EVTOL aircraft power system damping device

Abstract

The utility model provides an eVTOL aircraft power system damping device, which relates to the technical field of damping, and mainly comprises a damping component and a damping base, the damping base is of an annular structure and is made of metal materials, and a connecting column can realize the installation and fixation of the damping component and the damping base. 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 rubber materials and metal materials in a vulcanization mode, each vibration reduction assembly comprises a first vibration reduction piece and a second vibration reduction piece, and sleeve structures are arranged between the connection column and the first vibration reduction piece and between the connection column and the second vibration reduction piece. 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 utility model relates to mechanical damping technical field especially is related to a kind of eVTOL aircraft power system damping device. BACKGROUND

[0002] With the rapid development of low-altitude economy, urban air travel gradually becomes an important part of future transportation. eVTOL (Electric Vertical Take-off and Landing) is an electric vertical take-off and landing aircraft, which realizes vertical take-off and landing (VTOL) through electric power driving, without runway or special landing site, and can be widely applied in urban air transportation (UAM), logistics distribution, emergency rescue and other fields. As a key transportation tool in low-altitude economy, eVTOL aircraft has application scenarios including urban short-distance transportation, emergency rescue, logistics distribution, etc., with advantages of high efficiency, flexibility, environmental protection, etc.

[0003] However, eVTOL aircraft needs frequent take-off and landing and low-speed flight in complex urban environment, which puts higher requirements on vibration control of power system. The vibration of power system not only affects the stability and safety of aircraft, but also reduces the comfort of passengers, and even shortens the service life of key components.

[0004] During the flight subject test phase of eVTOL aircraft, the whole machine shows serious vibration problem, which seriously threatens the aircraft structure and series subsystems (avionics, flight control, photoelectricity), especially between the wing and the motor seat, due to excessive vibration, which directly leads to the occurrence of vibration cracking phenomenon in many places of wing arm structure, and it is urgent to introduce damping device to solve the current problem. UTILITY MODEL CONTENT

[0005] Therefore, the purpose of the utility model is to provide an eVTOL aircraft power system damping device to solve the technical problem that the existing eVTOL aircraft has serious vibration problem, which seriously threatens the aircraft structure and series subsystems (avionics, flight control, photoelectricity).

[0006] In order to achieve the above object, the utility model provides a kind of eVTOL aircraft power system damping device, including several damping components and the damping pedestal for supporting and fixing the damping component, further include the connecting column for connecting and fixing the damping component and the damping pedestal, the damping pedestal is annular structure, made of metal material, for being connected with load and fixed, and the damping pedestal is equipped with the mounting point position adapted with the damping component, the damping component is vulcanized by rubber material and metal material, and including first damping piece and second damping piece, the first damping piece and the second damping piece are located on the two sides of the damping pedestal, and the connecting column sequentially passes through the first damping piece, the damping pedestal and the second damping piece, sleeve structure is equipped between the connecting column and the first damping piece and the second damping piece.

[0007] Optionally, the first damping piece is equipped with first mounting hole, the second damping piece is equipped with second mounting hole, and the connecting column simultaneously passes through the first mounting hole and the second mounting hole.

[0008] Optionally, the first damping piece and the second damping piece are consistent in shape, and symmetrically arranged on the two sides of the damping pedestal.

[0009] Optionally, the two side surfaces of the damping pedestal are equipped with positioning pin, and the opposite surfaces of the first damping piece and the second damping piece to the damping pedestal are equipped with positioning groove.

[0010] Or the two side surfaces of the damping pedestal are equipped with positioning groove, and the opposite surfaces of the first damping piece and the second damping piece to the damping pedestal are equipped with positioning pin.

[0011] Optionally, the first damping piece and the second damping piece are both equipped with bottom septum between the damping pedestal, and the bottom septum is equipped with hole structure corresponding to the positioning pin.

[0012] Optionally, the first damping piece is equipped with first slot hole, and the second damping piece is equipped with second slot hole, and the first mounting hole and the first slot hole are eccentrically arranged, and the second mounting hole and the second slot hole are eccentrically arranged.

[0013] Or, the first damping piece is equipped with first slot hole, and the second damping piece is equipped with second slot hole, and the first mounting hole is located at the center of the first slot hole, and the second mounting hole is located at the center of the first slot hole.

