EVTOL aircraft cargo compartment structure

Abstract

The utility model discloses an eVTOL aircraft cargo hold structure which comprises a cargo hold body and a skin, the skin is installed on the cargo hold body, the cargo hold body comprises a sealing frame assembly, the sealing frame assembly is connected with one end of a floor, the other end of the floor is connected with a tail frame, and the two sides of the floor are connected with a floor beam I and a floor beam II. The two ends of the floor beam I and the two ends of the floor beam II are connected with the sealing frame assembly and the tail frame, the bottom of the floor is connected with the supporting frame, the hinge longitudinal beam is arranged above the floor beam I, and the two ends of the hinge longitudinal beam are connected with the sealing frame assembly and the tail frame. The space of the structure is large, namely, the areas among the tail frame, the frame sealing assembly and the floor and enclosed by the left and right skins can be filled with goods, so that the loading space is large; the cargo hold and the passenger cabin at the front part are separated by the sealing plate, so that when the eVTOL aircraft lands emergently, cargoes in the cargo hold are prevented from entering the passenger cabin due to inertia, and passengers are prevented from being hurt.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, and in particular to an eVTOL aircraft cargo compartment structure. 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 cargo hold of the eVTOL aircraft provides space for passengers to load luggage, and the size, weight, and convenience of picking up and placing luggage of passengers need to be considered; while meeting the functional requirements, the weight of the cargo hold structure needs to be reduced as much as possible. In addition, many of the existing cargo holds, such as the pressurized cargo hold of transport aircraft, the cargo hold of drones, and the luggage hold of helicopters and general aviation aircraft, do not separate the cargo hold from the front passenger cabin during design, such as patent 202310425372.8 (aircraft cargo hold and drone), which poses a safety hazard. Utility Model Content

[0004] The purpose of the utility model is to provide an eVTOL aircraft cargo hold structure 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 cargo hold structure, including a cargo hold body and a skin, the skin is installed on the cargo hold body, the cargo hold body includes a sealing frame assembly, the sealing frame assembly is connected to one end of the floor, the other end of the floor is connected to the tail frame, the two sides of the floor are connected with floor beams I and II, the ends of the floor beams I and II are connected to the sealing frame assembly and the tail frame, the bottom of the floor is connected to a support frame, a hinged longitudinal beam is provided above the floor beam I, and the two ends of the hinged longitudinal beam are connected to the sealing frame assembly and the tail frame.

[0005] Preferably, the skin comprises a left skin and a right skin, the left skin is provided with a cargo hold opening, the floor beam I and the hinged longitudinal beam are located at the upper and lower sides of the cargo hold opening and are fixedly connected.

[0006] Preferably, the sealing frame assembly includes a sealing frame, which is an annular structure as a whole, a crossbeam is installed on the sealing frame as a whole, a sealing plate is connected to the sealing frame, the middle part of the sealing plate is connected to the crossbeam, and the sealing plate is a carbon fiber composite material foam sandwich structure.

[0007] Preferably, a hinge support is provided on the hinge longitudinal beam.

[0008] Preferably, the floor is a structural member formed by integrally curing a carbon fiber layer on the surface and a foam core inside.

[0009] Preferably, the cargo hold body is bonded to the skin by means of structural adhesive.

[0010] The technical effects and advantages of the utility model are as follows: the structure has a large space: the area between the tail frame, the sealing frame assembly and the floor and surrounded by the left and right skins can be loaded with goods, and the loading space is large;

[0011] Good safety: The sealing plate separates the cargo hold from the front passenger cabin to prevent the cargo in the cargo hold from entering the passenger cabin due to inertia when the eVTOL aircraft makes an emergency landing, causing harm to the passengers;

[0012] High rigidity: The carbon fiber composite floor and cover board with foam core are light in weight and high in rigidity.

[0013] Benefits the center of gravity of the whole aircraft: The cargo hold is close to the center of gravity of the eVTOL aircraft. When the weight of the cargo in the cargo hold changes, the center of gravity of the whole aircraft is less affected, which is beneficial to the flight of the eVTOL aircraft.

