Integrated installation structure of eVTOL aircraft equipment compartment
The modular equipment bay integration solution solves the problem of insufficient design flexibility of eVTOL aircraft equipment bays, enabling rapid disassembly and replacement of equipment, and improving the efficiency of aircraft use and ease of maintenance.
Patent Information
- Application Number
- CN202520032794.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-07
- Publication Date
- 2025-12-16
- Estimated Expiration
- 2035-01-07
AI Technical Summary
The existing eVTOL aircraft equipment bay design lacks flexibility and adaptability, failing to meet the rapidly changing flight mission requirements, and equipment replacement is complex and costly.
A modular equipment compartment integration solution is adopted, which enables rapid disassembly and replacement of equipment through equipment compartment mounting sections and equipment compartment panel assemblies. Standardized interfaces and modular design are used. The equipment mounting plate is fixed to the equipment compartment bracket with nuts and fasteners. The equipment compartment is located in the middle and rear of the passenger cabin. The equipment compartment bracket is fixed to the cabin beam. Universal installation interfaces are set on the equipment mounting plate.
It enables rapid equipment replacement and maintenance, facilitates operation, reduces the impact of equipment replacement on the aircraft itself, and improves the efficiency and ease of maintenance of the aircraft.
Smart Images
Figure CN223672801U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to the field of aircraft, especially to an eVTOL aircraft equipment cabin integrated installation structure. BACKGROUND
[0002] With the gradual development of low-altitude economy, various types of eVTOL, i.e., electric vertical take-off and landing aircraft, are being rapidly developed. In the development process of a certain type of tilt configuration eVTOL, in order to meet various needs such as testing, configuration improvement, and simulated test flight, various different equipment or combinations of different equipment need to be arranged in the aircraft equipment cabin. Different equipment has different installation interfaces and requirements, resulting in the need for more manpower and time to replace equipment on site each time. Moreover, due to the limited installation space and available interfaces of the equipment cabin, the frequent replacement of equipment cannot be met.
[0003] To solve the above problems, in the existing eVTOL aircraft design, a fixed equipment cabin design is usually adopted, i.e., the layout and interfaces of the equipment cabin are preset during aircraft manufacturing. However, this design method, although simplifying the on-site operation to a certain extent, has poor flexibility and adaptability, and cannot adapt to the rapidly changing flight task requirements. In addition, the fixed equipment cabin design also limits the upgrading and maintenance of the aircraft. Once the equipment cabin layout is determined, subsequent improvement and upgrading will become complex and costly.
[0004] In view of the above problems, the present patent proposes a modular equipment cabin integration scheme for eVTOL aircraft. SUMMARY
[0005] The utility model provides a kind of eVTOL aircraft equipment cabin integrated installation structure, including equipment cabin installation section (21) and equipment cabin plate assembly (22), equipment cabin installation section (21) includes equipment cabin support (211), support fastener (212) and backing plate nut (213), equipment cabin plate assembly (22) includes equipment installation plate (221) and installation plate fastener (222);Equipment cabin support (211) side is installed in equipment cabin left and right beam inner side, and equipment cabin support (211) is fixed on equipment cabin left and right beam by support fastener (212), equipment cabin support (211) top lower surface is provided backing plate nut (213), the both ends of equipment installation plate (221) are pressed on the top of equipment cabin support (211), and equipment installation plate (221) is fixed with equipment cabin support (211) by rotating installation plate fastener (222) into backing plate nut (213).
[0006] As described above, in an eVTOL aircraft equipment compartment integrated installation structure, the equipment compartment bracket (211) in the equipment compartment installation section (21) is in an "L" shape, formed by a horizontal arm and a vertical arm. A support plate nut (213) is installed at the bottom of the horizontal arm, and the vertical arm is fixed to the inner side of the left and right beams of the equipment compartment by bracket fasteners (212).
[0007] As described above, in an eVTOL aircraft equipment bay integrated installation structure, an equipment mounting plate (221) is mounted on the horizontal arm of an equipment bay bracket (211). Holes are made on the edge of the equipment mounting plate (221) at corresponding positions to the support plate nuts (213) of the equipment bay bracket (211). The mounting plate fasteners (222) pass through the holes on the equipment mounting plate (221) and are connected to the support plate nuts (213).