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

[0015] Optionally, the connecting column is provided as a bolt, and the end is provided with an anti-loosening mechanism, the anti-loosening mechanism comprising a slotted nut and a split pin, the slotted nut being sleeved on the end of the bolt, and the split pin penetrating through the slotted nut and the bolt and being locked.

[0016] Optionally, the mounting points are consistent in number with the damping assemblies, and each damping assembly can be randomly matched with each mounting point.

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

[0018] The eVTOL aircraft power system damping device provided by the utility model has the following technical effects:

[0019] The damping device mainly comprises a damping assembly and a damping base, the damping base is in a ring structure and is made of a metal material, the connecting column can realize mounting and fixing of the damping assembly and the damping base, the damping assembly is vulcanized from a rubber material and a metal material and comprises a first damping piece and a second damping piece, the first damping piece and the second damping piece are arranged on the two sides of the damping base, and the connecting column penetrates through the first damping piece, the damping base and the second damping piece in sequence, and a sleeve structure is arranged between the connecting column and the first damping piece and the second damping piece, since the damping base is provided with mounting points consistent in number with the damping assemblies, and the damping base and the damping assembly form a rubber-metal composite structure, multidirectional vibration control, wideband damping and light weight can be realized, strong technical support is provided for application of the eVTOL aircraft in low-altitude economy, and innovation of urban air travel mode and sustainable development of low-altitude economy are promoted.

[0020] The damping device adopts a rubber-metal composite structure, excellent static damping effect and impact isolation performance are realized, through stiffness matching design and a multidirectional bearing structure (the damping base is in a ring structure and is provided with a plurality of mounting points for mounting the damping assemblies), 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 shearing.

[0021] In addition, the device also has an overload protection function, which significantly improves the safety and reliability of the system. The damping device is particularly suitable for distributed electric propulsion systems of eVTOL aircrafts, can effectively reduce high-frequency vibrations generated by motors and rotors, improve flight comfort and structural fatigue life, and at the same time meet strict weight and maintenance requirements in the aviation field. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced as follows. Obviously, the drawings in the following description only constitute some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

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

[0024] Figure 2 is Figure 1 is an enlarged structural schematic diagram of position A in the damping device;

[0025] Figure 3 is Figure 2 is a sectional view along the A-A direction in the damping device;

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

[0027] Figure 5 is Figure 4 is a partial sectional view of the damping device in the damping device;

[0028] Figure 6 is Figure 4 is a side view of the damping device in the damping device;

[0029] Figure 7 is Figure 1 is a dynamic property analysis model diagram of the damping device in the damping device;

[0030] Figure 8 is Figure 1 is a coordinate diagram of the damping device in the damping device;

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

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

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

[0034] wherein, Figures 1-11 :

[0035] 1, damping base; 11, mounting point; 12, load mounting hole; 121, positioning hole; 13, positioning pin;

[0036] 2, damping assembly; 21, first damping piece; 211, positioning groove; 22, second damping piece; 23, bottom partition; 24, upper partition;

[0037] 3, connecting column;

[0038] 41, straight sleeve; 42, T-shaped sleeve; 43, nylon sleeve;

[0039] 5, anti-loosening mechanism; 51, slotted nut; 52, cotter pin. DETAILED DESCRIPTION

[0040] In order to make the purpose, technical scheme and advantages of the utility model more clear, the technical scheme of the utility model will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the scope protected by the utility model.

[0041] Based on the defects recorded in the prior art, the specific drawings will be combined below Figures 1-11 The damping device for the power system of the eVTOL aircraft of the utility model is described in detail.

[0042] As Figures 1-6 shown, it is the structure schematic view of the preferred embodiment of the damping device for the power system of the eVTOL aircraft of the utility model. The damping device is mainly composed of the following parts.

[0043] The damping base 1, as Figure 1 shown, is made of metal material and has a ring structure. The damping base 1 has mounting points 11 adapted to the damping assemblies 2. Since the embodiment includes four damping assemblies 2, it also includes four mounting points 11.

[0044] The damping assembly 2 of the utility model can be randomly matched with each mounting point 11, which reduces the installation difficulty and improves the portability of installation.

[0045] In addition to the mounting points 11, the damping base 1 is also provided with a plurality of load mounting holes 12, for example, 3, 4 or 5, etc. The load mounting holes 12 are located between the mounting points 11 and are arranged at a predetermined distance apart, used for mounting loads, and do not coincide with the mounting points 11.

