EVTOL aircraft power system damping device

Abstract

The invention provides an eVTOL aircraft power system damping device and relates to the technical field of damping, the damping device is mainly composed of a damping assembly and a damping base, the damping base is of an annular structure and is made of a metal material, a connecting column can achieve installation and fixation of the damping assembly and the damping base, and the damping assembly and the damping base are connected through a connecting rod. The vibration reduction base is provided with installation point positions, the number of the installation point positions is the same as that of the vibration reduction assemblies, the vibration reduction assemblies are formed by vulcanizing rubber materials and metal materials and comprise first vibration reduction pieces and second vibration reduction pieces, and sleeve structures are arranged between the connection columns and the first vibration reduction pieces and between the connection columns and the second vibration reduction pieces. And the vibration reduction base and the vibration reduction assembly form a rubber-metal composite structure, so that multidirectional vibration control, broadband vibration reduction and light weight can be realized, powerful technical support is provided for application of the eVTOL aircraft in low-altitude economy, and innovation of an urban air travel mode and sustainable development of the low-altitude economy are promoted.

Description

Technical Field

[0001] The present invention relates to the technical field of mechanical vibration damping, and more particularly to a vibration damping device for the power system of an eVTOL aircraft. Background Art

[0002] With the rapid development of the low-altitude economy, urban air travel has gradually become an important part of future transportation. An eVTOL (Electric Vertical Take-off and Landing) aircraft is an aircraft that realizes vertical take-off and landing (VTOL) through electric drive. It does not require a runway or a dedicated take-off and landing site and can be widely used in urban air traffic (UAM), logistics distribution, emergency rescue and other fields. As a key means of transportation in the low-altitude economy, the application scenarios of eVTOL aircraft include urban short-distance transportation, emergency rescue, logistics distribution, etc., and it has the advantages of high efficiency, flexibility, environmental protection, etc.

[0003] However, eVTOL aircraft need to take off and land frequently and fly at low speeds in complex urban environments, which puts higher requirements on the vibration control of the power system. The vibration of the power system not only affects the stability and safety of the aircraft, but also reduces the comfort of passengers and even shortens the service life of key components.

[0004] During the flight test phase of eVTOL aircraft, the overall vibration problem is serious, which poses a serious threat to the aircraft structure and a series of subsystems (avionics, flight control, optoelectronics). Especially between the wing and the motor mount, due to excessive vibration, cracks appear in many places on the wing arm structural parts, and it is urgent to introduce a vibration damping device to solve the current problem. Summary of the Invention

[0005] In view of this, the purpose of the present invention is to provide a vibration damping device for the power system of an eVTOL aircraft to solve the technical problem that the existing eVTOL aircraft has serious vibration problems and poses a serious threat to the aircraft structure and a series of subsystems (avionics, flight control, optoelectronics).

[0006] To achieve the above object, the present invention provides a vibration damping device for an eVTOL aircraft power system, which includes a plurality of vibration damping components and a vibration damping base for supporting and fixing the vibration damping components, and further includes a connecting column for connecting and fixing the vibration damping components and the vibration damping base. The vibration damping base is in a ring structure, made of a metal material, for connecting and fixing with a load, and the vibration damping base is provided with installation points adapted to the vibration damping components. The vibration damping components are vulcanized from a rubber material and a metal material, and include a first vibration damping member and a second vibration damping member. The first vibration damping member and the second vibration damping member are arranged on both sides of the vibration damping base, and the connecting column sequentially passes through the first vibration damping member, the vibration damping base and the second vibration damping member. A sleeve structure is provided between the connecting column and the first vibration damping member and the second vibration damping member.

[0007] Optionally, a first mounting hole is provided on the first vibration damping member, and a second mounting hole is provided on the second vibration damping member. The connecting column simultaneously passes through the first mounting hole and the second mounting hole.

[0008] Optionally, the first vibration damping member and the second vibration damping member have the same shape and are symmetrically arranged on both sides of the vibration damping base.

[0009] Optionally, positioning pins are provided on both side surfaces of the vibration damping base, and positioning grooves are provided on the surfaces of the first vibration damping member and the second vibration damping member opposite to the vibration damping base;

[0010] Or, positioning grooves are provided on both side surfaces of the vibration damping base, and positioning pins are provided on the surfaces of the first vibration damping member and the second vibration damping member opposite to the vibration damping base.

