EVTOL aircraft wing body fairing

Abstract

The utility model discloses an eVTOL aircraft wing body fairing which comprises a skin, a rear supporting beam and a front supporting beam, the front supporting beam is connected with the middle of the skin through a connecting piece and supports the middle of the skin, the rear supporting beam is installed on the right portion of the skin through a connecting piece, and the skin is a carbon fiber composite material piece. The rear sides of the supporting beam and the front supporting beam are connected with supporting ribs, the side edges of the supporting ribs are connected with a skin, a thickening area is arranged on the periphery of the skin, and the skin is connected with the eVTOL aircraft, the rear supporting beam and the supporting ribs through the thickening area in cooperation with connecting pieces. The fairing is good in aerodynamic performance, the bolts are adopted as connecting pieces and do not protrude out of the aerodynamic surface, meanwhile, the supporting ribs, the front supporting beam and the rear supporting beam are adopted for supporting the skin, the precision of the appearance of the skin is ensured, and the aerodynamic performance is consistent with the design.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, and in particular to an eVTOL aircraft wing-body fairing. 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-body fairing can reduce the interference drag between the wing and the body, reduce the drag during cruising, increase the lift-to-drag ratio of the entire aircraft, improve the aircraft's range and the aircraft's low-speed aerodynamic characteristics, and is used in large quantities on aircraft. In order to reduce the weight of the fairing, many wing-body fairings are made of rubber materials with moderate hardness. Taking advantage of the softness of the rubber, they are installed on the fuselage together with the wing so that they are close to the fuselage on all sides. For example: the Chinese utility model patent "A UAV wing fairing structure" with application number 202121044337.4. However, soft materials similar to rubber materials will produce greater deformation due to the influence of aerodynamic forces when the aircraft is flying at a faster speed, which will affect the lift of the aircraft. At the same time, soft materials are also easy to fall off after large deformation. In addition, the wing-body fairing is made of additional rubber material, which cannot transmit force and is heavier. Utility Model Content

[0004] The purpose of the utility model is to provide an eVTOL aircraft wing-body fairing to solve the problems mentioned in the background technology. To achieve the above purpose, the utility model provides the following technical solutions: an eVTOL aircraft wing-body fairing, including a skin, a rear support beam and a front support beam, the front support beam is connected to the middle part of the skin through a connector and supports the middle part of the skin, the rear support beam is installed on the right part of the skin through a connector, the skin is a carbon fiber composite material, the support beam and the rear side of the front support beam are connected to the support rib, the side of the support rib is connected to the skin, the periphery of the skin is provided with a thickened area, and the skin is connected to the eVTOL aircraft, the rear support beam and the support rib through the thickened area and the connector.

[0005] Preferably, the rear support beam and the front support beam both include a support beam, a lightening hole is opened on the support beam, reinforcing ribs are arranged around the lightening hole, a connecting edge is arranged around the support beam, and the connecting edge cooperates with a connecting piece to connect the skin and the eVTOL aircraft.

[0006] Preferably, a wire hole is formed on the support rib, and the material of the support rib is one of aluminum alloy, glass fiber composite material and carbon fiber composite material.

[0007] Preferably, the rear support beam and the front support beam are aluminum alloy frame structures.

[0008] Preferably, the connecting members are bolts and nuts.

[0009] The technical effects and advantages of the utility model are as follows: the fairing has good aerodynamic performance, the connecting parts are bolts, and do not protrude from the aerodynamic surface, and the skin is supported by supporting ribs and front and rear support beams to ensure the accuracy of the skin shape, thereby ensuring that the aerodynamic performance is consistent with the design;

[0010] Lightweight: The area of ​​the wing-body fairing is the area where the front part of the wing front beam merges with the wing body, and the area is relatively small. The rear area of ​​the front beam is designed as a force transmission structure to minimize the area of ​​the fairing; the skin is made of carbon fiber composite materials. Except for the thickened area as the connection area, the other internal areas are thinner in thickness and supported by supporting ribs, rear support beams and front support beams; the rear support beams and front support beams are hollow structures with large-area lightening holes designed to reduce the structural weight by using space reinforcement rib structure;

[0011] Good maintainability: The connecting parts are all detachable bolts and nuts, which can be easily disassembled for maintenance, and have good maintainability;

[0012] High fatigue strength: A thickened area is designed around the skin to meet the countersinking requirements of the bolts in the connector, avoid the knife edge effect, and have high fatigue strength. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is an axonometric view of the utility model from the outside perspective;

[0014] Figure 2 An axonometric view of the interior of the present invention;

[0015] Figure 3 It is an exploded view of the utility model;

[0016] Figure 4 This is an axonometric view of the utility model after the hidden skin;

[0017] Figure 5 This is a schematic diagram of the rear support beam structure of the utility model;

[0018] Figure 6 This is a schematic diagram of the skin structure of the utility model;

[0019] Figure 7 This is a schematic diagram of the installation of the connector of the utility model;

[0020] Figure 8 This is a schematic diagram of the installation of the utility model on an eVTOL aircraft.

[0021] In the figure, 1. Wing-body fairing; 11. Skin; 111. Thickened area; 12. Support ribs; 13. Rear support beam; 131. Lightening holes; 132. Reinforcement ribs; 133. Connecting edge; 134. Support beam; 14. Front support beam; 15. Connector; 16. Wire hole; 2. eVTOL aircraft. DETAILED DESCRIPTION

[0022] In order to make the technical means for realizing the utility model, creative features, objectives and effects easy to understand, the utility model is further explained below in conjunction with specific diagrams. In the description of the utility model, 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 internal communication between two components.

