EVTOL aircraft fuselage skin

Abstract

The utility model discloses an eVTOL aircraft fuselage skin which comprises a left skin and a right skin, the left skin and the right skin are oppositely arranged, the middle of the left skin and the middle of the right skin are connected with each other, and the bottom of the left skin and the bottom of the right skin are matched with a nose landing gear covering cap and a nose landing gear covering cap to form a nose landing gear mounting hole and a nose landing gear mounting hole. A left cockpit door opening, a passenger cabin door opening, a cargo hold door opening and a left windshield opening are formed in the left skin, and left sealing edges are arranged on the peripheries of the left cockpit door opening, the passenger cabin door opening and the cargo hold door opening. The fuselage skin is high in bearing capacity, a thick carbon fiber composite material laminated plate structure is adopted at the position where passengers sit and other positions with high strength requirements, carbon fiber composite material sandwich skins are adopted at other positions with small stress, rigidity is improved, the fuselage skin and the framework are matched together to bear loads transmitted by the front undercarriage and the rear undercarriage, and the bearing capacity is high.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, and in particular to an eVTOL aircraft fuselage skin. 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 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, very low noise and vibration levels, and good ride comfort. It is a truly environmentally friendly aircraft. In addition, it also has the characteristics of safety and reliability, 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, the optimal layout and unconventional / innovative layout can be adopted; aircraft with extraordinary performance can be designed to meet special purpose needs, etc.

[0003] The fuselage of the eVTOL aircraft is a cabin that carries passengers and cargo, and at the same time transmits the eVTOL aircraft load and provides protection for the passengers. The fuselage skin maintains the shape of the eVTOL aircraft fuselage and reduces aerodynamic resistance. At the same time, the fuselage skin needs to meet a certain load-bearing capacity, provide openings for passengers to enter and exit, have the function of draining water and sewage, and provide installation support for avionics equipment on the aerodynamic surface. Therefore, this application provides an eVTOL aircraft fuselage skin to meet the above requirements. Utility Model Content

[0004] The purpose of the utility model is to provide an eVTOL aircraft fuselage skin 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 fuselage skin, including a left skin and a right skin, the left skin and the right skin are placed opposite to each other, the middle parts of the left skin and the right skin are connected to each other, the bottoms of the left skin and the right skin cooperate with the front landing gear cover and the rear landing gear cover to form the front landing gear mounting hole and the rear landing gear mounting hole, the left skin is provided with a left cockpit door opening, a cabin door opening, a cargo door opening, and a left windshield opening, and the left cockpit door opening, the cabin door opening, and the cargo door opening are provided with a left sealing edge around them.

[0005] Preferably, a right cockpit door opening, a window opening, and a right windshield opening are formed on the right skin, and a right sealing edge is provided around the right cockpit door opening.

[0006] Preferably, the cabin door opening has a hinge opening on the upper side and lock tongue openings on the front and rear sides.

[0007] Preferably, a drainage hole is provided at the bottom of the right skin.

[0008] Preferably, a flange is provided at the periphery of the right skin, and the right skin is connected to the middle part of the left skin by structural adhesive in combination with the flange.

[0009] Preferably, the upper and lower parts of the window opening are provided with window reinforcements.

[0010] Preferably, the left skin and the right skin are made of carbon fiber composite laminates in the area where passengers sit, and foam sandwich skins are used in the front and rear areas.

[0011] Preferably, the foam sandwich skin is a structure with internal foam and external carbon fiber wrapping.

[0012] The technical effects and advantages of the utility model are as follows: The fuselage skin has high bearing capacity: a thicker carbon fiber composite laminate structure is used in positions with high strength requirements such as the positions where the passengers sit, and a carbon fiber composite sandwich skin is used in other positions with less stress to improve rigidity. The fuselage skin cooperates with the skeleton to bear the load transmitted by the front and rear landing gears, and has high bearing capacity;

[0013] Light weight: The fuselage skin consists of only two large left and right skins, the front landing gear cover and the rear landing gear cover. The number of parts is small, the product has a high degree of integration, and the product structure weight and connection relationship are effectively reduced;

[0014] Good maintainability: The front and rear landing gear covers are designed at the lower part of the fuselage skin. After removing the covers, the landing gear can be exposed as a whole, which is convenient for disassembly, installation and maintenance of the landing gear;