[0011] Optionally, bottom spacers are provided between both the first vibration damping member and the second vibration damping member and the vibration damping base, and hole-shaped structures corresponding to the positioning pins are provided on the bottom spacers.

[0012] Optionally, a first slotted hole is provided on the first vibration damping member, and a second slotted hole is provided on the second vibration damping member. The first mounting hole and the first slotted hole are eccentrically arranged, and the second mounting hole and the second slotted hole are eccentrically arranged;

[0013] Or, a first slotted hole is provided on the first vibration damping member, and a second slotted hole is provided on the second vibration damping member. The first mounting hole is located at the center of the first slotted hole, and the second mounting hole is located at the center of the first slotted hole.

[0014] Optionally, the sleeve structure includes one sleeve or multiple sleeves.

[0015] Optionally, the connecting column is a bolt, and a loosening prevention mechanism is provided at the end. The loosening prevention mechanism includes a slotted nut and a split pin. The slotted nut is sleeved on the end of the bolt, and the split pin passes through the slotted nut and the bolt and is locked.

[0016] Optionally, the number of the installation points is the same as that of the damping components, and each of the damping components can be randomly assembled with each of the installation points.

[0017] Optionally, a plurality of load mounting holes are provided on the damping base, and the load mounting holes are arranged at a preset interval for mounting the load.

[0018] The damping device for the eVTOL aircraft power system provided by the present invention has the following technical effects:

[0019] This damping device is mainly composed of a damping component and a damping base. The damping base is in a ring structure and is made of a metal material. The connecting column can realize the installation and fixation of the damping component and the damping base. The damping component is vulcanized from a rubber material and a metal material, and includes a first damping member and a second damping member. The first damping member and the second damping member are arranged on both sides of the damping base, and the connecting column sequentially passes through the first damping member, the damping base and the second damping member. A sleeve structure is provided between the connecting column and the first damping member and the second damping member. Since the damping base of the present invention has installation points with the same number as the damping components, and the damping base and the damping component form a rubber-metal composite structure, multi-directional vibration control, broadband damping and lightweight can be realized, providing strong technical support for the application of the eVTOL aircraft in the low-altitude economy, and promoting the innovation of the urban air travel mode and the sustainable development of the low-altitude economy.

[0020] The damping device of the present invention adopts a rubber and metal composite structure, achieving excellent static damping effect and shock isolation performance. Through the stiffness matching design and the multi-directional bearing structure (the damping base is in a ring structure, and there are multiple installation points on it for installing the damping components), the damping device can effectively absorb axial and radial vibrations at the same time and maintain stable performance under various working conditions such as compression and shear.

[0021] In addition, the device also has an overload protection function, significantly improving the safety and reliability of the system. The damping device of the present invention is particularly suitable for the distributed electric propulsion system of the eVTOL aircraft, can effectively reduce the high-frequency vibrations generated by the motor and the rotor, improve the flight comfort and the structural fatigue life, and at the same time meet the strict weight and maintenance requirements in the aviation field. Brief Description of the Drawings

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0023] Figure 1 It is a schematic diagram of the overall structure of a preferred embodiment of the vibration damping device for the power system of the eVTOL aircraft of the present invention;

[0024] Figure 2 is Figure 1 The enlarged structural schematic diagram at position A in

[0025] Figure 3 is Figure 2 The sectional view along the A-A direction in

[0026] Figure 4 It is a schematic diagram of the overall structure of another preferred embodiment of the vibration damping device for the power system of the eVTOL aircraft of the present invention;

[0027] Figure 5 is Figure 4 The partial sectional view of the vibration damping device in

[0028] Figure 6 is Figure 4 The side view of the vibration damping device in

[0029] Figure 7 is Figure 1 The dynamic attribute analysis model diagram of the vibration damping device in

[0030] Figure 8 is Figure 1 The coordinate schematic diagram of the vibration damping device in

[0031] Figure 9 is Figure 1 The X-direction model of the vibration damping device in

[0032] Figure 10 is Figure 1 The Y-direction model of the vibration damping device in

[0033] Figure 11 is Figure 1 The Z-direction model of the vibration damping device in

[0034] Among them, Figures 1 - 11 :

[0035] 1. Vibration damping base; 11. Installation point; 12. Load installation hole; 121. Positioning hole; 13. Positioning pin;

[0036] 2. Vibration damping assembly; 21. First vibration damping member; 211. Positioning groove; 22. Second vibration damping member; 23. Bottom spacer; 24. Upper spacer;

[0037] 3. Connecting column;

[0038] 41. Straight sleeve; 42. T-shaped sleeve; 43. Nylon sleeve;

[0039] 5. Anti-loosening mechanism; 51. Slotted nut; 52. Split pin. Detailed implementation manner

[0040] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all embodiments. Based on the embodiments of the present invention, all other implementation manners obtained by those of ordinary skill in the art without creative efforts shall fall within the scope protected by the present invention.

