EVTOL aircraft electronic speed controller vibration reduction structure

Abstract

The utility model discloses an eVTOL aircraft electronic speed controller vibration reduction structure which comprises an electronic speed controller, four corners of the bottom of the electronic speed controller are installed on electronic speed controller installation positions on a motor arm through vibration reduction blocks, a motor installation position is arranged on one side of each electronic speed controller installation position, a motor is installed on each motor installation position, and the output end of each motor is connected with a propeller. The vibration reduction block is installed at the bottom of the electronic speed controller, a truss structure is not adopted at the bottom of the motor, and space is saved.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, and in particular to an eVTOL aircraft electrically adjustable vibration reduction structure. Background Art

[0002] The eVTOL (Electric Vertical Takeoff and Landing) electric vertical takeoff and landing aircraft uses a motor to drive the propeller to provide lift to complete the takeoff and landing of the eVTOL aircraft. When the propeller rotates, the air is disturbed, which will produce large vibrations, have a great impact on the electrical equipment on the aircraft, and even damage the recording equipment, causing great losses.

[0003] The electronic speed controller adjusts the speed of the motor according to the control signal to achieve controllable speed of the motor. It is generally arranged at a very close distance to the motor. According to the principle of vibration, the closer the distance to the vibration source, the greater the vibration and the easier it is to be damaged. Existing electric aircraft use trusses and buffer structures for vibration filtering design. For example, the structure published in Chinese utility model patent 202120766534.0 prevents the vibration of the engine and propeller from being transmitted to the fuselage structure, preventing vibration damage to onboard equipment. However, its truss system requires a large installation space and cannot be applied to the lift system of eVTOL aircraft. Utility Model Content

[0004] The purpose of the utility model is to provide an electric adjustment vibration reduction structure for 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: an eVTOL aircraft electric adjustment vibration reduction structure, including an electric adjustment, wherein the four corners of the bottom of the electric adjustment are installed on the electric adjustment installation position on the motor arm through vibration reduction blocks, a motor installation position is provided on one side of the electric adjustment installation position, a motor is installed on the motor installation position, and the output end of the motor is connected to a propeller.

[0005] Preferably, the vibration damping block includes a connector and a vibration damping block body. Two connectors are provided, which are respectively installed at the upper and lower ends of the vibration damping block body. The ends of the connectors are provided with threads. The upper and lower connectors are respectively connected to the electric regulator and the motor arm through nuts.

[0006] Preferably, the connecting head comprises a stud and a plate, the bottom of the stud is connected to the plate, the plate is connected to the vibration damping block body, the stud is threadedly connected to a nut, and the connecting head is a steel or aluminum metal part.

[0007] Preferably, the vibration damping block body is made of rubber material.

[0008] Preferably, the nut is a self-locking nut.

[0009] The technical effects and advantages of the utility model are as follows: the structure occupies little space: a vibration reduction block is installed at the bottom of the electric regulator, avoiding the use of a truss structure at the bottom of the motor, thus saving space;

[0010] Light weight: The load of the motor is large, usually several hundred kilograms. If the motor is to be vibrated, a very large vibration damping block is needed to improve its bearing capacity. The vibration damping block at the bottom of the ESC only needs to bear the weight of the ESC, which is only a few kilograms, and is relatively light.

[0011] Large vibration isolation range: By changing the material properties, height and diameter of the vibration damping block, vibration isolation of different frequencies can be achieved and different vibration conditions of different models can be adapted. The vibration isolation range is large and the application is wide.

[0012] Low cost: The upper and lower parts of the vibration damping block are metal heads with threads, which are vulcanized together with the vibration damping block body made of rubber in the middle, which is simple to process and low in cost;

[0013] Easy installation: The installation of the vibration damping block only requires nuts, which is easy to install. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is an axonometric drawing of the utility model;

[0015] Figure 2 It is an exploded view of the utility model;

[0016] Figure 3 It is a partial view of the installation of the electric regulator and the motor arm of the utility model;

[0017] Figure 4 It is an exploded view of the vibration damping block of the utility model;

[0018] Figure 5 This is a cross-sectional view of the installation of the electric regulator and the motor arm of the utility model.

[0019] In the figure, 1. ESC; 2. Vibration damping block; 21. Connector; 22. Vibration damping block body; 3. Propeller; 4. Motor; 5. Motor arm; 6. Nut; 7. ESC mounting position; 8. Motor mounting position. DETAILED DESCRIPTION

[0020] 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.