[0015] Good compatibility: The fuselage skin is designed with drainage holes in the bottom area and openings for avionics equipment installation. During use, cabin condensation water can be discharged in time, while providing support for avionics equipment;

[0016] Good processability: Both the left and right skins are formed by laying out carbon fiber composite materials, which have a high degree of freedom in forming and can effectively form complex curved surfaces, solving the problem that metal skins cannot form complex curved surfaces. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is an axonometric drawing of the utility model;

[0018] Figure 2 It is an exploded view of the utility model;

[0019] Figure 3 It is an axonometric view of the left skin of the utility model;

[0020] Figure 4 It is an axonometric view of the right skin of the utility model;

[0021] Figure 5 It is a partial view of the surrounding skin of the cabin door opening of the utility model;

[0022] Figure 6 It is a partial view of the bottom of the right skin of the utility model;

[0023] Figure 7 It is a cross-sectional view of the adhesive joint between the left and right skins of the utility model;

[0024] Figure 8 This is a cross-sectional view of the foam core skin of the utility model;

[0025] Fig. 9 It is an axonometric view of the utility model in the position of an eVTOL aircraft.

[0026] In the figure, 1. fuselage skin; 11. left skin; 111. left cockpit door opening; 112. cabin door opening; 1121. hinge opening; 1122. latch opening; 113. cargo door opening; 114. left windshield opening; 115. front landing gear mounting hole; 116. avionics equipment opening; 117. rear landing gear mounting hole; 118. left sealing edge; 119. right sealing edge; 12. right skin; 121. right cockpit door opening; 122. window opening; 123. window reinforcement; 124. right windshield opening; 126. drainage hole; 13. front landing gear cover; 14. rear landing gear cover; 15. structural adhesive; 2. eVTOL aircraft; 16. foam sandwich skin; 161. foam; 162. carbon fiber. DETAILED DESCRIPTION

[0027] 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.

[0028] Example

[0029] like Fig. 9As shown, the fuselage skin 1 is the outer shape of the fuselage, and together with the fuselage frame, it forms the passenger space to meet the requirements of passenger safety and riding comfort. The upper part cooperates with the skin of the central wing, and the landing gear and its connection area are at the bottom of the fuselage skin 1. The fuselage skin 1 maintains the fuselage shape of the eVTOL aircraft 2 and provides cabin and eVTOL aircraft doors, windshields, and window openings.

[0030] like Figure 1 and Figure 2 As shown, the fuselage skin 1 includes a left skin 11, a right skin 12, a front landing gear cover 13, and a rear landing gear cover 14. The left skin 11 and the right skin 12 are bonded at the middle joint position using a structural adhesive 15. The left skin 11 provides a large opening on the left side for passengers and cargo to enter and exit the fuselage, and the right skin 12 provides a large opening on the right side for passengers to enter and exit. The front landing gear cover 13 and the rear landing gear cover 14 correspond to the positions of the front landing gear and the rear landing gear, and cover the connection area between the landing gear and the fuselage. The front landing gear mounting hole 115 and the rear landing gear mounting hole 117 are formed between the front landing gear cover 13, the rear landing gear cover 14 and the left skin 11 and the right skin 12. The front landing gear mounting hole 115 and the rear landing gear mounting hole 117 are used to install the skid-type landing gear, and a certain deformation safety distance is reserved, which is 10 mm in this example.

[0031] like Figure 3 , Figure 4 As shown, the left skin 11 and the right skin 12 have similar structures. A thicker carbon fiber composite laminate is used in the area where the passengers sit, which has higher strength and can effectively protect the passengers in an emergency. The front and rear areas use a foam sandwich skin 115, and the carbon fiber wrapped outside the foam is thinner, which can effectively reduce the weight and have better rigidity to maintain the shape of the skin.

[0032] The left skin 11 is respectively designed with a left cockpit door opening 111, a cabin door opening 112, a cargo door opening 113, and a left windshield opening 114, which cooperate with the left cockpit door, cabin door, cargo door, and left windshield respectively. The edge skins of the left cockpit door opening 111, cabin door opening 112, and cargo door opening 113 are designed with a left sealing edge 118, which cooperates with the left cockpit door, cabin door, and cargo door to seal and prevent rainwater from flowing in. The skin at the edge of the left windshield opening 114 is sunken and is bonded to the left windshield with glass glue. The front, rear, and lower areas of the left skin 11, which are less stressed, are designed as foam sandwich skins 16, which provide high rigidity while being lightweight. An avionics equipment opening 116 is designed in the lower area to provide installation access and support for some of the exposed avionics equipment arranged in the lower area of ​​the fuselage.