[0041] Based on the defects recorded in the prior art, the following will be combined with specific attached Figures 1 - 11 to describe in detail the vibration damping device for the power system of the eVTOL aircraft of the present invention.

[0042] As Figures 1 - 6 shown, it is a schematic structural diagram of the preferred implementation manner of the vibration damping device for the power system of the eVTOL aircraft of the present invention, and this kind of vibration damping device is mainly composed of the following parts.

[0043] Vibration damping base 1, as Figure 1 shown, it is made of metal material and has an annular structure. The vibration damping base 1 has installation points 11 adapted to the vibration damping assembly 2. Since this implementation manner includes four vibration damping assemblies 2, it also includes four installation points 11.

[0044] The vibration damping assembly 2 of the present invention can be randomly assembled with each installation point 11, reducing the installation difficulty and improving the installation portability.

[0045] In addition to the installation points 11, the vibration damping base 1 is also provided with a plurality of load installation holes 12, such as including 3, 4 or 5, etc. The load installation holes 12 are located between the installation points 11 and are arranged at a preset distance interval for installing loads and do not coincide with the installation points 11.

[0046] In addition to the load mounting holes 12, the vibration damping base 1 is also provided with positioning holes 121. The positioning holes 121 are arranged adjacent to the load mounting holes 12. Here, the number of the positioning holes 121 can be the same as that of the load mounting holes 12 or different from that of the load mounting holes 12. The function of the positioning holes 121 is to realize the mounting and positioning of the load. Here, the load can be a motor or the inner base of the aircraft arm.

[0047] When the load is the inner base of the aircraft arm, the vibration damping assembly 2 is installed on the vibration damping base 1 through hexagon head bolts, and the inner base of the aircraft arm is installed on the load mounting holes 12 through hexagon head bolts. Note the installation direction of the vibration damping assembly 2. The hexagon head bolts are specified with a tightening torque.

[0048] When the load is a motor, the vibration damping base 1 and the motor are connected by bolts at the load mounting holes 12.

[0049] In addition to realizing positioning through the positioning holes 121, protrusions can also be provided on the vibration damping base 1. When the load is a motor, the protrusions and the positioning holes 121 can be used to distinguish the forward and reverse motors.

[0050] The vibration damping assembly 2, as Figures 1 - 3 shown, includes several, preferably four in this embodiment. The four vibration damping assemblies 2 are arranged at a certain distance. The vibration damping assembly 2 is vulcanized from rubber material and metal material, and includes a first vibration damping member 21 and a second vibration damping member 22. The first vibration damping member 21 and the second vibration damping member 22 are arranged on both sides of the annular vibration damping base 1, that is, one of the first vibration damping member 21 and the second vibration damping member 22 is located on the front of the vibration damping base 1, and the other is located on the back of the vibration damping base 1. The connecting column 3 sequentially passes through the first vibration damping member 21, the vibration damping base 1 and the second vibration damping member 22, that is, the connecting column 3 is perpendicular to the plane where the first vibration damping member 21 is located, the plane where the vibration damping base 1 is located and the plane where the second vibration damping member 22 is located at the same time, so as to install and fix the first vibration damping member 21 and the second vibration damping member 22 on the vibration damping base 1.

[0051] As Figure 3 and Figure 5 shown, the shapes of the first vibration damping member 21 and the second vibration damping member 22 are the same and are symmetrically arranged on both sides of the vibration damping base 1. The first vibration damping member 21 is provided with a first mounting hole, and the second vibration damping member 22 is provided with a second mounting hole. The connecting column 3 passes through the first mounting hole and the second mounting hole at the same time.