[0008] As described above, in an eVTOL aircraft equipment bay integrated installation structure, the equipment bay crossbeam (223) is glued to the bottom of the equipment mounting plate (221).
[0009] In the above-described eVTOL aircraft equipment bay integrated installation structure, the top of the horizontal arm of the equipment bay bracket (211) is flush with the top of the equipment bay crossbeam (223).
[0010] As described above, an integrated installation structure for an eVTOL aircraft equipment bay includes a universal installation interface (224) for equipment modules on an equipment mounting plate (221).
[0011] As described above, in an eVTOL aircraft equipment bay integrated installation structure, the equipment bay is located below the equipment bay floor in the rear middle part of the passenger cabin.
[0012] As described above, the integrated installation structure for the equipment compartment of an eVTOL aircraft includes a front and rear frame, left and right beams, and a floor. The front and rear frame and the left and right beams are fixedly welded to form a support frame structure, and the floor is detachably connected to the support frame structure.
[0013] The beneficial effects achieved by this utility model are as follows:
[0014] (1) The eVTOL aircraft equipment bay integrated installation structure provided by this utility model has a simple configuration, a simple and clear principle, and is universal;
[0015] (2) Different equipment installation modules are consistent with the aircraft interface. When replacing equipment, the aircraft body does not need to be modified and has no impact on the aircraft body.
[0016] (3) Whether installing or replacing equipment, only one side of the screw needs to be tightened, which is simple to operate, does not require special tools, and is safe and convenient. Attached Figure Description
[0017] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this utility model. For those skilled in the art, other drawings can be obtained based on these drawings.
[0018] Figure 1 This is a schematic diagram showing the location of the equipment bay on an eVTOL aircraft.
[0019] Figure 2 This is a schematic diagram of the fuselage equipment bay structure of an eVTOL aircraft.
[0020] Figure 3 A top view of the fuselage equipment bay structure of an eVTOL aircraft;
[0021] Figure 4 A schematic diagram of an integrated installation structure for an eVTOL aircraft equipment bay is provided for this utility model.
[0022] Figure 5 Left view of the integrated installation structure;
[0023] Figure 6 Front view of the integrated installation structure;
[0024] Figure 7 for Figure 3 Partial cross-sectional view of the AA position;
[0025] Figure 8 for Figure 4 Partial cross-sectional view of the BB location;
[0026] Figure 9 Diagram of equipment installation modules.
[0027] Figure label:
[0028] 11. Equipment compartment front frame; 12. Equipment compartment left beam; 13. Equipment compartment rear frame; 14. Equipment compartment right beam; 15. Equipment compartment floor; 2. Equipment compartment mounting section; 22. Equipment compartment panel assembly; 211. Equipment compartment bracket; 212. Bracket fasteners; 213. Support plate nuts; 221. Equipment mounting plate; 222. Mounting plate fasteners; 223. Equipment compartment crossbeam; 224. Equipment module universal installation interface. Detailed Implementation
[0029] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are some of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of the utility model.
[0030] Embodiment
[0031] Figure 1 The figure shows the position of the equipment cabin of the eVTOL aircraft, and the center of gravity of the passenger cabin of the eVTOL aircraft is located in the middle and rear part of the fuselage. The equipment cabin proposed in the utility model considers the distribution and position of the center of gravity of the equipment, and is also arranged below the equipment cabin floor in the middle and rear part of the fuselage passenger cabin, thereby ensuring the stability and safety of the equipment during flight.
[0032] Figure 2 And Figure 3 The figure shows the structure of the equipment cabin, which comprises an equipment cabin front and rear frame, an equipment cabin left and right beam and an equipment cabin floor. The equipment cabin is a support frame structure formed by sequentially fixing and welding the equipment cabin front frame 11, the equipment cabin left beam 12, the equipment cabin rear frame 13 and the equipment cabin right beam 14, and the equipment cabin front frame 11, the equipment cabin left beam 12, the equipment cabin rear frame 13 and the equipment cabin right beam 14 are fixed and cannot be disassembled. The equipment cabin floor 15 is covered on the support frame structure and is a part that can be quickly disassembled, and is fixed with the equipment cabin front frame 11, the equipment cabin left beam 12, the equipment cabin rear frame 13 and the equipment cabin right beam 14 through bolts.
