Light cabin door interior panel of eVTOL aircraft

Abstract

The utility model discloses a light cabin door interior panel of an eVTOL aircraft. The panel comprises an inner decorative plate, a storage box cover plate detachably covering the outer side face of the inner decorative plate, an outer decorative plate detachably connected with the storage box cover plate or the inner decorative plate and covering the outer side face of the storage box cover plate, a handrail detachably installed on the inner side face of the inner decorative plate and a handrail cover detachably installed on the outer side face of the handrail. The storage box comprises a storage box cover plate and an inner decorative plate, the elbow support decorative plate is detachably installed on the inner side face of the inner decorative plate, the upper decorative cover is detachably installed on the top of the inner side face of the inner decorative plate, a storage box is arranged at the bottom of the storage box cover plate, a through hole capable of being communicated with the storage box is formed in the inner decorative plate, and a plurality of first honeycomb-shaped lightening holes are formed in the outer side face of the inner decorative plate.

Description

Technical Field

[0001] The utility model relates to the field of eVTOL aircraft, and more specifically, to a lightweight cabin door interior decoration panel of an eVTOL aircraft. Background Art

[0002] eVTOL has special requirements for the overall weight of the fuselage. If the weight of the fuselage increases, then the weight of the batteries, motors, structures and other components needs to increase to maintain the same payload and performance. In fact, every pound of weight increase will increase the weight of the final product by three pounds.

[0003] Typical eVTOL hatch interior panel assemblies are made of carbon fiber composite materials or traditional injection molding processes. However, the application of carbon fiber composite materials and injection molding processes are limited by factors such as complex shapes, high mold costs, many connectors, and long manufacturing cycles, resulting in long R&D cycles and high R&D costs. Utility Model Content

[0004] In view of the above-mentioned defects of the prior art, the utility model provides a lightweight cabin door interior panel for an eVTOL aircraft.

[0005] The technical solution adopted by the utility model to solve its technical problems is: constructing a lightweight cabin door interior panel of an eVTOL aircraft, the panel comprising an interior panel, a storage box cover detachably covered on the outer side of the interior panel, an exterior panel detachably connected to the storage box cover or the interior panel and covered on the outer side of the storage box cover, an armrest detachably mounted on the inner side of the interior panel, an armrest cover detachably mounted on the outer side of the armrest, an elbow support panel detachably mounted on the inner side of the interior panel, and an upper decorative cover detachably mounted on the top of the inner side of the interior panel, the storage box cover is provided with a storage box at the bottom, the interior panel is provided with a through hole that can be connected to the storage box, and the outer side of the interior panel is provided with a plurality of first honeycomb-shaped weight-reducing holes.

[0006] In the lightweight door interior panel of the eVTOL aircraft described in the utility model, a plurality of second honeycomb weight-reducing holes are provided on the outer side surface of the storage box cover, a plurality of third honeycomb weight-reducing holes are provided on the outer side surface of the exterior trim, a plurality of fourth honeycomb weight-reducing holes are provided on the inner side surface of the elbow support trim, and a plurality of fifth honeycomb weight-reducing holes are provided on the inner side surface of the upper trim.

[0007] In the lightweight door interior panel of the eVTOL aircraft described in the utility model, the interior panel, storage box cover, exterior panel, armrest, armrest cover, elbow support panel and upper cover are all made of nylon material by 3D printing.

[0008] In the lightweight door interior panel of the eVTOL aircraft described in the utility model, a plurality of first buckle holes are provided on the inner side edge of the storage box cover, and a plurality of first pins and / or first buckles that can be inserted into and connected to the first buckle holes are provided at positions corresponding to the plurality of first buckle holes on the outer side of the interior panel.

[0009] In the lightweight cabin door interior panel of the eVTOL aircraft described in the utility model, a plurality of second buckle holes are provided at the edge of the exterior panel, and a plurality of second pins and / or second buckles that can be inserted into and connected to the second buckle holes are provided at positions corresponding to the plurality of second buckle holes on the outer side of the storage box cover.

[0010] In the lightweight door interior panel of the eVTOL aircraft described in the utility model, a first connecting portion is provided on the interior panel on the first side of the through hole, a second connecting portion is provided on the interior panel on the second side of the through hole, the first end of the armrest is connected to the first connecting portion, and the second end of the armrest is connected to the second connecting portion.

