and the longitudinal lower skin 121 together with the skeleton 11 form a bearing structure for the lifting force of the motor arm. The carbon fiber 0-degree plies are arranged more longitudinally, which is 60% in this example, to transfer the longitudinal load. The carbon fiber 0-degree plies of the span-up skin 123 and the span-down skin 124 are arranged more along the span direction, which is 50% in this example, effectively improving the bearing capacity in the 0-degree direction. The wingtip winglet 125 is on the outside of the outer wing, providing dimensional and aerodynamic characteristics. The interior is a hollow structure, which is connected to the ribs on the outer wing by detachable fasteners. The motor cover 126 is a maintenance cover, which is divided into two parts on the left and right. When the motor needs maintenance, the motor cover 126 is removed.

[0037] like Figure 4As shown, the skeleton 11 includes an intersection area structure 111 attached longitudinally and connected to the skeleton in the span direction, a support frame 112, a reinforcement frame 113, a long girders 114, a motor connection seat 115, ribs 116 and an aileron joint 117. The long girders 114 are provided with a plurality of them, which are distributed in parallel. The two ends of the long girders 114 are connected to the reinforcement frames 113. The middle of the long girders 114 is equipped with an intersection area structure 111. A plurality of ribs 116 are installed on the intersection area structure 111. The side of the intersection area structure 111 is connected to the aileron 13 through the aileron joint 117. A plurality of support frames 112 are installed between the plurality of long girders 114. A motor connection seat 115 is connected to one side of the reinforcement frame 113. The longitudinal lower skin 121 is installed below the long stringer 114 and the motor connection seat 115. The top of the long stringer 114 is covered with a longitudinal upper skin 122. The upper end of the motor connection seat 115 is covered with a motor cover 126. The longitudinal lower skin 121 and the longitudinal upper skin 122 and the motor cover 126 are connected to each other at the edges. The upper and lower parts of the intersection area structure 111 are respectively installed with a span-up skin 123 and a span-down skin 124. The end of the intersection area structure 111 is installed with a winglet 125. The intersection area structure 111 connects the longitudinal skeleton and the span-wise skeleton together to bear more complex loads. At the same time, the intersection area structure 111 connects the outer wing and the inner wing together to achieve a detachable function. The support frame 112 supports the longitudinal skin 12 to prevent the stressed skin 12 from losing stability. The reinforcement frame 113 is connected to the motor connection seat 115 and the long girder 114 to bear a large load. The long girder 114 is a longitudinally arranged part with a T-shaped cross-section and is made of carbon fiber composite material. It can be formed separately and then glued together with the skin 12, or it can be co-cured with the skin 12. In this example, it is co-cured with the skin 12. The motor connection seat 115 is connected to the motor to bear the torque of the motor and the lift generated by the lift unit. The motor connection seat 115 is a structure composed of multiple metal machined parts to ensure that it can withstand loads in multiple directions. The rib 116 supports the upward skin 123 and the downward skin 124 in the skin 12 to prevent them from buckling, and at the same time connects the beam 1114 together to bear the torque of the structure. The outermost rib 1116 is connected to the wingtip winglet 125 through a fastener that can be disassembled on one side. In this example, it is connected by a support plate nut and a bolt pair. The aileron joint 117 is connected to the aileron 13 so that the aileron 13 can rotate around the axis of the hole on the joint. The lift on the outer wing is changed by deflecting the aileron 13, thereby achieving the purpose of changing the roll-on state of the eVTOL aircraft.

[0038] like Figure 5As shown, the intersection structure 111 includes a butt joint 1111, a butt frame 1112, a reinforced half frame 1113, a beam 1114, and a butt rib 1115. The two ends of the butt joint 1111 are connected to the beam 1114. A butt rib 1115 is installed between the two beams 1114. A reinforced half frame is installed between the butt joint 1111 and the adjacent butt ribs. A butt frame is installed on the outside of the beam. The butt joint is connected to the inner wing, connecting the entire outer wing structure to the inner wing. The butt joint is a metal machined part, which can be made of steel, stainless steel, or aluminum alloy. The preferred material is 7050 aluminum alloy, and the preferred heat treatment state is T7451. The butt frame 1112 transfers the load of the motor arm to the beam 1114, and the shear force of the motor arm is transferred to the beam 1114 through the front and rear two butt frames 1112. The butt frame 1112 is divided into upper and lower parts, which are connected to the beam 1114 with fasteners. The two parts are mainly split into two parts to adjust the tolerance accumulation of the connection here and reduce the difficulty of assembly. The reinforced half frame 1113 is used to reinforce the longitudinal upper skin 122. Since the aerodynamic force transmitted from the outer wing is a compressive load in this area, and the area here is in a bending state along the force direction, it is not friendly to the force of the composite material. Therefore, it is reinforced in the upper part, and the half frame 1113 is strengthened. The two sides of the reinforced half frame 1113 are respectively connected to the butt joint 1113 and the butt rib 1115, which plays a role in supporting the longitudinal upper skin 122 in the span direction. There are two beams 1114, which are arranged along the span direction to bear the aerodynamic force received by the outer wing. The inner side is connected to the butt joint 1111, and the load is transferred to the butt joint 1111. It is connected to the butt frame 1112 through the position of the motor arm to transfer the load of the motor arm. While the butt rib 1115 connects the front and rear beams, it also serves as the rib 116 connecting the longitudinal upper skin 122, the longitudinal lower skin 121, the span-up skin 123, and the span-down skin 124. The skin is connected together on the edge strip of the butt rib 1115.