[0021] Example

[0022] like Figure 1 , Figure 2 and Figure 3 As shown, an eVTOL aircraft electric speed controller vibration reduction structure includes an electric speed controller 1, a vibration reduction block 2, a propeller 3, a motor 4, a motor arm 5 and a nut 6. The motor arm 5 is a structural component of the eVTOL aircraft, and provides an electric speed controller mounting position 7 and a motor mounting position 8 for the electric speed controller 1 and the motor 4 to withstand the tension generated by the propeller 3.

[0023] The motor 4 is installed on the motor mounting position 8, and the propeller 3 is installed at the output end of the motor 4. The motor 4 drives the propeller 3 to rotate, driving the surrounding air to wash downward, thereby generating an upward pulling force. The surrounding air is periodically disturbed by the propeller 3, causing the propeller 3 to generate periodic vibrations, which are transmitted to the motor arm 5 through the motor 4.

[0024] Motor 4 drives propeller 3 to rotate. Motor 4 is controlled by ESC 1. The speed and change rule of motor 4 are realized according to the signal of ESC 1. ESC 1 receives the flight control computer signal of eVTOL aircraft and controls motor 4 to realize the power control requirements of the entire eVTOL aircraft. Connection structures are designed at the four corners of the bottom of ESC 1, which are connected to vibration damping block 2.

[0025] The vibration-damping block 2 is connected between the motor arm 5 and the electric speed controller 1 to prevent the vibration of the propeller 3 from being transmitted to the motor arm 5 and then further transmitted to the electric speed controller 1, thereby avoiding damage to the electric speed controller 1. The vibration-damping block 2 has the function of vibration isolation and vibration filtering. The upper and lower parts of the vibration-damping block 2 are connected to the electric speed controller 1 and the motor arm 5 respectively with nuts 6.

[0026] like Figure 4 As shown, the vibration damping block 2 includes a connector 21 and a vibration damping block body 22. Two connectors 21 are provided, which are installed at the upper and lower ends of the vibration damping block body 22. The vibration damping block body 22 is in the middle, and the electric regulator 1 connected to the upper connector 21 and the motor arm 5 connected to the lower connector 21 are separated by the vibration damping block body 22. The connector 21 includes a stud and a plate. The stud is designed with threads for easy connection with the nut 6. The connector 21 can be made of metal materials such as steel and aluminum, preferably stainless steel. The stud with a threaded structure and the bottom plate can be machined by a lathe, or the stud and the plate can be welded after machining. The stud and the plate are welded in this example. The vibration damping block body 22 is made of a soft material, preferably a rubber material, and is vulcanized together with the connector 21 to form an integral vibration damping block structure. According to the performance of the rubber, the diameter and height of the vibration damping block body 22 can be changed to achieve vibration isolation and vibration filtering of vibrations of different frequencies.

[0027] like Figure 5As shown, the upper connector 21 of the vibration damping block 2 is connected to the electric regulator 1, and the lower connector 21 is connected to the motor arm through the nut 6. The nut 6 is a self-locking nut to prevent the nut 6 from loosening due to vibration after connection, thereby causing the equipment to fall off and fail.

[0028] 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. An eVTOL aircraft electric adjustment vibration reduction structure, including electric adjustment, characterized in that: The four corners of the bottom of the electric speed controller are installed on the electric speed controller mounting position on the motor arm through vibration-damping blocks. A motor mounting position is provided on one side of the electric speed controller mounting position. A motor is installed on the motor mounting position. The output end of the motor is connected to the propeller. The vibration-damping block includes a connector and a vibration-damping block body. Two connectors are provided, which are respectively installed at the upper and lower ends of the vibration-damping block body. Threads are provided on the ends of the connectors. The upper and lower connectors are respectively connected to the electric speed controller and the motor arm through nuts.

2. The eVTOL aircraft electrically adjustable vibration reduction structure according to claim 1, characterized in that: The connecting head comprises a stud and a plate, the bottom of the stud is connected to the plate, the plate is connected to the vibration damping block body, the stud is threadedly connected to a nut, and the connecting head is a steel or aluminum metal part.

3. The eVTOL aircraft electrically adjustable vibration reduction structure according to claim 1, characterized in that: The vibration damping block body is made of rubber material.

4. The eVTOL aircraft electrically adjustable vibration reduction structure according to claim 1, characterized in that: The nut is a self-locking nut.

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