EVTOL aircraft lift motor vibration reduction structure

Abstract

The utility model discloses an eVTOL aircraft lift motor vibration reduction structure which comprises a vibration reduction structure, a lift motor is installed on the vibration reduction structure, the vibration reduction structure comprises a lower support, an upper support is arranged above the lower support, the upper support is connected with the lower support through a fastener matched with a vibration reduction block, and the fastener penetrates through the vibration reduction block. The structure is good in vibration reduction effect, the vibration reduction block is installed between the upper support and the lower support, it is guaranteed that no metal hard connection exists between the upper support and the lower support through the rubber machine body, vibration generated on the lifting motor in the X direction, the Y direction and the Z direction is filtered out, the vibration on the lifting motor cannot be transmitted to the lower support and then cannot be transmitted to the machine body structure, and the vibration reduction effect is good. The vibration reduction rate of the vibration reduction block reaches 80% or above.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, and particularly relates to a vibration damping structure for a lift motor of an eVTOL aircraft. Background Art

[0002] During the take-off and landing phases, an eVTOL (electric vertical take-off and landing) aircraft uses lift motors to drive the rotation of propellers, generating an upward pulling force to drive the take-off and landing of the eVTOL aircraft. At the same time, during the conversion phase, an upward pulling force is also required to complete the conversion process from vertical flight to horizontal flight. During the conversion process, there are propeller pulling forces, vibrations, and disturbances of the forward flight airflow on the propellers, etc. The forces are complex and the vibrations are strong. Therefore, it is necessary to ensure the safety of the eVTOL aircraft structure and prevent accidents from occurring to the eVTOL aircraft. The lift motors of the eVTOL aircraft are installed on the motor arms, and generally a relatively strong motor seat structure is designed to withstand the unbalanced bending moments in the front-back and left-right directions during the conversion flight of the lift motors. However, the connection stiffness is large, and the vibrations generated by the lift motors and propellers are directly transmitted to the structure, easily causing cracks in parts in some areas and posing a safety risk. Summary of the Utility Model

[0003] The purpose of the utility model is to provide a vibration damping structure for a lift motor of an eVTOL aircraft to solve the problems mentioned in the background art. To achieve the above purpose, the utility model provides the following technical solution: A vibration damping structure for a lift motor of an eVTOL aircraft, including a vibration damping structure, on which a lift motor is installed. The vibration damping structure includes a lower support, above which there is an upper support. The upper support is connected to the lower support through fasteners in cooperation with vibration damping blocks, and the fasteners pass through the vibration damping blocks.

[0004] Preferably, the lower support is integrally in a ring structure, with a through hole in the middle. There are connecting edges on the front and rear sides of the lower support. There is a lower earpiece in the middle of the lower support, and the lower earpiece is located inside the through hole. There are reinforcing ribs at the bottom of the lower support.

[0005] Preferably, there are upper earpieces at the four corners of the upper support. There is a round hole in the middle of the upper support, and there are motor connection holes around the round hole. There are upper reinforcing ribs at the four corners of the upper support. The motor connection holes are connected to the lift motor through connecting pieces, and the positions of the upper earpieces and the lower earpieces correspond to each other.

[0006] Preferably, the vibration damping blocks include rubber matrices. There are two rubber matrices. A metal pad is installed on the top of the rubber matrix, and an anti-pressure sleeve is installed at the bottom. The two rubber matrices are placed opposite to each other, and a bushing passes through the inside of both. The bushing connects the fasteners.

[0007] Preferably, the anti-pressure sleeve is a T-shaped sleeve.

[0008] Preferably, the fastener includes a bolt, which passes through the upper lug, the bushing and the lower lug and is then connected to a nut. The nut is a self-locking nut, and a gasket is provided between the metal pad and the nut located below.