[0039] like Figure 6 , Figure 7 and Figure 8 As shown, the long stringer 114 is connected to the reinforcement frame 113 through a hinge. At the same time, the width of the edge strip of the long stringer 114 is widened at the connection position, and the edge strip of the reinforcement frame 113 is also partially lengthened at the connection position, mainly considering the margin requirements of the connecting fasteners, meeting the margin requirements of the fasteners, and improving fatigue performance. The long stringer 114 mainly transmits longitudinal loads, and keeps continuous from the front reinforcement frame to the rear reinforcement frame, effectively improving the load-bearing capacity and reducing the weight. The reinforcement frame 113 is connected to the motor connection seat, and the external support skin 12 transmits the load of the motor.

[0040] like Fig. 9As shown, beam connection areas 11112 are provided at both ends of the butt joint 1111, and lugs 11111 are installed on the outer side of the beam connection area 11112. The beam connection area 11112 is connected to the beam 1114. The two lugs 11111 of the butt joint 1111 are connected to the inner wing respectively. The holes on the lugs 11111 are connected by fasteners to transfer all the loads of the outer wing to the inner wing. The two ends of the butt joint 1111 are connected to the beam respectively to transfer the main load to the butt joint 1111. The overall machined lugs have high precision, which effectively improves the connection precision and reduces the complexity of the assembly tooling.

[0041] like Fig.10 As shown, the support frame supports the skin to prevent it from buckling. In order to ensure the continuity of the long stringer, a long stringer gap is designed on the support frame for the passage of the occasion. In the area where the upper and lower skins overlap, a depression is designed to avoid the overlapping area of ​​the skin.

[0042] like Fig.11 As shown, a small butt edge 1221 is integrated on the longitudinal upper skin 122 to connect with the extensional upward skin 123, maintaining a flat section of the connecting surface at one end, so that when the structural adhesive is used for connection, the bonding thickness of the structural adhesive can be guaranteed to be uniform, thereby improving the bonding quality. The longitudinal lower skin 121 has a similar structure.

[0043] like Fig.12 As shown, the motor arm section of the outer wing structure of the present invention is composed of a skin 12 and a long stringer 114. The cross section of the long stringer 114 is a T-shaped long stringer, which is connected to the skin 12. In this example, the co-curing process is used to connect them together.

[0044] like Fig.13 The butt joint edge 1221 of the longitudinal upper skin 122 and the spanwise upward skin 123 are connected together at the butt joint rib 1115 by means of structural adhesive. The edge strip width of the butt joint frame 1112 is relatively wide, which can meet the width requirement of the butt joint connection between the spanwise upward skin 123 and the longitudinal upper skin 122. The longitudinal lower skin 121 and the spanwise downward skin 124 are connected in a similar manner on the other side of the butt joint frame 1112.

[0045] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An eVTOL aircraft outer wing structure, comprising a frame, characterized in that: The frame is covered with a skin, an aileron is installed on one side of the frame, the frame includes a long stringer, and a plurality of the long stringers are provided and distributed in parallel, both ends of the long stringers are connected to reinforcement frames, an intersection area structure is installed in the middle of the long stringer, a plurality of ribs are installed on the intersection area structure, the side of the intersection area structure is connected to the aileron through an aileron joint, a plurality of support frames are installed between the plurality of the long stringers, and a motor connecting seat is connected to one side of the reinforcement frame.

2. An eVTOL aircraft outer wing structure according to claim 1, characterized in that: The skin includes a longitudinal lower skin, which is installed below the long stringer and the motor connection seat. The top of the long stringer is covered with a longitudinal upper skin. The upper end of the motor connection seat is covered with a motor cover. The longitudinal lower skin, the longitudinal upper skin and the motor cover are connected to each other at the edge. The span-up skin and the span-down skin are installed above and below the intersection structure respectively. A wingtip winglet is installed at the end of the intersection structure. The span-up skin, the span-down skin and the wingtip winglet are connected to each other at the edges.

3. An eVTOL aircraft outer wing structure according to claim 2, characterized in that: The intersection structure includes a butt joint, with beams connected at both ends of the butt joint, a butt rib installed between the two beams, a reinforced half frame installed between the butt joint and adjacent butt ribs, and a butt frame installed on the outside of the beam.

4. The eVTOL aircraft outer wing structure according to claim 1, characterized in that: Both ends of the long stringer are provided with widened edge strips, and the reinforcement frame is provided with long stringer connecting edges along the periphery, and the long stringer connecting edges are connected to the widened edge strips through angle pieces.

5. The outer wing structure of an eVTOL aircraft according to claim 3, characterized in that: Beam connection areas are provided at both ends of the butt joint, and lugs are installed on the outer side surfaces of the beam connection areas, and the beam connection areas connect beams.

6. The outer wing structure of an eVTOL aircraft according to claim 2, characterized in that: The support frame is provided with a long girder notch for the long girder to pass through, and a depression is provided at the overlap between the support frame and the longitudinal lower skin and the longitudinal upper skin.

7. The eVTOL aircraft outer wing structure according to claim 2, characterized in that: A butt edge is integrated in the middle of the longitudinal upper skin.

8. The eVTOL aircraft outer wing structure according to claim 1, characterized in that: The long stringer is a T-shaped long stringer.

9. The outer wing structure of an eVTOL aircraft according to claim 3, characterized in that: The butt joint edge of the longitudinal upper skin and the spanwise upward skin are connected at the butt joint ribs by using structural adhesive.

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