EVTOL aircraft motor arm and wing fusion area structure

Abstract

The utility model discloses an eVTOL aircraft motor arm and wing fusion area structure which comprises a framework, the upper side and the lower side of the framework are connected with an upper skin and a lower skin respectively, the framework comprises wing beams, the number of the wing beams is two, a middle rib is connected between the two wing beams, the outer side faces of the two wing beams are respectively connected with a motor arm bulkhead, and the motor arm bulkhead is connected with the upper skin and the lower skin. The two sides of the motor arm bulkhead located on the front side are connected with front edge ribs, the two sides of the motor arm bulkhead located on the rear side are connected with rear edge ribs, and the front edge ribs and the rear edge ribs are connected with the corresponding wing beams respectively. The structure is good in bearing capacity and high in safety, the framework is provided with structures in the front-back direction, the left-right direction and the up-down direction and can bear loads in the three directions, meanwhile, parts in the three directions are connected into a whole, and the structure is good in bearing capacity, not prone to damage and high in safety.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, and in particular to a fusion zone structure of a motor arm and a wing of an eVTOL aircraft. Background Art

[0002] The area where the eVTOL aircraft and the motor meet, in addition to bearing the load of the wing itself, is also subject to the load transmitted by the motor arm. The forces are complex, and loads such as bending, torsion, shear, and vibration converge in this area. The force transmission is complex, the structure is harshly loaded, and is easily damaged. Utility Model Content

[0003] The purpose of the utility model is to provide a structure of the fusion zone of the motor arm and the wing 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 structure of the fusion zone of the motor arm and the wing of an eVTOL aircraft, comprising a skeleton, wherein the upper and lower sides of the skeleton are respectively connected to the upper skin and the lower skin, the skeleton comprises a wing beam, the wing beam is provided with two, a middle rib is connected between the two wing beams, the outer sides of the two wing beams are respectively connected to motor arm bulkheads, the two sides of the motor arm bulkhead located on the front side are connected to the leading edge ribs, and the two sides of the motor arm bulkhead located on the rear side are connected to the trailing edge ribs, and the leading edge ribs and the trailing edge ribs are respectively connected to the corresponding wing beams.

[0004] Preferably, the interior of the motor arm bulkhead is a hollow structure.

[0005] Preferably, the frame is made of carbon fiber composite material.

[0006] Preferably, the upper skin and the lower skin are both made of carbon fiber composite materials.

[0007] Preferably, the leading edge ribs, trailing edge ribs, motor arm bulkheads and middle ribs are connected to the wing beams by means of structural adhesives or fasteners.

[0008] The technical effects and advantages of the utility model are as follows: the structure has good bearing capacity and high safety: the frame has structures in the front and back, left and right, and up and down, and can bear loads in three directions. At the same time, the parts in the three directions are connected to each other into a whole, with good bearing capacity, not easy to be damaged, and high safety;

[0009] Good maintainability: After the hollow area designed inside the motor arm bulkhead is connected back to back with the wing beam, the upper and lower parts of the wing beam have channels for the power harness to pass through, which facilitates the maintenance of the power harness;

[0010] High skin stability: leading edge ribs, middle ribs and trailing edge ribs are designed at the bending position of the skin to support the skin and prevent the skin from becoming unstable and losing its bearing capacity when under pressure. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 This is an exploded view of the utility model;

[0012] Figure 2 It is an axonometric drawing of the framework of the utility model;

[0013] Figure 3 It is a cross-sectional view of the connection between the wing beam, the motor arm bulkhead, the leading edge rib and the middle rib of the utility model;

[0014] Figure 4 This is an axonometric diagram of the position of the utility model on the eVTOL aircraft.

[0015] Numbers in the figure: 1. Fusion area structure; 11. Upper skin 12. Lower skin; 13. Frame; 131. Leading edge rib; 132. Wing beam; 133. Motor arm bulkhead; 134. Middle rib; 135. Trailing edge rib; 2. eVTOL aircraft. DETAILED DESCRIPTION

[0016] 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.

[0017] Example

[0018] like Figure 4 As shown, the motor arm and the wing are integrated together, which has the advantage of low aerodynamic resistance and helps to improve the range of the eVTOL aircraft 2. Therefore, the motor and the wing are integrated into a design to bear the loads of the motor arm and the wing. The relationship between the two is similar to a cross, and loads in different main force directions converge in this area, resulting in complex forces.