[0052] As a preferred embodiment, as Figure 3As shown, positioning pins 13 are provided on both side surfaces of the vibration damping base 1, and positioning grooves 211 are provided on the surfaces of the first vibration damping member 21 and the second vibration damping member 22 opposite to the vibration damping base 1; or positioning grooves 211 are provided on both side surfaces of the vibration damping base 1, and positioning pins 13 are provided on the surfaces of the first vibration damping member 21 and the second vibration damping member 22 opposite to the vibration damping base 1.

[0053] In this embodiment, the positioning pins 13 are located on the vibration damping base 1, while the positioning grooves 211 are located on the first vibration damping member 21 and the second vibration damping member 22. The positioning pins 13 are of different sizes, and the corresponding positioning grooves 211 are also of different sizes. They are evenly distributed on both sides of the connecting column 3. The existence of the positioning pins 13 and the positioning grooves 211 can ensure the directionality of installation.

[0054] In the prior art, there is a vibration damping device in which the connecting column 3 passes through the vibration damping assembly 2, the vibration damping base 1 and the load at the same time. In this structure, the load is fixed by the connecting column 3, which is inconvenient to disassemble and is also prone to damage the load. In the present invention, the load is directly installed on the vibration damping base 1 and has no connection relationship with the vibration damping assembly 2, which also facilitates the replacement of the vibration damping assembly 2.

[0055] As Figure 4 shown, a first slotted hole is provided on the first vibration damping member 21, a second slotted hole is provided on the second vibration damping member 22, the first mounting hole is located in the first slotted hole, and the second mounting hole is located in the second slotted hole.

[0056] It should be noted that the first slotted hole and the second slotted hole can be of a slotted shape, a circular shape, or other shapes. The first mounting hole can be concentrically arranged with the first slotted hole or eccentrically arranged with the first slotted hole, and the second mounting hole can be concentrically arranged with the second slotted hole or eccentrically arranged with the second slotted hole.

[0057] When the first mounting hole is concentrically arranged with the first slotted hole and the second mounting hole is concentrically arranged with the second slotted hole, it is not necessary to distinguish the forward and reverse rotations of the motor.

[0058] When the first mounting hole is eccentrically arranged with the first slotted hole and the second mounting hole is eccentrically arranged with the second slotted hole, when bearing the load torque, the first mounting hole and the second mounting hole are twisted relative to the motor, that is, the straight sleeve 41 or the two T-shaped sleeves 42 will return to the middle position of the vibration damping device to ensure that no structural collision occurs under vibration displacement.

[0059] For eVTOL aircraft, there are some points with single motors. In this case, the slotted holes and the mounting holes are set to be non-concentric to resist torque; for some points with dual motors, the torques can cancel each other out, and it is better to set the slotted holes and the mounting holes to be concentric.

[0060] Connecting column 3. The connecting column 3 in this embodiment is preferably a bolt, and the bolt passes through the first mounting hole and the second mounting hole at the same time. As Figure 3 and Figure 5 shown, a loosening prevention mechanism 5 is provided at the end of the bolt, and the connection and fixation of the vibration damping component 2 and the vibration damping base 1 are realized through the loosening prevention mechanism 5.

[0061] The loosening prevention mechanism 5 includes a slotted nut 51 and a split pin 52. The slotted nut 51 is sleeved on the end of the bolt, and the split pin 52 is arranged on the slotted nut 51. The bolt and the slotted nut 51 cooperate with the split pin 52 to achieve the loosening prevention effect.

[0062] The sleeve structure can include one sleeve or three sleeves.

[0063] As Figure 3 shown, when including one sleeve, it is a straight sleeve 41. The straight sleeve 41 is located between the structure composed of the connecting column 3, the vibration damping component 2 and the vibration damping base 1. That is, after the connecting column 3 passes through the straight sleeve 41, the straight sleeve 41 then passes through the vibration damping component 2 and the vibration damping base 1.

[0064] A bottom spacer 23 is provided between both the first vibration damping member 21 and the second vibration damping member 22 and the vibration damping base 1. On the other side of the first vibration damping member 21 and the second vibration damping member 22 away from the vibration damping base 1, there is an upper spacer 24. The straight sleeve 41 is located between the two upper spacers 24. The straight sleeve 41 of the present invention ensures the connection reliability of the structure and ensures the connection and fixation of the load and the vibration damping base 1.

[0065] In addition, in addition to having a hole structure adapted to the straight sleeve 41, the bottom spacer 23 is also provided with a hole structure corresponding to the positioning pin 13, while the upper spacer 24 has a hole structure corresponding to the connecting column 3.

