A lift cell damping structure for an eVTOL aircraft

Abstract

The utility model discloses a lift unit damping structure of eVTOL aircraft, including the lift unit damping structure for eVTOL aircraft, lift unit damping structure is by lift unit, support structure and fastener composition, the lift unit is fixedly installed on the support structure with fastener, the support structure is the framework structure of eVTOL aircraft in lift unit position. The utility model discloses a motor seat design electricity joint hole, utilizes fastener and connects electricity joint hole and shock absorber installation fastener and forms the conductive path, can effectively lead out motor electrostatic, guarantees normal operation of motor, adopts the double locking device of "self -locking nut + bolt head fuse hole two and motor seat fuse hole one cooperation fuse " simultaneously, even if a set locking structure failure, another set still can prevent bolt loosening, and the structural safety performance is greatly promoted, satisfies eVTOL aircraft airworthiness requirement.

Description

Technical Field

[0001] This utility model relates to the field of eVTOL aircraft technology, specifically to a vibration reduction structure for the lift unit of an eVTOL aircraft. Background Technology

[0002] eVTOL (Electric Vertical Takeoff and Landing) aircraft can take off and land vertically, eliminating the need for long runways and enabling takeoff and landing operations within limited spaces. This significantly improves the flexibility and accessibility of air transport, making them suitable for scenarios such as urban air mobility. Powered by electricity, they produce no pollutants such as carbon dioxide and nitrogen oxides during operation, meeting the zero-carbon vision and environmental requirements. They also significantly reduce noise, enhancing the passenger experience and comfort. The overall configuration allows for various innovative integrated aerodynamic propulsion designs and unconventional aerodynamic layouts, including multi-rotor, compound, and vector propulsion types, to meet diverse travel needs. Their structure is relatively simple, maintenance requirements are low, and electricity costs are typically lower than fuel costs, suggesting the potential for lower operating costs after large-scale commercial operation.

[0003] The lift unit of an eVTOL aircraft generates lift through the rotation of its propeller blades. Due to the ground effect, the lift is greater when the blades pass the motor arm, while the lift is smaller for other blades that haven't passed the motor arm. This difference in force creates torque. Furthermore, during flight transitions, the advancing blade generates more lift than the retreating blade due to the velocity of the incoming airflow, resulting in a larger bending moment. Because of the rapid propeller rotation, this generates cyclic bending moments and rapid vibrations. The fewer the number of blades, the more concentrated the force on each blade, leading to more pronounced differences in cyclic loads and thus greater bending moments and vibrations. Prolonged exposure to significant vibrations and bending moments can damage the equipment and fuselage structure. Additionally, the large vibrations transmitted into the fuselage can affect passenger comfort, necessitating vibration damping measures.

[0004] The lift unit of an eVTOL aircraft enables vertical takeoff and landing and is a critical power component. To ensure crew safety, all structures must meet relevant airworthiness requirements. Airworthiness regulations explicitly require that "if the loss of a removable fastener may impede continued safe flight and landing, it must have two sets of locking devices." In particular, for the power component, in addition to ensuring the relevant safety factor, the above locking requirements must also be met.

[0005] Chinese utility model patent application number 202422055457.4 discloses "a vibration damping structure for an eVTOL aircraft lift motor," which includes a vibration damping structure on which a lift motor is mounted. The vibration damping structure includes a lower support and an upper support above the lower support. The upper support is connected to the lower support via fasteners and a vibration damping block, with the fasteners passing through the vibration damping block. This structure has good vibration damping effect: the vibration damping block is installed between the upper and lower supports, and the rubber body ensures that there is no hard metal connection between the upper and lower supports, filtering out vibrations generated by the lift motor in the X, Y, and Z directions. This prevents vibrations from the lift motor from being transmitted to the lower support and thus to the aircraft structure. In this example, the vibration damping block achieves a vibration reduction rate of over 80%.

[0006] The Chinese utility model patent application number 202422055457.4, entitled "A Vibration Damping Structure for an eVTOL Aircraft Lift Motor," uses a circular hole connection between the damping block and the lower support. In the high-vibration environment of eVTOL, this connection rotates, causing friction between parts and resulting in wear on the connecting surfaces. After installation, marking lines are made between the bolt heads, connectors, damping blocks, and nuts to facilitate inspection for looseness. If the damping block rotates between itself and the lower support, the marking lines become misaligned, requiring more frequent inspections and leading to higher maintenance costs. Furthermore, the nuts are self-locking nuts with only one locking device, which does not comply with airworthiness regulations. The damping block is installed on the lower support, with half of the structure inside the fuselage, making installation and operation inconvenient and maintenance difficult.

[0007] Therefore, a vibration reduction structure for the lift unit of an eVTOL aircraft is needed to solve the aforementioned problems. Utility Model Content

[0008] To address the problems mentioned in the background art, the purpose of this utility model is to provide a vibration damping structure for the lift unit of an eVTOL aircraft. This structure has the advantages of facilitating motor operation, high safety, good maintainability, reserved space for improvement, and long service life. It solves the problems in existing eVTOL aircraft lift unit vibration damping structures, such as easy rotation of the vibration damping block and support hole connection leading to wear of parts, misalignment of marking lines and increased maintenance costs, insufficient safety due to a single locking device not meeting airworthiness requirements, inconvenient maintenance due to the vibration damping block being located inside the fuselage, and shortened lifespan due to friction between the rubber block and the metal structure.