[0019] like Figure 1 As shown, the fusion area structure 1 includes an upper skin 11, a lower skin 12, and a skeleton 13. The upper skin 11 and the lower skin 12 are connected to the upper and lower sides of the skeleton 13 respectively. The upper skin 11 and the lower skin 12 maintain the shape, provide aerodynamic force, and transmit the load transmitted by the motor arm and the wing at the same time. The upper skin 11 and the lower skin 12 are both made of carbon fiber composite materials. The wing area is mainly 0 degrees, and the motor arm area has an additional 90-degree layer to bear the load transmitted by the motor. The thickness of the raised area is greater than the thickness of the two sides. The skeleton 13 provides support for the upper skin 11 and the lower skin 12 to prevent the skin from buckling and improve the stability of the skin. At the same time, the skeleton also transmits most of the load (excluding the load transmitted by the skin).

[0020] As Figure 2 shown, the frame 13 includes a leading edge rib 131, a wing beam 132, a motor arm bulkhead 133, a middle rib 134, and a trailing edge rib 135, all of which are made of carbon fiber composite materials. There are two wing beams 132. A middle rib 134 is connected between the two wing beams 132. Motor arm bulkheads 133 are respectively connected to the outer sides of the two wing beams 132. The leading edge rib 131 is connected to both sides of the motor arm bulkhead 133 at the front side, and the trailing edge rib 135 is connected to both sides of the motor arm bulkhead 133 at the rear side. The leading edge rib 131 and the trailing edge rib 135 are respectively connected to the corresponding wing beam 132. The wing beam 132 is the main load-bearing structure, so it needs to be continuous. Therefore, the ribs are divided into the leading edge rib 131, the middle rib 134, and the trailing edge rib 135, and are arranged at the positions where the skin is bent to prevent the bending from weakening the stability of the skin and to enhance it with ribs. The motor arm bulkhead 133 supports the upper and lower skins in this area and transfers the shear force on the motor arm to the wing beam 132. The upper and lower surfaces of the wing mainly bear tensile and compressive loads. Due to the characteristics of carbon fiber composite materials, bending will weaken the load-bearing capacity. Therefore, in the fusion area, the wing beam remains straight, and the upper and lower surfaces do not bend along with the skin in the motor arm area. The inside of the motor arm bulkhead 133 is a hollow structure. After being connected to the wing beam 132, the empty area is for the power wire harness to pass through, ensuring the passing and maintenance requirements of the wire harness.

[0021] As Figure 3 shown, taking the connection of the leading edge rib 131 as an example in this figure, the connection form of the trailing edge rib 135 is similar. The leading edge rib 131, the motor arm bulkhead 133, and the middle rib 134 are all connected to the wing beam 132. They can be connected by structural adhesive or by fasteners to transfer the load to the wing beam 132. The leading edge rib 131 and the motor arm bulkhead 133 are also connected at the overlapping positions to improve the connection strength and stiffness.

[0022] Finally, it should be noted that the above are only the preferred embodiments of the present invention and are not used to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, for those skilled in the art, they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An eVTOL aircraft motor arm and wing fusion zone structure, including a frame, characterized in that: The upper and lower sides of the skeleton are respectively connected to the upper skin and the lower skin, the skeleton includes a wing beam, two wing beams are provided, a middle rib is connected between the two wing beams, the outer sides of the two wing beams are respectively connected to motor arm bulkheads, the two sides of the motor arm bulkhead located on the front side are connected to leading edge ribs, and the two sides of the motor arm bulkhead located on the rear side are connected to trailing edge ribs, and the leading edge ribs and trailing edge ribs are respectively connected to the corresponding wing beams.

2. The eVTOL aircraft motor arm and wing fusion zone structure according to claim 1, characterized in that: The interior of the motor arm bulkhead is a hollow structure.

3. The eVTOL aircraft motor arm and wing fusion area structure according to claim 1, characterized in that: The frame is made of carbon fiber composite material.

4. The eVTOL aircraft motor arm and wing fusion zone structure according to claim 1, characterized in that: The upper skin and the lower skin are both made of carbon fiber composite materials.

5. The eVTOL aircraft motor arm and wing fusion zone structure according to claim 1, characterized in that: The leading edge rib, the trailing edge rib, the motor arm bulkhead, and the middle rib are connected to the wing beam through structural adhesive or fasteners.

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