Supporting structure for eVTOL aircraft floor

Abstract

The utility model discloses a supporting structure for an eVTOL aircraft floor, which comprises a floor and a supporting beam, an equipment plate assembly is mounted on the supporting beam, the equipment plate assembly and the supporting beam form an avionics cabin, avionics equipment is mounted in the avionics cabin, and the floor is positioned above the avionics cabin and is connected with the supporting beam; the supporting beam comprises a plurality of longitudinal beams, the longitudinal beams are distributed adjacently, a cross beam is installed between every two longitudinal beams, and the bottom of the floor is connected with the longitudinal beams and the cross beams. The structure is high in space utilization rate: the avionics equipment and a passage for connecting the avionics equipment with the wiring harness are arranged at the lower part of the floor, the space at the lower part of the floor is fully utilized, the occupation of the avionics equipment on other area spaces is reduced, and the space utilization efficiency is high.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, and in particular to a supporting structure for an eVTOL aircraft floor. 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 is 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, 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 eVTOL aircraft is an electric-powered fly-by-wire aircraft with a large number of devices and a large occupied volume. It is necessary to reasonably arrange the relevant equipment to make full use of the space of the eVTOL aircraft. The floor in the cabin is generally a flat structure to facilitate the needs of passengers, so that the area enclosed between the floor and the lower skin of the fuselage can be fully utilized. However, the floor support structure of existing aircraft, such as large passenger aircraft, general aviation small aircraft, helicopters, etc., cannot meet the needs of eVTOL aircraft. Utility Model Content

[0004] The purpose of the utility model is to provide a support structure for the floor of an eVTOL aircraft to solve the problems mentioned in the background technology. To achieve the above purpose, the utility model provides the following technical solutions: a support structure for the floor of an eVTOL aircraft, comprising a floor and a support beam, an equipment plate assembly is installed on the support beam, the equipment plate assembly and the support beam form an avionics cabin, avionics equipment is installed inside the avionics cabin, the floor is located above the avionics cabin and connected to the support beam; the support beam includes a longitudinal beam, the longitudinal beam is provided with a plurality of adjacently distributed longitudinal beams, a cross beam is installed between two longitudinal beams, and the bottom of the floor connects the longitudinal beam and the cross beam.

[0005] Preferably, the longitudinal beam is provided with connecting ribs, the connecting ribs are connected to the cross beam, the longitudinal beam is provided with lightening holes, and the sides of the lightening holes are provided with reinforcing ribs.

[0006] Preferably, the equipment plate assembly comprises an equipment plate body, the equipment plate body is connected with brackets on all sides, and the brackets connect longitudinal beams and transverse beams.

[0007] Preferably, a mounting channel is provided on the equipment plate body.

[0008] Preferably, the floor is a carbon fiber foam sandwich structure.

[0009] Preferably, the cross beam adopts a segmented structure and is connected to the longitudinal beam by fasteners.

[0010] Preferably, the equipment plate body is a carbon fiber composite material structure, and the bracket is a carbon fiber composite material.

[0011] The technical effects and advantages of the utility model are as follows: the structure has high space utilization rate: the passages for the avionics equipment and its connecting harnesses are arranged under the floor, which makes full use of the space under the floor, reduces the space occupied by the avionics equipment in other areas, and has high space utilization efficiency;

[0012] Good safety: The support beam is composed of longitudinal beams in the front and rear directions and transverse beams in the left and right directions. At the same time, oblique reinforcement ribs are designed in the upper and lower directions to meet the safety requirements of the eVTOL aircraft in the front, rear, left and right directions for emergency landing, and meet the crash requirements in the upper and lower directions;

[0013] Lightweight: The longitudinal beams and cross beams adopt a three-dimensional reinforced structure, and most areas are lightening holes, which meet the performance requirements while being lightweight;

[0014] Good maintainability: The entire floor above the avionics equipment is a detachable structure. When the avionics equipment under the floor needs to be maintained, the avionics equipment can be exposed after the floor is removed, making maintenance easier. 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 the axonometric view of the utility model after the floor is hidden;

[0018] Figure 4 This is an axonometric view of the support beam of the utility model;

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

[0020] Figure 6 It is an axonometric view of the equipment plate assembly of the utility model;

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

[0022] In the figure, 1. support structure for floor; 11. floor; 12. support beam; 121. longitudinal beam; 1211. connecting rib; 1212. reinforcing rib; 1213. lightening hole; 122. cross beam; 13. equipment plate assembly; 131. equipment plate body 1311. installation channel; 132. bracket; 14. avionics equipment; 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 floor support structure 1 is arranged at the lower part of the cabin of the eVTOL aircraft 2, the floor 11 supports the occupants, and the support structure provides support for the floor. In addition to bearing the load of the occupants inside the cabin, the floor support structure 1 also bears the inertia force of the internal equipment and personnel of the eVTOL aircraft 2 during emergency landing, and also absorbs energy through deformation to try to ensure the survival rate of the occupants in the cabin.

[0026] like Figure 1 , Figure 2 , Figure 3 As shown, the floor support structure 1 includes a floor 11, a support beam 12, an equipment plate assembly 13 and an avionics device 14, the equipment plate assembly 13 is mounted on the support beam 12, the avionics device 14 is mounted on the equipment plate assembly 13, the floor 11 is located above the avionics device 14 and connected to the support beam 12; the floor 11 remains flat, and the upper part supports the occupants, so that the occupants can move conveniently inside the eVTOL aircraft 2. Considering the lightweight and the riding quality of the occupants, the floor 11 needs to have a high rigidity so that the occupants will have less deformation when stepping on the floor 11. Therefore, the floor 11 preferably adopts a composite sandwich structure, which can be a glass fiber honeycomb sandwich structure, a carbon fiber honeycomb sandwich structure, a glass fiber foam sandwich structure, or a carbon fiber foam sandwich structure. This embodiment adopts a carbon fiber foam sandwich structure.