[0066] It should be noted that the bottom spacer 23 and the upper spacer 24 of the present invention are made of the same material as the first vibration damping member 21 and the second vibration damping member 22, and are also bonded and vulcanized with rubber into one body. Reinforcing ribs can also be designed on the bottom spacer 23 and the upper spacer 24 to improve the strength and stability of the structure.

[0067] As Figure 5 shown, when including three sleeves, these three sleeves are respectively two T-shaped sleeves 42 and one nylon sleeve 43. The nylon sleeve 43 is located inside the vibration damping base 1, and the two T-shaped sleeves 42 are respectively located inside the first vibration damping member 21 and the second vibration damping member 22. The inner diameter of the T-shaped sleeve 42 is in transition fit with the inner diameter of the nylon sleeve 43. Therefore, a part of the T-shaped sleeve 42 is placed inside the nylon sleeve 43. The T-shaped sleeve 42 can provide a compression amount, while the nylon sleeve 43 is convenient for installation.

[0068] Next, the dynamic properties of the vibration damping device of the present invention are analyzed.

[0069] The core principle of the dynamic property analysis is to optimize the design of the vibration damping system through simulation modeling and multi-dimensional mechanical evaluation. This analysis adopts a static-dynamic dual-state coupling method, and the main parameters of the vibration damping device are the stiffness and damping coefficient of the vibration damping component 2. The simulation calculation mainly includes the following calculation analyses:

[0070] (1) Static characteristic analysis, such as the static deformation of the motor mount, calculation of the torsional angle, strength calculation, etc.;

[0071] (2) Dynamic characteristic analysis, including the dynamic analysis of the whole machine, vibration coupling analysis, and vibration isolation efficiency analysis;

[0072] The vibration damping base 1 and the vibration damping component 2 are used for static and dynamic analyses to establish a calculation model, as Figure 7 shown.

[0073] First, in the static characteristic analysis, taking the center of the bottom circle of the vibration damping base 1 as the origin of the coordinate system, as Figure 8 shown, the static deformation, torsional angle, and strength check of the metal parts (aluminum alloy 7050) are carried out. This step aims to verify the mechanical properties of the structure under normal and fault condition loads.

[0074] The dynamic characteristic analysis focuses on the dynamic response of the whole machine. By establishing a multi-degree-of-freedom model considering the stiffness and damping coefficient of the vibration damping component 2, the vibration coupling and vibration isolation efficiency are calculated. The design criterion follows the frequency matching principle. For the vibration characteristics at a specific operating speed, the vibration damping target frequency is set to avoid overlapping with the main excitation frequency band.

[0075] The material selection strategy involves differential strength matching. Different yield strength materials (such as stainless steel 304 and 17-4PH alloy) are used to construct a gradient strength system, and the safety of the multi-level load-bearing structure is ensured through the verification of the compressive stress of the vibration damping component 2. The modal analysis confirms the rationality of the installation stiffness design and ensures the effective isolation of the system natural frequency.

[0076] According to Figures 9 - 11 the vibration damping device X-direction model, Y-direction model, and Z-direction model, the parameters shown in Table 1 are obtained.

[0077] Table 1

[0078]

[0079]

[0080] The damping efficiency is evaluated by the power spectral density method to analyze the three-axis vibration transmission. The analysis results show that at the key operating frequencies, the damping efficiency exceeds 95% in the X / Y directions and exceeds 89% in the Z direction, and the overall vibration transmission rate of the machine is reduced by more than 85%. Through the verification of random vibration spectrum loading, the system maintains a high damping efficiency under high-speed conditions, proving the effectiveness of the vibration energy attenuation mechanism and meeting the aircraft's requirements for high-frequency vibration suppression and broadband vibration isolation.

[0081] The following is the material selection of the damping device of the present invention.

[0082] (1) Selection of rubber materials

[0083] The first damping member 21 and the second damping member 22 of the damping assembly 2 are made of the high-temperature durable ZT511 hydrogenated nitrile rubber material independently developed by Zhitian Xinhang. The moisture resistance, salt spray resistance, and acid-resistant atmosphere performance of the hydrogenated nitrile rubber are mainly improved through the research on the vulcanization system and the reinforcing system; the mold resistance performance of the hydrogenated nitrile rubber is studied through the mold prevention system; this rubber material is widely used in engine vibration isolators and aviation dampers, and has excellent shock absorption performance and environmental adaptability. This rubber material has passed the 84d mold strengthening test and the verification and assessment of environmental tests such as GJB salt spray and humidity and heat, and has excellent comprehensive performance.