[0011] In the lightweight door interior panel of the eVTOL aircraft described in the utility model, the first connecting portion is provided with a first connecting hole penetrating the first connection, the first end of the armrest is provided with a first threaded hole at a position corresponding to the first connecting hole, the second end of the armrest is fixed with a third pin, and the second connecting portion is provided with a third buckle hole for the third pin to be inserted and connected.

[0012] In the lightweight door interior panel of the eVTOL aircraft described in the utility model, a plurality of fourth buckle holes are provided on the outer side surface of the armrest, and a plurality of fourth pins and / or fourth buckles that can be inserted into and connected with the fourth buckle holes are provided on the inner side surface of the armrest cover at positions corresponding to the plurality of fourth buckle holes.

[0013] In the lightweight door interior panel of the eVTOL aircraft described in the utility model, a plurality of fifth buckle holes are provided on the inner side surface of the interior panel, and a plurality of fifth pins and / or fifth buckles that can be inserted into and connected to the fifth buckle holes are provided at positions corresponding to the plurality of fifth buckle holes on the connecting surface of the elbow support trim.

[0014] In the lightweight door interior panel of the eVTOL aircraft described in the utility model, a plurality of sixth buckle holes are provided on the inner side surface of the interior panel, and a plurality of sixth pins and / or sixth buckles that can be inserted into and connected to the sixth buckle holes are provided at positions corresponding to the plurality of sixth buckle holes on the connecting surface of the upper decorative cover.

[0015] The implementation of the lightweight cabin door interior panel of the eVTOL aircraft of the utility model has the following beneficial effects: when using the lightweight cabin door interior panel of the eVTOL aircraft of the utility model, by setting the first honeycomb-shaped weight-reducing hole on the interior panel, the weight of the interior panel can be reduced as much as possible without reducing the strength of the interior panel. During assembly, the storage box cover is first connected to the exterior panel, and then the storage box cover and the exterior panel are installed on the outer side of the interior panel. After that, the armrest, elbow support panel, and upper cover are installed on the inner side of the interior panel in sequence, and finally the armrest cover is covered on the armrest to complete the assembly of the cabin door interior panel. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments, in which:

[0017] Figure 1 This is a first exploded structural diagram of a lightweight door interior panel of an eVTOL aircraft of the utility model;

[0018] Figure 2 This is a second exploded structural diagram of the lightweight door interior panel of the eVTOL aircraft of the utility model;

[0019] Figure 3 This is a schematic diagram of the outer side structure of the lightweight door interior panel of the eVTOL aircraft of the utility model;

[0020] Figure 4 It is a schematic diagram of the inner side structure of the lightweight cabin door interior panel of the eVTOL aircraft of the present invention. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solution and advantages of the present invention more clear, the implementation mode of the present invention will be further described in detail below with reference to the accompanying drawings.

[0022] like Figure 1-4 As shown, in the first embodiment of the lightweight cabin door interior panel of the eVTOL aircraft of the utility model, the panel 10 includes an interior panel 11, a storage box cover 12 detachably covered on the outer side of the interior panel 11, an outer decorative panel 13 detachably connected to the storage box cover 12 or the interior panel 11 and covered on the outer side of the storage box cover 12, an armrest 14 detachably mounted on the inner side of the interior panel 11, an armrest cover 15 detachably mounted on the outer side of the armrest 14, an elbow support decorative panel 16 detachably mounted on the inner side of the interior panel 11, and an upper decorative cover 17 detachably mounted on the top of the inner side of the interior panel 11, a storage box 18 is provided at the bottom of the storage box cover 12, a through hole 19 which can be connected to the storage box 18 is provided on the interior panel 11, and a plurality of first honeycomb weight reduction holes 20 are provided on the outer side of the interior panel 11.

[0023] Preferably, a plurality of second honeycomb weight-reducing holes 21 are provided on the outer side surface of the storage box cover 12, a plurality of third honeycomb weight-reducing holes 22 are provided on the outer side surface of the exterior trim 13, a plurality of fourth honeycomb weight-reducing holes 23 are provided on the inner side surface of the elbow support trim 16, and a plurality of fifth honeycomb weight-reducing holes 24 are provided on the inner side surface of the upper trim cover 17.