[0009] The technical effects and advantages of the present utility model are as follows: This structure has good vibration damping effect: The vibration damping block is installed between the upper support and the lower support. By means of the rubber body, it is ensured that there is no hard metal connection between the upper support and the lower support, filtering out the vibrations in the X, Y, and Z directions generated on the lift motor, so that the vibrations on the lift motor will not be transmitted to the lower support, and thus will not be transmitted to the airframe structure. In this example, the vibration damping rate of the vibration damping block reaches more than 80%;

[0010] High safety: Four vibration damping blocks are adopted. When a certain vibration damping block is damaged, the other three can still bear the load. At the same time, there is a clearance space designed between the bushing and the metal pad inside the vibration damping block. When the vibration damping block is subjected to excessive force, the rubber matrix deforms greatly, and the bushing contacts the upper and lower metal pads, forming a hard connection between rigid bodies, still having connection strength. The vibration damping block isolates the vibration on the lift motor from the airframe, reducing the vibration transmitted to the airframe by a large margin and ensuring the safety of the airframe structure;

[0011] Good lateral stiffness: The bushing is supported in the central hole of the rubber matrix to ensure high lateral stiffness and prevent excessive deformation of the rubber body when subjected to lateral force;

[0012] Long service life: The rubber matrix inside the vibration damping block is isolated from the connection surfaces of the fastener, the upper support and the lower support by metal structural parts, preventing wear between the rubber matrix and the fastener, the upper support and the lower support, and ensuring a long service life of the vibration damping block. Description of the Drawings

[0013] Figure 1 Isometric view of the present utility model;

[0014] Figure 2 Isometric view of the vibration damping structure of the present utility model;

[0015] Figure 3 Exploded view of the vibration damping structure of the present utility model;

[0016] Figure 4 Isometric view of the lower support of the present utility model;

[0017] Figure 5 Isometric view of the upper support of the present utility model;

[0018] Figure 6 Cross-sectional view of the connection between the vibration damping pad and the upper and lower supports of the present utility model;

[0019] Figure 7 Isometric view of the present utility model installed on an eVTOL.

[0020] In the figure, 1. Lift motor vibration damping structure; 11. Vibration damping structure; 111. Lower support; 1111. Connection edge; 1112. Lower ear piece; 1113. Lower reinforcing rib; 112. Upper support; 1121. Motor connection hole; 1122. Upper ear piece; 1123. Upper reinforcing rib; 113. Vibration damping block; 1131. Rubber matrix; 1132. Bush; 1133. Anti-pressure sleeve; 1134. Metal pad; 114. Fastener; 1141. Bolt; 1142. Nut; 1143. Gasket; 12. Lift motor; 2. eVTOL aircraft. Detailed implementation manners

[0021] In order to make the implementation means, creative features, achieved purposes and functions of the present utility model easy to understand, the present utility model will be further described below with reference to specific drawings. In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "connection", and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection or a mechanical connection, and it can also be an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and the internal communication of two components can be achieved.

[0022] Embodiment

[0023] As Figure 7 shown, the upper part of the lift motor vibration damping structure 1 is connected to the lift propeller, and the lower part is connected to the eVTOL aircraft 2. According to the overall layout, it is distributed on the motor arm, and there are 8 places in this example.

[0024] As Figure 1 shown, the lift motor vibration damping structure 1 includes the lower vibration damping structure 11 and the upper lift motor 12. The lift motor 12 is installed on the vibration damping structure 11. The lift, torque and vibration generated by the lift motor 12 driving the propeller are all borne by the vibration damping structure 11, ensuring the reliability and safety of the connection.