[0027] The support beam 12 supports the floor 11 and is connected to the floor 11 by fasteners. The fasteners can be screws, etc. When the floor 11 needs to be replaced, it can be easily replaced. The support beam 12 is the main force-bearing component, which transmits the forces of the eVTOL aircraft 2 in the front and rear, left and right, and up and down directions. The frame structure formed has a high energy absorption capacity. When the eVTOL aircraft 2 crashes, the support beam 12 absorbs energy by deformation, thereby protecting the occupants inside the eVTOL and improving the occupant survival rate.

[0028] The equipment board assembly 13 provides an installation interface for the avionics equipment 14, which is used to fix the avionics equipment 14. The equipment board assembly 13 is installed on the support beam 12. The two cooperate to form a fixed avionics cabin at the bottom of the floor 11. The avionics equipment 14 is installed inside the avionics cabin. The environment of the avionics equipment area is relatively clean, which is conducive to the use of the avionics equipment 14. The avionics equipment 14 is used to control the control, navigation, data transmission, etc. of the eVTOL aircraft 2, and meets the fly-by-wire control requirements of the eVTOL aircraft 2.

[0029] like Figure 4 As shown, the support beam 12 includes a longitudinal beam 121 in the front-to-back direction and a cross beam 122 in the left-to-right direction. A plurality of longitudinal beams 121 are provided and are adjacently distributed. A cross beam 122 is installed between two longitudinal beams 121. According to the requirements of relevant airworthiness regulations, the load in the front-to-back direction is greater than the load in the left-to-right direction. Therefore, the longitudinal beam 121 remains continuous. The cross beam 122 is a segmented beam connected to the longitudinal beam 121 by fasteners. Both the cross beam 122 and the longitudinal beam 121 are machined from aluminum alloy. The preferred material is 7075, and the preferred heat treatment state is T7351.

[0030] like Figure 5 As shown, the longitudinal beam 121 is designed with connecting ribs 1211 connected to the cross beam 122, reinforcing ribs 1212 for reinforcement, and lightening holes 1213; the connecting ribs 1211 cooperate with the cross beam 122 and are connected by fasteners, so that the longitudinal beam 121 and the cross beam 122 form an integral frame structure; the reinforcing ribs 1212 are located on the side of the lightening hole 1213 and form a certain angle with the axis of the longitudinal beam 121 to bear the loads in the front and rear and up and down directions. The reinforcing ribs 1212 and the connecting ribs 1211 are integrally processed, and the lightening holes 1213 are designed at the position of the longitudinal beam 121 with less stress to reduce the structural weight. At the same time, the lightening holes 1213 also provide a passage for the eVTOL aircraft wiring harness to pass through the lower part of the floor 11.

[0031] like Figure 6As shown, the equipment board assembly 13 includes an equipment board body 131 and a bracket 132. The bracket 132 is connected to the equipment board body 131 on all sides and connected to the support beam 12. The bracket 132 can be made of carbon fiber composite material or aluminum alloy sheet metal. This embodiment uses carbon fiber composite material to reduce weight. The equipment board body 131 needs to provide higher rigidity to reduce vibration in the connection area of ​​the avionics equipment 14 and prevent vibration from affecting the data collection of the avionics equipment 14. This embodiment uses a 3mm thick carbon fiber composite plate. An installation channel 1311 is designed on the equipment board body 131. Through the installation channel 1311, the installation tool can be extended to the lower part of the equipment board body 131 to install and remove the avionics equipment 14.

[0032] 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. A support structure for an eVTOL aircraft floor, comprising a floor and a support beam, characterized in that: An equipment plate assembly is installed on the support beam, and the equipment plate assembly and the support beam form an avionics cabin. Avionics equipment is installed inside the avionics cabin. The floor is located above the avionics cabin and connected to the support beam. The support beam includes a longitudinal beam, and a plurality of longitudinal beams are provided and distributed adjacent to each other. A cross beam is installed between two of the longitudinal beams, and the bottom of the floor connects the longitudinal beams and the cross beams.

2. The eVTOL aircraft floor support structure according to claim 1, characterized in that: The longitudinal beam is provided with connecting ribs, the connecting ribs are connected to the cross beam, the longitudinal beam is provided with lightening holes, and the sides of the lightening holes are provided with reinforcing ribs.

3. The eVTOL aircraft floor support structure according to claim 1, characterized in that: The equipment plate assembly comprises an equipment plate body, and brackets are connected to the equipment plate body on all sides, and the brackets are connected to the longitudinal beams and the transverse beams.

4. The eVTOL aircraft floor support structure according to claim 3, characterized in that: A mounting channel is provided on the equipment board body.

5. The eVTOL aircraft floor support structure according to claim 1, characterized in that: The floor is a carbon fiber foam sandwich structure.

6. The eVTOL aircraft floor support structure according to claim 1, characterized in that: The cross beam adopts a segmented structure and is connected to the longitudinal beam with fasteners.

7. The eVTOL aircraft floor support structure according to claim 3, characterized in that: The equipment plate body is a carbon fiber composite material structure, and the bracket is a carbon fiber composite material.

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