[0024] When using the lightweight cabin door interior panel of the eVTOL aircraft of the utility model, by setting the first honeycomb-shaped weight-reducing hole 20 on the interior panel 11, the weight of the interior panel 11 can be reduced as much as possible without reducing the strength of the interior panel 11. During assembly, the storage box cover 12 is first connected to the exterior panel 13, and then the storage box cover 12 and the exterior panel 13 are installed on the outer side of the interior panel 11. After that, the armrest 14, the elbow support panel 16, and the upper cover 17 are installed on the inner side of the interior panel 11 in sequence, and finally the armrest cover 15 is covered on the armrest 14, and the assembly of the cabin door interior panel 10 can be completed.

[0025] Preferably, the interior trim panel 11, the storage box cover 12, the exterior trim panel 13, the armrest 14, the armrest cover 15, the elbow support trim panel 16 and the upper trim cover 17 are all made of nylon material by 3D printing.

[0026] The door interior panels 10 of the present application are all manufactured using nylon material 3D printing advanced technology, without the need to develop and use molds, which greatly shortens the R&D and manufacturing cycle and reduces costs.

[0027] At the same time, the lightweight door interior panel 10 component of the present application adopts a honeycomb-shaped weight-reducing design on the outer side surface (a honeycomb-shaped array groove structure is designed on the outer side surface). The honeycomb size, depth (thickness of the interior panel 11), and density are all calculated. While ensuring that the structural strength requirements are met, the weight itself is extremely light. And through the installation of the latch buckle and the connection structure design, the connectors are reduced, further reducing the weight (details will be described later). The overall weight of the door interior panel 10 assembly is as light as 2,636g, thereby reducing the overall weight of the eVTOL, improving the cruising range, and increasing the payload.

[0028] At the same time, the lightweight interior panel 10 assembly is also designed with storage space for passengers to store small items. The elbow support panel 16 and the armrest 14 are designed to make passengers more comfortable.

[0029] like Figure 1 , 2 As shown, the inner side edge of the storage box cover 12 is provided with a plurality of first buckle holes 25, and the outer side of the interior trim panel 11 is provided with a plurality of first pins 26 and / or first buckles that can be inserted into and connected to the first buckle holes 25 at positions corresponding to the plurality of first buckle holes 25.

[0030] Similarly, a plurality of second buckle holes 27 are provided at the edge of the exterior panel 13, and a plurality of second latches 28 and / or second buckles that can be inserted into and connected to the second buckle holes 27 are provided at positions corresponding to the plurality of second buckle holes 27 on the outer surface of the storage box cover 12.

[0031] like Figure 2 As shown, the interior panel 11 is provided with a first connection portion 29 on the first side of the through hole 19, the interior panel 11 is provided with a second connection portion 30 on the second side of the through hole 19, the first end of the armrest 14 is connected to the first connection portion 29, and the second end of the armrest 14 is connected to the second connection portion 30. Specifically, the first connection portion 29 is provided with a first connection hole 31 penetrating the first connection, the first end of the armrest 14 and the first connection hole 31 are provided with a first threaded hole 33 at corresponding positions, the second end of the armrest 14 is fixed with a third latch 34, and the second connection portion 30 is provided with a third buckle hole 35 for the third latch 34 to be inserted and connected.

[0032] like Figure 1 , 2 As shown, the outer side surface of the armrest 14 is provided with a plurality of fourth buckle holes 37, and the inner side surface of the armrest cover 15 is provided with a plurality of fourth pins 36 and / or fourth buckles that can be inserted into and connected with the fourth buckle holes 37 at positions corresponding to the plurality of fourth buckle holes 37.

[0033] Similarly, a plurality of fifth buckle holes 39 are provided on the inner side surface of the interior trim panel 11, and a plurality of fifth pins 38 and / or fifth buckles that can be inserted into and connected to the fifth buckle holes 39 are provided at positions corresponding to the plurality of fifth buckle holes 39 on the connecting surface of the elbow support trim panel 16.

[0034] Similarly, a plurality of sixth button holes 41 are provided on the inner side surface of the interior trim panel 11, and a plurality of sixth pins 40 and / or sixth buckles that can be inserted into and connected to the sixth button holes 41 are provided at positions corresponding to the plurality of sixth button holes 41 on the connecting surface of the upper decorative cover 17.