[0025] As Figure 2 , Figure 3As shown in the figure, the vibration damping structure 11 includes a lower support 111, an upper support 112, a vibration damping block 113 and a fastener 114. The upper support 112 is arranged above the lower support 111. The upper support 112 is connected to the lower support 111 through the fastener 114 in cooperation with the vibration damping block 113, and the fastener 114 passes through the vibration damping block 113. The lower support 111 is connected to the airframe structure of the eVTOL aircraft 2 to meet the requirements of load bearing and force transmission. The lower support 111 can be made of stainless steel, titanium alloy or aluminum alloy. Preferably, 2024 aluminum alloy is used, and the preferred heat treatment state is T351, which meets the requirements of structural stiffness and fatigue characteristics, and at the same time has a certain lightweight effect. The upper support 112 is connected to the lift motor 12. In the case of severe vibration, it is designed with a relatively thick thickness and a large stiffness to meet the requirements of deformation and strength. The upper support 112 can be made of stainless steel, titanium alloy or aluminum alloy. Preferably, TC4 titanium alloy is used. The vibration damping block 113 has a vibration damping function. The vibration transmitted from the lift motor 12 to the upper support 112 is reduced by the vibration damping block 113 and then transmitted to the lower support. In this example, the vibration damping effect reaches more than 80%. The fastener 114 connects the vibration damping block 113, the upper support 112 and the lower support 111 together, enabling them to perform their respective functions and meet the functions of force transmission, vibration attenuation, etc.

[0026] As Figure 4 shown, the lower support 111 is integrally in a ring structure, with a through hole in the middle. Connecting edges 1111 are provided on the front and rear sides of the lower support 111. A lower lug 1112 is provided in the middle of the lower support 111. The lower lug 1112 is located inside the through hole. A lower reinforcing rib 1113 is provided at the bottom of the lower support 111. In this example, the connecting edge 1111 is connected to the structure adjacent to the eVTOL aircraft 2 to transmit the force on the lower support 111 to the eVTOL aircraft 2. The lower lug 1112 is connected to the vibration damping block 113 and is stuck in the middle of the vibration damping block 113. The lower lug 1112 meets the connection requirements with a relatively large base size of the vibration damping block 113, and the connection holes on the lower lug 1112 are relatively large. The lower reinforcing rib 1113 improves the connection strength and stiffness and minimizes the deformation of the lower support 111 caused by the force.

[0027] As Figure 5As shown in the figure, upper lugs 1122 are provided at the four corners of the upper support 112. A round hole is opened in the middle of the upper support 112, and motor connection holes 1121 are provided around the round hole. Upper reinforcing ribs 1123 are provided at the four corners of the upper support 112. The motor connection holes 1123 are connected to the lift motor 12 through connectors. The lift motor 12 has relatively large vibrations and requires relatively high structural stiffness. Therefore, the thickness of the parts in the area where the upper support 112 is connected to the lift motor 12 is relatively thick, which is 20 mm in this example. The positions of the upper lugs 1122 and the lower lugs 1112 correspond to each other. The holes of the upper lugs 1122 are directly connected to the fasteners 114, and the hole diameters are relatively small, just meeting the connection strength requirements. The upper reinforcing ribs 1123 improve the connection strength and stiffness, and minimize the deformation of the upper support 112 caused by the force.