[0046] The damping base 1 has positioning holes 121 in addition to the load mounting holes 12, which are arranged close to the load mounting holes 12. The number of the positioning holes 121 can be consistent with or inconsistent with the number of the load mounting holes 12. The positioning holes 121 are used for positioning the load, which can be a motor or an internal base of an airplane arm.

[0047] When the load is an internal base of an airplane arm, the damping assembly 2 is mounted on the damping base 1 by hexagonal head bolts, and the internal base of the airplane arm is mounted on the load mounting holes 12 by hexagonal head bolts. The mounting direction of the damping assembly 2 is noted, and the hexagonal head bolts are provided with a tightening torque.

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

[0049] In addition to positioning by the positioning holes 121, protrusions can be provided on the 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 rotation motors.

[0050] The damping assembly 2, as shown in Figures 1-3 , includes several, preferably four, damping assemblies 2. The damping assemblies 2 are arranged at a certain distance apart and are vulcanized from rubber and metal materials. The damping assembly 2 includes a first damping piece 21 and a second damping piece 22. The first damping piece 21 and the second damping piece 22 are arranged on both sides of the annular damping base 1, i.e., one of the first damping piece 21 and the second damping piece 22 is located on the front surface of the damping base 1, and the other is located on the back surface of the damping base 1. The connecting column 3 passes through the first damping piece 21, the damping base 1, and the second damping piece 22 in sequence, i.e., the connecting column 3 is perpendicular to the planes on which the first damping piece 21, the damping base 1, and the second damping piece 22 are located, thereby mounting and fixing the first damping piece 21 and the second damping piece 22 on the damping base 1.

[0051] As shown in Figure 3 and Figure 5 , the first damping piece 21 and the second damping piece 22 have the same shape and are symmetrically arranged on both sides of the damping base 1. The first damping piece 21 is provided with a first mounting hole, and the second damping piece 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 shown in Figure 3As shown, the two side surfaces of the damping base 1 are provided with positioning pins 13, and the surfaces opposite to the damping base 1 of the first damping member 21 and the second damping member 22 are provided with positioning grooves 211; or the two side surfaces of the damping base 1 are provided with positioning grooves 211, and the surfaces opposite to the damping base 1 of the first damping member 21 and the second damping member 22 are provided with positioning pins 13.

[0053] The positioning pins 13 of the embodiment are located on the damping base 1, and the positioning grooves 211 are located on the first damping member 21 and the second damping member 22. The positioning pins 13 are large and small, and the corresponding positioning grooves 211 are large and small. They are 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] The prior art has a damping device in which the connecting column 3 simultaneously penetrates the damping assembly 2, the damping base 1 and the load. This structure fixes the load through the connecting column 3, which is inconvenient to disassemble and is easy to damage the load. The load of the damping device is directly installed on the damping base 1 and does not have a connection relationship with the damping assembly 2, which is convenient for replacing the damping assembly 2.

[0055] As shown in the accompanying drawings, Figure 4 The first mounting hole is located in the first slot-shaped hole, and the second mounting hole is located in the second slot-shaped hole.

[0056] It should be noted that the first slot-shaped hole and the second slot-shaped hole can be slot-shaped, circular or other shapes. The first mounting hole can be concentrically arranged with the first slot-shaped hole or eccentrically arranged with the first slot-shaped hole. The second mounting hole can be concentrically arranged with the second slot-shaped hole or eccentrically arranged with the second slot-shaped hole.

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

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

[0059] For eVTOL aircraft, some points are single motors. In this case, the slot-shaped hole and the mounting hole are arranged to be eccentric to resist torque. For the case where some points are double motors, the torque can be offset by each other, and it is better to arrange the slot-shaped hole and the mounting hole to be concentric.

[0060] The connecting column 3 is preferably a bolt in the embodiment, the bolt passes through the first mounting hole and the second mounting hole at the same time, as shown in the figure Figure 3 And Figure 5 As shown, the end of the bolt is provided with a lock mechanism 5, and the connection and fixation of the damping assembly 2 and the damping base 1 are realized through the lock mechanism 5.

[0061] The lock 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, and the bolt and the slotted nut 51 cooperate with the split pin 52 to achieve the locking effect.

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

[0063] As shown in the figure Figure 3 When including one sleeve, it is a straight sleeve 41, the straight sleeve 41 is located between the connecting column 3 and the structure composed of the damping assembly 2 and the damping base 1, that is, after the connecting column 3 passes through the straight sleeve 41, the straight sleeve 41 passes through the damping assembly 2 and the damping base 1.