[0033] The right skin 12 is respectively designed with a right cockpit door opening 121, a window opening 122, and a right windshield opening 124, which cooperate with the right cockpit door, the window, and the right windshield, respectively. The edge skin of the right cockpit door opening 121 is designed with a right sealing edge 119, which cooperates with the right cockpit door to seal and prevent rainwater from flowing in. The skin at the edge of the window opening 122 is sunken, and is bonded to the window and the right windshield with glass glue. The window opening 122 is a large opening, and a window reinforcement 132 is provided in the upper and lower regions for local reinforcement. The window reinforcement 123 can be a separate part, or it can be formed by locally adding foam and carbon fiber plies to co-curing. This example adopts local addition of foam and carbon fiber plies to co-curing to reduce manufacturing costs. The foam sandwich skin 16 on the right skin 12 is similar to the left skin 11, respectively in the front, rear and lower regions.

[0034] like Figure 5 As shown, the skin around the cabin door opening 112 is designed with openings that cooperate with the cabin door hinge and lock. At the upper part that cooperates with the hinge, three hinge openings 1121 are designed to meet the clearance requirement for the cabin door hinge movement, which is 12.7 mm in this example. Two lock tongue openings 1122 are designed at the front and rear parts that cooperate with the lock for the lock tongue to pass through and lock the cabin door.

[0035] like Figure 6 As shown, since there will be condensed water inside the cabin, it will accumulate at the lowest point of the skin due to gravity, so a drainage hole 126 is designed on the right skin 12 at the lowest point to drain the condensed water.

[0036] like Figure 7 As shown, the left skin 11 and the right skin 12 are bonded together in the upper and lower regions by using structural adhesive, and the right skin 12 is designed with a flange, and the flange length is not less than 20 mm to ensure the bonding strength.

[0037] like Figure 8 As shown, the foam sandwich skin area of ​​the left skin 11 and the right skin 12 adopts the method of internal foam and external carbon fiber wrapping. Compared with the laminate, the thickness of the carbon fiber in the upper and lower parts of the foam is thinner, and the density of the foam is lower, which can effectively reduce the structural weight and improve the out-of-plane stiffness of the foam sandwich area.

[0038] 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 fuselage skin, comprising a left skin and a right skin, characterized in that: The left skin and the right skin are placed opposite to each other, and the middle parts of the left skin and the right skin are connected to each other. The bottoms of the left skin and the right skin cooperate with the front landing gear cover and the rear landing gear cover to form the front landing gear mounting hole and the rear landing gear mounting hole. The left skin is provided with a left cockpit door opening, a passenger cabin door opening, a cargo door opening, and a left windshield opening. The left cockpit door opening, the passenger cabin door opening, and the cargo door opening are surrounded by a left sealing edge.

2. The eVTOL aircraft fuselage skin according to claim 1, characterized in that: The right cover is provided with a right cockpit door opening, a window opening and a right windshield opening, and a right sealing edge is arranged around the right cockpit door opening.

3. The eVTOL aircraft fuselage skin according to claim 1, characterized in that: The upper side of the cabin door opening is provided with a hinge opening, and the front and rear sides are provided with lock tongue openings.

4. The eVTOL aircraft fuselage skin according to claim 1, characterized in that: A drainage hole is provided at the bottom of the right skin.

5. The eVTOL aircraft fuselage skin according to claim 1, characterized in that: The periphery of the right skin is provided with a flange, and the middle part of the right skin and the left skin are connected by structural adhesive in combination with the flange.

6. The eVTOL aircraft fuselage skin according to claim 2, characterized in that: Window reinforcements are provided at the upper and lower parts of the window opening.

7. The eVTOL aircraft fuselage skin according to claim 1, characterized in that: The left and right skins are formed of carbon fiber composite laminates in the passenger seating area, and foam sandwich skins are formed in the front and rear areas.

8. The eVTOL aircraft fuselage skin according to claim 7, characterized in that: The foam sandwich skin is a structure with foam inside and carbon fiber wrapped outside.

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