[0014] Good maintainability: The sealing plate and sealing frame, the floor and floor beam I, floor beam II, tail frame and support frame are all connected with fasteners. When the floor and sealing plate are damaged, they can be easily replaced. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is an axonometric drawing of the utility model;

[0016] Figure 2 It is an exploded view of the utility model;

[0017] Figure 3 This is an axonometric view of the cargo hold body of the utility model;

[0018] Figure 4 It is an axonometric view of the sealing frame assembly of the utility model;

[0019] Figure 5 It is an axonometric view of the hinged longitudinal beam of the utility model;

[0020] Figure 6 It is a cross-sectional view of the floor of the utility model;

[0021] Figure 7 It is an axonometric view of the utility model in the position of an eVTOL aircraft.

[0022] In the figure, 1. cargo hold structure; 11. cargo hold body; 111. sealing frame assembly; 1111. sealing plate; 1112. sealing frame; 11121. cross beam; 112. support frame; 113. tail frame; 114. hinge longitudinal beam; 1141. hinge support; 115. floor beam I; 116. floor beam II; 117. floor; 1171. carbon fiber layer; 1172. foam core; 12. skin; 121. right skin; 122. left skin; 1221. cargo hold opening; 2. eVTOL aircraft. DETAILED DESCRIPTION

[0023] 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.

[0024] Example

[0025] like Figure 7 As shown, the cargo hold structure 1 is arranged at the rear of the passenger cabin of the eVTOL aircraft 2 and in front of the tail wing, and is closer to the center of gravity. When the weight of the cargo and luggage inside the cargo hold changes, the impact on the center of gravity is small. In addition to bearing the weight of the internal luggage, the cargo hold structure 1 also bears the load transmitted from the tail wing and transmits the tail wing load to the middle fuselage.

[0026] like Figure 1 , Figure 2 As shown, the cargo hold structure 1 includes a cargo hold body 11 and a skin 12. The skin 12 is installed on the cargo hold body 11. The skin 12 is divided into two parts, namely a left skin 122 and a right skin 121. The left skin 122 is provided with a cargo hold opening 1221 for installing a cargo door, for taking and placing luggage inside the cargo hold structure. The cargo hold body 11 is a skeleton structure, which mainly provides the functions of strengthening the skin 12 and fixing the internal luggage, transferring the weight load of the internal luggage, and transferring part of the load of the fuselage. The skin 12 constitutes the outer surface of the eVTOL aircraft 2 in the cargo hold structure area, ensuring the aerodynamic shape, and at the same time transferring the load transferred by the tail wing. The skin 12 can be an aluminum alloy extended stringer structure or a carbon fiber laminate extended stringer structure. This example adopts a carbon fiber composite foam sandwich structure, which has a small number of parts, a large out-of-plane stiffness, and will not buckle during flight. The surface where the structure of the cargo hold body 11 contacts the skin 12 is bonded with a structural adhesive.

[0027] like Figure 3 As shown, the cargo hold body 11 includes a sealing frame assembly 111, a support frame 112, a tail frame 113, a hinged longitudinal beam 114, a floor beam I 115, a floor beam II 116, and a floor 117. The sealing frame assembly 111 is connected to one end of the floor 117, and the other end of the floor 117 is connected to the tail frame 113. The floor 117 is connected to the floor beam I 115 and the floor beam II 116 on both sides. Both ends of the floor beam I 115 and the floor beam II 116 are connected to the sealing frame assembly 111 and the tail frame 113. The hinged longitudinal beam 114 is arranged above the floor beam I 115, and both ends of the hinged longitudinal beam 114 are connected to the sealing frame assembly 111 and the tail frame 113. The sealing frame assembly 111 separates the passenger cabin at the front of the fuselage from the cargo hold structure 1 to prevent the luggage inside the cargo hold structure 1 from rushing into the passenger cabin to cause harm to the passengers when the eVTOL aircraft 2 makes an emergency landing, and also prevents the passengers inside the passenger cabin from entering the cargo hold structure 1.

[0028] The support frame 112 is supported and installed at the lower part of the floor 117. Since the floor 117 is large in size and heavy objects such as luggage are pressed on the floor 117, in order to improve the bearing capacity of the floor 117, the support frame 112 is designed in the middle area of ​​the floor 117; the floor 117 is supported by the tail frame 113, the floor beam I 115, the floor beam II 116 and the sealing frame assembly 111 on all sides, which are connected by fasteners. When the floor is damaged, it is convenient to replace the floor 117. The floor beam I 115, the floor beam II 116 and the support frame 112 are all made of carbon fiber composite materials, and the area connected to the skin 12 is glued with structural adhesive. In addition to supporting the floor 117, the tail frame 113 also supports the skin 12 to improve the stability of the skin 12 and prevent the skin 12 from buckling when it is stressed. The connection point designed on the tail frame 113 with the luggage fixing device will bear concentrated force, so it is made of aluminum alloy. The preferred material is 7075, and the heat treatment state is T7351.