[0035] In the present application, the number of connectors is reduced and the weight of the hatch is further reduced through the installation of the latch and buckle and the design of the connection structure.

[0036] In addition, in the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", "stacked" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected, or indirectly connected through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0037] The above description is only an embodiment of the present invention, and does not limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made by using the contents of the specification and drawings of the present invention, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A lightweight door interior panel for an eVTOL aircraft, characterized in that: The panel includes an interior panel, a storage box cover detachably mounted on the outer side of the interior panel, an exterior panel detachably connected to the storage box cover or the interior panel and covering the outer side of the storage box cover, an armrest detachably mounted on the inner side of the interior panel, an armrest cover detachably mounted on the outer side of the armrest, an elbow support panel detachably mounted on the inner side of the interior panel, and an upper decorative cover detachably mounted on the top of the inner side of the interior panel, a storage box is provided at the bottom of the storage box cover, a through hole communicated with the storage box is provided on the interior panel, and a plurality of first honeycomb weight-reducing holes are provided on the outer side of the interior panel.

2. The lightweight door interior panel for an eVTOL aircraft according to claim 1, characterized in that: The outer side surface of the storage box cover is provided with a plurality of second honeycomb weight-reducing holes, the outer side surface of the exterior trim is provided with a plurality of third honeycomb weight-reducing holes, the inner side surface of the elbow support trim is provided with a plurality of fourth honeycomb weight-reducing holes, and the inner side surface of the upper trim cover is provided with a plurality of fifth honeycomb weight-reducing holes.

3. The lightweight door interior panel for an eVTOL aircraft according to claim 2, characterized in that: The interior trim panel, storage box cover panel, exterior trim panel, armrest, armrest cover, elbow support trim panel and upper trim cover are all made of nylon material by 3D printing.

4. The lightweight door interior panel for an eVTOL aircraft according to claim 1, characterized in that: The inner side edge of the storage box cover is provided with a plurality of first buckle holes, and the outer side of the interior trim panel is provided with a plurality of first pins and / or first buckles that can be inserted into and connected with the first buckle holes at positions corresponding to the plurality of first buckle holes.

5. The lightweight door interior panel for an eVTOL aircraft according to claim 4, characterized in that: The edge of the exterior panel is provided with a plurality of second buckle holes, and the outer side surface of the storage box cover is provided with a plurality of second pins and / or second buckles which can be inserted into and connected with the second buckle holes at positions corresponding to the plurality of second buckle holes.

6. The lightweight door interior panel for an eVTOL aircraft according to claim 1, characterized in that: A first connection portion is provided on the interior panel at a first side of the through hole, a second connection portion is provided on the interior panel at a second side of the through hole, a first end of the armrest is connected to the first connection portion, and a second end of the armrest is connected to the second connection portion.

7. The lightweight door interior panel for an eVTOL aircraft according to claim 6, characterized in that: The first connecting portion is provided with a first connecting hole penetrating the first connection, the first end of the armrest and a first threaded hole are provided at a position corresponding to the first connecting hole, the second end of the armrest is fixed with a third pin, and the second connecting portion is provided with a third buckle hole for the third pin to be inserted into and connected.

8. The eVTOL aircraft lightweight door interior panel according to claim 7, characterized in that: The outer side surface of the armrest is provided with a plurality of fourth buckle holes, and the inner side surface of the armrest cover is provided with a plurality of fourth pins and / or fourth buckles which can be inserted into and connected with the fourth buckle holes at positions corresponding to the plurality of fourth buckle holes.

9. The eVTOL aircraft lightweight door interior panel according to claim 1, characterized in that: A plurality of fifth buckle holes are provided on the inner side surface of the interior trim panel, and a plurality of fifth pins and / or fifth buckles which can be inserted into and connected with the fifth buckle holes are provided at positions corresponding to the plurality of fifth buckle holes on the connecting surface of the elbow support trim panel.

10. The eVTOL aircraft lightweight door interior panel according to claim 1, characterized in that: A plurality of sixth button holes are provided on the inner side surface of the interior trim panel, and a plurality of sixth pins and / or sixth buckles that can be inserted into and connected to the sixth button holes are provided at positions corresponding to the plurality of sixth button holes on the connecting surface of the upper decorative cover.

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