[0064] The first damping part 21 and the second damping part 22 are provided with a bottom partition 23 between the damping base 1, and the other side of the first damping part 21 and the second damping part 22 away from the damping base 1 has an upper partition 24, and the straight sleeve 41 is located between the two upper partitions 24, the straight sleeve 41 of the utility model ensures the connection reliability of the structure, and ensures the connection and fixation of the load and the damping base 1.

[0065] In addition, in addition to having a hole structure matched with the straight sleeve 41, the bottom partition 23 also has a hole structure corresponding to the positioning pin 13, and the upper partition 24 has a hole structure corresponding to the connecting column 3.

[0066] It should be noted that the bottom partition 23 and the upper partition 24 of the utility model are consistent with the material of the first damping part 21 and the second damping part 22, and are also integrated with the rubber vulcanization through bonding, and the bottom partition 23 and the upper partition 24 can also be designed with reinforcing ribs to improve the strength and stability of the structure.

[0067] As shown in the figure Figure 5 When including three sleeves, the three sleeves are two T-shaped sleeves 42 and a nylon sleeve 43, the nylon sleeve 43 is located in the damping base 1, and the two T-shaped sleeves 42 are located in the first damping part 21 and the second damping part 22 respectively, the inner diameter of the T-shaped sleeve 42 is in transition fit with the inner diameter of the nylon sleeve 43, so that the T-shaped sleeve 42 is in the nylon sleeve 43, the T-shaped sleeve 42 can provide a compression amount, and the nylon sleeve 43 is convenient to install.

[0068] The dynamic properties of the damping device of the utility model are analyzed as follows.

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

[0070] (1) Static characteristic analysis, including static deformation of motor mounting, calculation of torsion angle, and strength calculation;

[0071] (2) Dynamic characteristic analysis, whole machine dynamics analysis, vibration coupling analysis, vibration isolation efficiency analysis;

[0072] Static and dynamic analyses were performed using vibration damping base 1 and vibration damping component 2 to establish a calculation model, such as... Figure 7 As shown.

[0073] Firstly, in the static characteristic analysis, the center of the bottom circle of the vibration damping base 1 is taken as the origin of the coordinate system, such as... Figure 8 As shown, static deformation, torsional angle, and strength checks were performed on the metal component (aluminum alloy 7050). This step aims to verify the mechanical properties of the structure under normal and fault load conditions.

[0074] Dynamic characteristic analysis focuses on the overall dynamic response of the machine. By establishing a multi-degree-of-freedom model that considers the stiffness and damping coefficient of vibration damping component 2, vibration coupling and isolation efficiency are calculated. The design criteria follow the frequency matching principle, setting the target frequency for vibration reduction based on the vibration characteristics at a specific operating speed to avoid overlap with the main excitation frequency band.

[0075] The material selection strategy involves differentiated strength matching, using materials with different yield strengths (such as 304 stainless steel and 17-4PH alloy) to construct a gradient strength system, and ensuring the safety of the multi-layered load-bearing structure through compressive stress verification of vibration damping component 2. Modal analysis confirmed the rationality of the installation stiffness design and ensured effective isolation of the system's natural frequencies.

[0076] according to Figures 9-11 The X-direction model, Y-direction model and Z-direction model of the vibration damping device were used to obtain the parameters shown in Table 1.

[0077] Table 1

[0078] Direction 2 input / RMS (gHz) 2 output / RMS (gHz) De- efficacy (%) X 17.462 0.61609 96.5 Y 15.56 0.62754 96 Z 9.1529 1.0011 89.1

[0079] The vibration reduction efficiency is evaluated by using the power spectral density method, and the three-axis vibration transmission is analyzed. The analysis results show that at the key working frequency, the vibration reduction efficiency is more than 95% in the X / Y direction, more than 89% in the Z direction, and the whole machine vibration transmission rate is reduced by more than 85%. Through the verification of random vibration spectrum loading, the system maintains high vibration reduction efficiency under high-speed working condition, which proves the effectiveness of the vibration energy attenuation mechanism and meets the needs of the aircraft for high-frequency vibration suppression and wide-frequency vibration isolation.

[0080] The following is the material selection of the vibration reduction device of the utility model.