[0029] The hinged longitudinal beam 114 and the floor beam I 115 reinforce the cargo hold opening 1221 on the left skin 122 , thereby increasing the strength of the cargo hold opening 1221 area and transferring the load of the opening area through the hinged longitudinal beam 114 and the floor beam I 115 .

[0030] like Figure 4 As shown, the sealing frame assembly 111 includes a sealing plate 1111 and a sealing frame 1112. The sealing frame 1111 is an annular structure as a whole, and a reinforcing crossbeam 11121 is installed in the middle. Due to the large overload of luggage in the forward direction during emergency landing, in order to prevent the luggage from entering the cabin and causing harm to the passengers, it is necessary to provide additional support for the sealing plate 1111. In this example, the crossbeam 11121 is used to support the sealing plate 1111 and resist the inertial force of the luggage. Another solution is to design the reinforced crossbeam 11121 in a vertical direction, which can also meet the requirements. The sealing plate 1111 needs to provide a structure to resist the inertial force of the luggage. In this example, a carbon fiber composite foam sandwich structure is used. The sealing plate 1111 is connected to the sealing frame 1112 and the crossbeam 11121 by fasteners on all sides. The crossbeam 11121 can be installed on the sealing frame 1112 by assembly, or it can be integrally processed together with the sealing frame 1112. The sealing frame 1112 requires greater rigidity. In this example, the sealing frame 1112 and the crossbeam 11121 are integrally machined from aluminum alloy, the material is 7075, and the heat treatment state is T7351.

[0031] like Figure 5 As shown, a hinge support 1141 is designed on the hinge longitudinal beam 114, which is connected to the hinge of the cargo door and rotates around the axis of the hinge support 1141 to achieve the purpose of opening and closing the cargo door. The hinge support 1141 and the hinge longitudinal beam 114 are directly formed by integral machining of aluminum alloy, the material is 7075, and the heat treatment state is T7351.

[0032] like Figure 6 As shown, the floor 117 is formed by solidifying the carbon fiber layer on the surface and the foam core inside. The foam core has a low density and supports the height of the floor 117, improves the out-of-plane stiffness of the floor 117, and enables it to withstand heavier loads. The foam core material used in this example is polyurethane foam with a density of 60kg / m 3 .

[0033] 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 cargo hold structure, comprising a cargo hold body and a skin, characterized in that: The skin is installed on the cargo hold body, and the cargo hold body includes a sealing frame assembly, the sealing frame assembly is connected to one end of the floor, and the other end of the floor is connected to the tail frame, floor beams I and II are connected on both sides of the floor, and both ends of the floor beams I and II are connected to the sealing frame assembly and the tail frame, and the bottom of the floor is connected to a support frame, and a hinged longitudinal beam is provided above the floor beam I, and the two ends of the hinged longitudinal beam are connected to the sealing frame assembly and the tail frame.

2. The eVTOL aircraft cargo hold structure according to claim 1, characterized in that: The skin comprises a left skin and a right skin, the left skin is provided with a cargo hold opening, the floor beam I and the hinged longitudinal beam are located at the upper and lower sides of the cargo hold opening and are fixedly connected.

3. The eVTOL aircraft cargo hold structure according to claim 1, characterized in that: The sealing frame assembly comprises a sealing frame, which is an annular structure as a whole, a crossbeam is installed on the sealing frame as a whole, a sealing plate is connected to the sealing frame, the middle part of the sealing plate is connected to the crossbeam, and the sealing plate is a carbon fiber composite material foam sandwich structure.

4. The eVTOL aircraft cargo hold structure according to claim 1, characterized in that: A hinge support is arranged on the hinge longitudinal beam.

5. The eVTOL aircraft cargo hold structure according to claim 1, characterized in that: The floor is a structural component formed by solidifying the carbon fiber layer on the surface and the foam core inside.

6. The eVTOL aircraft cargo hold structure according to claim 2, characterized in that: The cargo hold body is bonded to the skin by means of structural adhesive.

Images