[0023] Example

[0024] like Figure 8 As shown, the wing-body fairing 1 is only designed at a relatively complex position in the front part of the wing-body connection area. The wing box area where the wing is connected to the fuselage is designed as a force transmission structure. The wing-body fairing 1, as a non-force transmission structure, occupies a small area and is light in weight. At the same time, the quality control of the manufacturing process of parts with complex shapes is relatively complex. As a non-force transmission structure, it contributes to the safety of the eVTOL aircraft 2.

[0025] like Figure 1-Figure 4 As shown, the wing-body fairing 1 includes a skin 11, a support rib 12, a rear support beam 13, a front support beam 14, and a connector 15. The skin 11 is a carbon fiber composite material part, which is used to maintain the shape of the eVTOL aircraft 2 in this area, bear the load of the airflow of the eVTOL aircraft 2 during flight, and is subjected to less force. At the same time, the skin 11 needs to maintain the accuracy of the shape so that the aerodynamic performance is consistent with the design. Since the wing-body fairing 1 is not used as a force transmission structure, the strength requirement is not high, and the skin 11 can be processed very thin. In this example, the thickness of the large area of ​​the skin 11 is only 0.6mm. At the same time, the skin 11 needs to maintain its shape. When subjected to aerodynamic force, it needs to keep the shape unchanged, which requires a higher out-of-plane stiffness. Increasing the thickness of the skin 11 can increase the out-of-plane stiffness, which will bring greater weight. Therefore, support ribs 12, front support beams 14, and rear support beams 13 are designed to support the skin 11.

[0026] The support rib 12 is supported on the outside of the wing-body fairing 1, corresponding to the root of the wing leading edge, and the side of the support rib 12 is connected to the skin 11 to prevent side water vapor from entering the inside of the wing-body fairing 1. Only one wire hole 16 is opened on the support rib 12, and the periphery of the wire hole 16 is sealed after the wire is passed. The support rib 12 can be a structural member made of aluminum alloy, glass fiber composite material, or carbon fiber composite material, preferably made of carbon fiber composite material.

[0027] The front support beam 14 and the rear support beam 13 both adopt an aluminum alloy frame structure, the preferred material is 7075, and the preferred heat treatment state is T7351. The front support beam 14 is supported and connected to the middle part of the skin 11, and the rear support beam 13 is supported and connected to the right part of the skin 11 where the stiffness is the smallest, so as to maintain the appearance of the skin 11 in this area. At the same time, the front support beam 14 and the rear support beam 13 are connected to the skin 11 by a connector 15, and are also connected to the peripheral structure of the eVTOL aircraft 2 through the connector 15. The connector 15 includes a bolt and a nut, preferably a countersunk bolt and a support plate nut. The support plate nut is fixed on the support rib 12, the rear support beam 13, and the front support beam 14. The countersunk bolt installs the skin 11 to the support rib 12, the rear support beam 13, and the front support beam 14, completing the fixation of the skin 11, keeping the appearance of the skin 11 smooth, and reducing the aerodynamic resistance.

[0028] like Figure 5As shown, the rear support beam 13 and the front support beam 14 have similar structures, both including a support beam 134, a lightening hole 131, a reinforcing rib 132 and a connecting edge 133. Since the wing-body fairing 1 is not used as the main force transmission component, the rear support beam 13 and the front support beam 14 do not need high strength, so a large-area lightening hole 131 is designed on the support beam 134 to reduce weight. At the same time, the lightening hole 131 is used for the passage of the internal wiring harness of the wing-body fairing, and the wiring harness is fixed to the rear support beam 13. The reinforcing rib 132 is arranged around the lightening hole 131 for reinforcement, and the overall stiffness of the rear support beam 13 is improved by the reinforcing rib 132. The connecting edge 133 is arranged around the support beam 134, and cooperates with the connector 15 to connect the rear support beam 13, the front support beam 14 to the skin 11 and other peripheral structures of the eVTOL aircraft 2.

[0029] like Figure 6 and Figure 7 As shown, a thickened area 111 is designed in the area where the skin 11 is connected to the connector 15 at the periphery to meet the requirement of the countersunk bolts in the connector 15 on the countersunk depth of the skin 11. In this example, the countersunk depth is 65% of the thickness of the skin 11 to avoid the countersunk depth being greater than the thickness of the skin 11, forming a knife-edge effect, and affecting the fatigue life of the skin 11.

[0030] 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, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or 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 wing-body fairing, comprising a skin, a rear support beam and a front support beam, characterized in that: The front support beam is connected to the middle part of the skin through a connecting piece and supports the middle part of the skin. The rear support beam is installed on the right part of the skin through a connecting piece. The skin is a carbon fiber composite material. The support beam and the rear side of the front support beam are connected to the support rib. The side of the support rib is connected to the skin. A thickened area is provided around the skin. The skin is connected to the eVTOL aircraft, the rear support beam and the support rib through the thickened area and the connecting piece.

2. The eVTOL aircraft wing-body fairing according to claim 1, characterized in that: The rear support beam and the front support beam both include a support beam, a lightening hole is opened on the support beam, reinforcing ribs are arranged around the lightening hole, and a connecting edge is arranged around the support beam, and the connecting edge cooperates with a connecting piece to connect the skin and the eVTOL aircraft.

3. The eVTOL aircraft wing-body fairing according to claim 1, characterized in that: The support rib is provided with a wire hole, and the material of the support rib is one of aluminum alloy, glass fiber composite material and carbon fiber composite material.

4. The eVTOL aircraft wing-body fairing according to claim 2, characterized in that: The rear support beam and the front support beam are aluminum alloy frame structural parts.

5. The eVTOL aircraft wing-body fairing according to claim 1, characterized in that: The connecting pieces are bolts and nuts.

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