[0081] (1) Selection of rubber material

[0082] The first damping member 21 and the second damping member 22 of the damping assembly 2 are selected from the high-temperature durability ZT511 hydrogenated nitrile rubber material independently researched by Zitian Xinhang, which mainly improves the wet heat resistance, salt spray resistance and acid atmosphere resistance of the hydrogenated nitrile rubber through the research on the vulcanization system and the reinforcing system; the mold resistance of the hydrogenated nitrile rubber is researched through the mold resistance system; the rubber material is widely used in engine vibration isolators and aviation dampers, and has excellent damping performance and environmental adaptability. The rubber material has passed the 84d mold strengthening test, GJB salt spray, wet heat and other environmental test verification, and has excellent comprehensive performance.

[0083] (2) Selection of metal parts of the vibration reduction device

[0084] According to the stress and installation form of each component of the vibration reduction device, and considering the material cost and process of the system, the material selection of the product is to select mature materials. Zitian Xinhang has completed the research and development of multiple engine vibration isolation systems, and the damping base 1 adopts 7050 aluminum alloy light weight high strength aviation aluminum material. 7050 aluminum alloy is a cold treated forged alloy, which has high strength, good mechanical properties and corrosion resistance, and is widely used in aerospace, mold processing and other high stress structures. The metal parts of the damper are light in weight.

[0085] In the description of the utility model, it should be explained that, unless otherwise stated, the meaning of "multiple" is two or more; the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail" and the like indicate the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the utility model and simplifying the description, and does not indicate or imply that the indicated device or element must have a specific orientation, structure and operation, therefore it cannot be understood as a limitation on the utility model. In addition, the terms "first", "second", "third" and the like are only for description purposes, and cannot be understood as indicating or implying relative importance.

[0086] In the description of the utility model, still need to explain, unless another explicit provision and limitation, term " install " " link " " connection " should do broad sense understanding, for example, can be fixed connection, also can be detachable connection, or integrally connected;Can be mechanical connection, also can be electrical connection;Can be directly connected, also can be indirectly connected through the intermediate medium.

[0087] The above merely illustrates the specific embodiments of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An eVTOL aircraft power system damping device, comprising a plurality of damping assemblies and a damping base for supporting and fixing the damping assemblies, further comprising a connecting column for connecting and fixing the damping assemblies and the damping base, characterized in that, The damping base is annular in structure and made of metal material, is used for connecting and fixing with a load, and is provided with mounting point positions adapted to the damping assemblies.

2. The eVTOL aircraft power system damping device of claim 1, wherein, The first damping member and the second damping member are provided with first mounting holes and second mounting holes respectively, and the connecting column passes through the first mounting holes and the second mounting holes simultaneously.

3. The eVTOL aircraft power system damping device of claim 2, wherein, The first damping member and the second damping member are symmetrical and provided on two sides of the damping base.

4. The eVTOL aircraft power system damping device of claim 2, wherein, The opposite surfaces of the first damping member and the second damping member to the damping base are provided with positioning grooves. The opposite surfaces of the first damping member and the second damping member to the damping base are provided with positioning grooves.

5. The eVTOL aircraft power system damping device of claim 4, wherein, The first damping member and the second damping member are provided with bottom spacers between the damping base.

6. The eVTOL aircraft power system damping device of claim 2, wherein, The first damping member and the second damping member are provided with first slot-shaped holes and second slot-shaped holes respectively, the first mounting holes are eccentric to the first slot-shaped holes, and the second mounting holes are eccentric to the second slot-shaped holes. The first damping member and the second damping member are provided with first slot-shaped holes and second slot-shaped holes respectively, the first mounting holes are located at the centers of the first slot-shaped holes, and the second mounting holes are located at the centers of the second slot-shaped holes.

7. The eVTOL aircraft power system damping device of any of claims 2-6, wherein, The sleeve structure comprises one sleeve or a plurality of sleeves.

8. The eVTOL aircraft power system damping device of claim 1, wherein, The connecting column is provided as a bolt, and the end thereof is provided with a loosening prevention mechanism, the loosening prevention mechanism comprises a slotted nut and a split pin, the slotted nut is sleeved on the end of the bolt, the split pin passes through the slotted nut and the bolt, and is locked.

9. The eVTOL aircraft power system damping device of claim 1, wherein, The mounting point positions are consistent with the number of the damping assemblies, and each damping assembly can be randomly matched with each mounting point position.

10. The eVTOL aircraft power system damping device of claim 1, wherein, The damping base is provided with a plurality of load mounting holes, the load mounting holes are arranged at a predetermined distance, and are used for mounting the load.

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