[0084] (2) Selection of metal parts of the damping device

[0085] According to the forces and installation forms of the various components of the damping device, and considering the material cost and processability of the system, the main idea of material selection for this product is to select mature materials. Zhitian Xinhang has completed the development of multiple engine vibration isolation systems, and the damping base 1 is made of 7050 aluminum alloy, a lightweight and high-strength aviation aluminum material. 7050 aluminum alloy is a cold-treated forging alloy with high strength, good mechanical properties, and corrosion resistance, and is widely used in high-stress structures such as aerospace and mold processing. The metal parts of the damper are selected to be lightweight.

[0086] In the description of the present invention, it should be noted that unless otherwise specified, the meaning of "a plurality" is two or more; the orientation or positional relationships indicated by the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail", etc. are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention. In addition, the terms "first", "second", "third", etc. are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0087] In the description of the present invention, it should also be noted that, unless otherwise clearly specified and defined, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0088] As described above, the above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A vibration damping device for an eVTOL aircraft power system, comprising a plurality of vibration damping components and a vibration damping base for supporting and fixing the vibration damping components, and further comprising a connecting column for connecting and fixing the vibration damping components and the vibration damping base, characterized in that, The damping base is in a ring structure and made of metal material, for connecting and fixing with the load. And the damping base is provided with mounting points adapted to the damping components. The damping components are vulcanized from rubber material and metal material, and include a first damping member and a second damping member. The first damping member and the second damping member are arranged on both sides of the damping base, and the connecting column sequentially passes through the first damping member, the damping base and the second damping member. A sleeve structure is arranged between the connecting column and the first damping member and the second damping member.

2. The vibration damping device for the power system of the eVTOL aircraft according to claim 1, characterized in that, The first damping member is provided with a first mounting hole, and the second damping member is provided with a second mounting hole. The connecting column passes through the first mounting hole and the second mounting hole simultaneously.

3. The vibration damping device for the eVTOL aircraft power system according to claim 2, characterized in that The first damping member and the second damping member have the same shape and are symmetrically arranged on both sides of the damping base.

4. The vibration damping device for the eVTOL aircraft power system according to claim 2, wherein Positioning pins are arranged on the two side surfaces of the damping base, and positioning grooves are arranged on the surfaces of the first damping member and the second damping member opposite to the damping base; Or positioning grooves are arranged on the two side surfaces of the damping base, and positioning pins are arranged on the surfaces of the first damping member and the second damping member opposite to the damping base.

5. The vibration damping device for the eVTOL aircraft power system according to claim 4, characterized in that, A bottom spacer is arranged between both the first damping member and the second damping member and the damping base, and the bottom spacer is provided with a hole-shaped structure corresponding to the positioning pins.

6. The vibration damping device for the eVTOL aircraft power system according to claim 2, characterized in that, The first damping member is provided with a first slotted hole, and the second damping member is provided with a second slotted hole. The first mounting hole and the first slotted hole are eccentrically arranged, and the second mounting hole and the second slotted hole are eccentrically arranged; Or, the first damping member is provided with a first slotted hole, and the second damping member is provided with a second slotted hole. The first mounting hole is located at the center of the first slotted hole, and the second mounting hole is located at the center of the first slotted hole.

7. The vibration damping device for the eVTOL aircraft power system according to any one of claims 2-6, characterized in that, The sleeve structure includes one sleeve or multiple sleeves.

8. The vibration damping device for the eVTOL aircraft power system according to claim 1, wherein, The connecting column is set as a bolt, and an anti-loosening mechanism is arranged at the end. The anti-loosening mechanism includes a slotted nut and a split pin. The slotted nut is sleeved on the end of the bolt, and the split pin passes through the slotted nut and the bolt and is locked.

9. The vibration damping device for the eVTOL aircraft power system according to claim 1, wherein, The number of the mounting points is the same as that of the damping components, and each of the damping components can be randomly assembled with each of the mounting points.

10. The vibration damping device for the eVTOL aircraft power system according to claim 1, characterized in that, The damping base is provided with a plurality of load mounting holes, and the load mounting holes are arranged at intervals of a preset distance for mounting the load.

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