[0033] As Figures 4-8 shown, the utility model provides a kind of equipment cabin integrated installation structure of eVTOL aircraft, including equipment cabin mounting section 21 and equipment cabin plate assembly 22, equipment cabin mounting section 21 includes equipment cabin support 211, support fastener 212 and tray nut 213, equipment cabin plate assembly 22 includes equipment mounting plate 221 and mounting plate fastener 222;Equipment cabin support 211 side is installed in equipment cabin left and right beam inner side, and equipment cabin support 211 is fixed on equipment cabin left and right beam by support fastener 212, tray nut 213 is arranged on the top of equipment cabin support 211, and the two ends of equipment mounting plate 221 are pressed on the top of equipment cabin support 211, and equipment mounting plate 221 is fixed with equipment cabin support 211 by rotating mounting plate fastener 222 into tray nut 213.
[0034] Preferably, equipment cabin cross beam 223 is glued and installed at the bottom of equipment mounting plate 221, for enhancing the rigidity of equipment mounting plate 221, effectively preventing the vibration and displacement of equipment during flight, and ensuring the normal operation of equipment.
[0035] A plurality of equipment cabin mounting nodes 21 are respectively mounted on the left beam 12 and the right beam 14 of the equipment cabin. The equipment cabin support 211 in the equipment cabin mounting node 21 is integrally formed in an L-shaped structure, and a horizontal arm portion and a vertical arm portion are integrally formed. A supporting plate nut 213 is pre-installed at the bottom of the horizontal arm portion, and the vertical arm portion is fixed to the inner side of the left beam 12 and the right beam 14 of the equipment cabin through a support fastener 212. After the equipment cabin support 211 is mounted on the left and right beams of the equipment cabin, the top of the horizontal arm portion is flush with the top of the equipment cabin cross beam 223. The combination of the equipment cabin support 211 and the support fastener 212 not only ensures the firm installation of the equipment, but also allows quick replacement without damaging the main body structure of the aircraft, which makes the quick maintenance of the aircraft possible.
[0036] The equipment mounting plate 221 in the equipment cabin plate assembly 22 is mounted on the horizontal arm portion of the equipment cabin support 211. The equipment mounting plate 221 is provided with holes at the corresponding positions of the supporting plate nuts 213 of the equipment cabin support 211 on the left and right edges of the equipment mounting plate 221. The mounting plate fastener 222 penetrates the holes on the equipment mounting plate 221 and is connected to the supporting plate nuts 213 below the horizontal arm portion of the equipment cabin support 211. By tightening the mounting plate fastener 222, the equipment mounting plate 221 is fixed to the equipment cabin support 211.
[0037] As shown in Figure 9 The equipment contained in the equipment cabin can be an independent device or any combination of different devices, which are all mounted on the equipment mounting plate 221 and located between the equipment mounting plate 221 and the equipment cabin floor 15. The equipment and the equipment mounting plate 221 form an equipment installation module. The equipment installation module uses a standardized interface, and through modular design and standardized interface, the quick replacement and maintenance of the equipment are realized, and the use efficiency and maintenance convenience of the aircraft are significantly improved.
[0038] Specifically, a plurality of equipment module universal mounting interfaces 224 are arranged on the equipment mounting plate 221. The equipment module universal mounting interface 224 is a standardized electrical equipment interface device, adopts a modular design concept, and allows users to freely combine different interface modules according to needs. This design allows the interface socket to be flexibly combined and expanded according to different needs, and facilitates users to select appropriate interface types and quantities according to actual needs.