[0028] As Figure 6 shown, the vibration damping block 113 includes a rubber matrix 1131, a bushing 1132, an anti-pressure sleeve 1133, and a metal pad 1134. There are two rubber matrices 1131, which are divided into upper and lower blocks, and a design gap is left between the upper and lower blocks to facilitate the installation with the lower support 1111. The hole diameter on the lower lugs of the lower support 111 is smaller than the outer diameter of the upper and lower blocks of the rubber matrix, and they need to be separated for installation. A metal pad 1134 is installed on the top of the rubber matrix 1131, and an anti-pressure sleeve 1133 is installed on the bottom. The two rubber matrices 1131 are placed opposite to each other, and the bushing 1132 passes through both of them. The rubber matrix 1131 is the main vibration filtering part. Through its characteristic of relatively small stiffness and deformation when stressed, it absorbs vibrations. The bushing 1132 is a stainless steel part and is vulcanized together with the upper half of the rubber matrix 1131 to form an integral shape. The inside of the bushing 1132 is matched with the bolt 1141 of the fastener 114. The anti-pressure sleeve 1133 is a T-shaped sleeve and is vulcanized together with the positions where the upper and lower parts of the rubber matrix 1131 are connected to the lower support 111, isolating the direct contact between the rubber matrix 1131 and the lower support 111 and protecting the rubber matrix 1131 from being worn. The metal pad 1134 is vulcanized together with the rubber matrix 1131. When the bolt 1141 and the nut 1142 of the fastener 114 are installed, a certain tightening torque is required according to the requirements, which will generate a relatively large pre-tightening force along the axial direction of the bolt 1141. If directly connected to the rubber matrix 1131, it will crush the rubber matrix 1131. The metal pad 1134 is used to disperse the surrounding stress to ensure the connection of the fastener 114. A gasket 1143 is placed between the lower metal pad 1134 and the nut 1142 to prevent damage to the lower metal pad 1134 when the nut 1142 is turned. At the same time, the gasket 1143 needs to meet relatively high stiffness requirements to disperse the pre-tightening force on the nut 1142. To ensure the connection strength, the strength grade of the bolt 1141 is not less than 10.9. At the same time, the vibration here is relatively large, and the nut 112 is a self-locking nut to prevent loosening. Figure 6It can be seen that only the lower part of the rubber matrix 1131 is in contact with the bushing 1132. Therefore, when a force exceeding the designed magnitude is applied, if the lower part of the rubber matrix 1131 deforms significantly, the lower metal pad 1134 can be brought into contact with the bushing 1132, resulting in a rigid connection. This ensures the safety of the structural connection, but the vibration damping effect is lost at this time. Under normal circumstances, the upper support 112 and the lower support 111 are isolated by the rubber matrix 1131 without a rigid connection to ensure the vibration isolation function.

[0029] Finally, it should be noted that the above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described 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 within the protection scope of the present invention.

Claims

1. A vibration damping structure for a lift motor of an eVTOL aircraft, including a vibration damping structure, characterized in that: A lift motor is installed on the vibration damping structure. The vibration damping structure includes a lower support. An upper support is provided above the lower support. The upper support is connected to the lower support through fasteners in cooperation with vibration damping blocks, and the fasteners pass through the vibration damping blocks.

2. The vibration damping structure of the lift motor of an eVTOL aircraft according to claim 1, characterized in that: The lower support is integrally in a ring structure, with a through hole in the middle. Connection edges are provided on the front and rear sides of the lower support. Lower lugs are provided in the middle of the lower support. The lower lugs are located inside the through hole. Reinforcing ribs are provided at the bottom of the lower support.

3. The vibration damping structure of the lift motor of an eVTOL aircraft according to claim 2, wherein: Upper lugs are provided at the four corners of the upper support. A round hole is opened in the middle of the upper support. Motor connection holes are provided around the round hole. Upper reinforcing ribs are provided at the four corners of the upper support. The motor connection holes are connected to the lift motor through connectors. The positions of the upper lugs and the lower lugs correspond to each other.

4. The vibration damping structure of the lift motor of an eVTOL aircraft according to claim 1, characterized in that: The vibration damping blocks include rubber matrices. There are two rubber matrices. Metal pads are installed on the tops of the rubber matrices, and pressure-proof sleeves are installed on the bottoms. The two rubber matrices are placed opposite to each other, and bushings pass through their interiors. The bushings are connected to the fasteners.

5. The vibration damping structure of the lift motor of an eVTOL aircraft according to claim 4, characterized in that: The pressure-proof sleeve is a T-shaped sleeve.

6. The vibration damping structure of the lift motor of an eVTOL aircraft according to claim 4, wherein: The fasteners include bolts. The bolts pass through the upper lugs, bushings and lower lugs and then are connected to nuts. The nuts are self-locking nuts. Washers are provided between the metal pads located below and the nuts.

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