[0039] The working principle of the utility model:
[0040] The equipment cabin support 211 is fixed inside the left and right beams of the equipment cabin, and the vertical arm part of the equipment cabin support 211 is fixed with the inside of the left beam 12 and the right beam 14 of the equipment cabin through support fasteners 212. When it is necessary to install equipment on the eVTOL aircraft, the equipment is pre-installed on the equipment mounting plate 221 to form an equipment mounting module, the equipment mounting module is connected to the support plate nut 213 through the mounting plate fastener 222, and the mounting plate fastener is tightened to fix the equipment mounting module with the equipment cabin support 211, and the installation is completed.
[0041] When it is necessary to replace the equipment on the eVTOL aircraft, the mounting plate fastener 222 is loosened, the equipment mounting module is removed, the equipment is removed from the equipment mounting plate 221, and the original equipment mounting module is disassembled; then the replacement equipment is installed on the equipment mounting plate 221 again to form a new equipment mounting module, and then the equipment mounting module is installed on the equipment cabin support 211 to achieve equipment replacement.
[0042] It is obvious to those skilled in the art that the present application is not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or essential characteristics of the present application. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting, and the scope of the present application is defined by the appended claims rather than the above description, and therefore all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present application. Any reference signs in the claims should not be regarded as limiting the claims involved.
[0043] In the description of the present application, unless otherwise specified, the meaning of "a plurality of" is two or more; the orientations or positional relationships indicated by the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail" and the like are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" and the like are only for descriptive purposes and cannot be understood as indicating or implying relative importance.
[0044] In the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "connected", "connected" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.
Claims
1. An eVTOL aircraft equipment bay integrated mounting structure, characterized by, The device cabin mounting section (21) comprises a device cabin support (211), a support fastener (212) and a support nut (213), and the device cabin plate assembly (22) comprises a device mounting plate (221) and a mounting plate fastener (222); the device cabin support (211) is mounted on the inner side of the left and right beams of the device cabin, and is fixed on the left and right beams of the device cabin by the support fastener (212); the support nut (213) is arranged on the top lower surface of the device cabin support (211); the two ends of the device mounting plate (221) are pressed on the top of the device cabin support (211), and the device mounting plate (221) is fixed with the device cabin support (211) by rotating the mounting plate fastener (222) into the support nut (213).
2. The eVTOL aircraft equipment bay integrated mounting structure of claim 1, wherein, The device cabin support (211) in the device cabin mounting section (21) is integrally formed in an "L" shape structure, comprising a horizontal arm portion and a vertical arm portion; the support nut (213) is arranged on the bottom of the horizontal arm portion, and the vertical arm portion is fixed with the inner side of the left and right beams of the device cabin by the support fastener (212).
3. An eVTOL aircraft equipment bay integrated mounting structure as claimed in claim 2, wherein, The device mounting plate (221) is mounted on the horizontal arm portion of the device cabin support (211); the device mounting plate (221) is provided with a hole on the edge thereof corresponding to the position of the support nut (213) of the device cabin support (211); the mounting plate fastener (222) passes through the hole on the device mounting plate (221) and is connected with the support nut (213).
4. The eVTOL aircraft equipment bay integrated mounting structure of claim 1, wherein, The device mounting plate (221) is glued with the device cabin cross beam (223) on the bottom thereof.
5. An eVTOL aircraft equipment bay integrated mounting structure as claimed in claim 4, wherein, The top of the horizontal arm portion of the device cabin support (211) is flush with the top of the device cabin cross beam (223).
6. An eVTOL aircraft equipment bay integrated mounting structure as claimed in claim 1, wherein, A device module universal mounting interface (224) is arranged on the device mounting plate (221).
7. The eVTOL aircraft equipment bay integrated mounting structure of claim 1, wherein, The device cabin is arranged below the device cabin floor in the rear part of the passenger cabin.
8. An eVTOL aircraft equipment bay integrated mounting structure as claimed in claim 7, wherein, The device cabin comprises a device cabin front and rear frame, a device cabin left and right beam and a device cabin floor; the device cabin front and rear frame and the device cabin left and right beam are fixed and welded to form a support frame structure, and the device cabin floor is detachably connected to the support frame structure.