[0009] To achieve the above objectives, this utility model provides the following technical solution: a lift unit vibration reduction structure for an eVTOL aircraft, comprising a lift unit vibration reduction structure applied to an eVTOL aircraft, the lift unit vibration reduction structure being composed of a lift unit, a support structure and fasteners, the fasteners fixing the lift unit onto the support structure, the support structure being the skeleton structure of the eVTOL aircraft at the lift unit location;

[0010] The lifting unit includes a motor, a motor mount, and a vibration damper. The motor is mounted on the surface of the motor mount. The motor mount is connected to the vibration damper via four lugs. The surface of the motor mount is provided with reinforcing ribs. Vibration damper connection holes for mounting the vibration damper are provided at the four corners of the motor mount. The motor mount is provided with a fuse hole, an electrical connection hole, a test probe connection hole, and an anti-rotation pin hole.

[0011] The support structure includes a mounting frame and a support rib. The mounting frame consists of a mounting frame body and a steel bushing. The surface of the mounting frame body is provided with a reinforcing area, a connecting edge, and a motor wire passage hole. The steel bushing is interference-fitted with the hole of the mounting frame body. The surface of the support rib is connected to the mounting frame by high-strength bolts.

[0012] The fasteners include bolts, washers, and self-locking nuts. A fuse hole one is provided on the surface of the motor base, and a fuse hole two is provided on the head of the bolt. The fuse hole two and fuse hole one are connected by a fuse to form a locking structure, which together with the self-locking nut constitutes a double locking device.

[0013] As a preferred embodiment of this utility model, the vibration damper includes an anti-rotation pin, a rubber block, a metal structure, and a gap. The anti-rotation pin is positioned on the metal surface where the vibration damper and the motor base are in contact. The head of the anti-rotation pin has a tapered structure and is adapted to the anti-rotation pin hole of the motor base.

[0014] The rubber block is vulcanized on the metal structure. Except for the sleeve in the middle that mates with the fastener, the rest of the metal structure is vulcanized and connected to the rubber block. The gap is located between the rubber block and the middle metal structure.

[0015] As a preferred embodiment of this utility model, the surface of the motor base is provided with an electrical connection hole, and the electrical connection hole is connected to the eVTOL aircraft body structure through a ground wire.

[0016] The surface of the motor mount includes a motor connection platform for motor mounting. The surface of the motor connection platform has connection holes for fasteners to pass through, as well as through holes for power supply wiring harnesses and cooling pipes to pass through.

[0017] As a preferred embodiment of this utility model, the mounting frame includes a connecting edge, the front and rear ends of which are connected to the support rib by high-strength bolts, and the left and right ends of which are connected to the skin of the eVTOL aircraft by high-strength bolts.

[0018] The motor wiring hole is a hollow area through which the motor wiring harness and cooling pipes pass. The wiring harness and cooling pipes are connected to the battery pack inside the eVTOL aircraft via the hollow structure inside the support rib.

[0019] In a preferred embodiment of this utility model, the shock absorber is installed on the outside of the mounting frame in an open layout, the bolt passes through the shock absorber and the mounting frame in sequence, and the washer is disposed between the lower part of the mounting frame and the self-locking nut.

[0020] As a preferred embodiment of this invention, the lift unit vibration reduction structure is installed in eight locations on the eVTOL aircraft, with identical structures at each location. A lift unit is fixedly connected to the top and bottom of the support structure to form a coaxial structure, and the upper and lower lift units have the same structure.

[0021] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0022] 1. This utility model designs an electrical connection hole in the motor mount and uses fasteners to connect the electrical connection hole and the damper mounting fastener to form a conductive path, which can effectively discharge static electricity from the motor and ensure normal operation of the motor. At the same time, it adopts a double locking device of "self-locking nut + bolt head fuse hole two and motor mount fuse hole one matching fuse". Even if one locking structure fails, the other can still prevent the bolt from loosening, which greatly improves the structural safety performance and meets the airworthiness requirements of eVTOL aircraft.

[0023] 2. This utility model features a shock absorber mounted on the motor mount in an open-type layout, facilitating installation and maintenance. The anti-rotation pin of the shock absorber mates with the anti-rotation pin hole of the motor mount, preventing the marking lines from misaligning due to the shock absorber's rotation and making it easy to check for loose bolts. Considering the complex airflow and irregular vibration characteristics of eVTOL aircraft during the transition flight phase, a test probe connection hole is reserved in the motor mount. The probe can be installed to measure flight vibration data and compare it with the vibration data of the airframe structure to evaluate the shock absorber's effectiveness and provide data support for subsequent adjustments to the shock absorber design and optimization of its vibration reduction performance.

[0024] 3. This utility model has a gap between the rubber block of the shock absorber and the central metal structure. When the lift unit is subjected to bending moment and vibration, the gap can provide sufficient deformation space for the rubber block, avoid the rubber block from directly rubbing against the central metal structure and causing wear, effectively extend the service life of the shock absorber and reduce the component replacement cost in the long-term operation of eVTOL aircraft. Attached Figure Description

[0025] Figure 1 This is an isometric view of a vibration reduction structure for the lift unit of an eVTOL aircraft, as described in this utility model, installed on an eVTOL aircraft.

[0026] Figure 2 This is an isometric view of a vibration reduction structure for an eVTOL aircraft lift unit according to this utility model;

[0027] Figure 3This is an exploded view of a vibration reduction structure for an eVTOL aircraft lift unit according to this utility model.

[0028] Figure 4 This is an isometric view of the support structure of this utility model;

[0029] Figure 5 This is an exploded view of the mounting frame of this utility model;

[0030] Figure 6 This is an isometric view of the mounting frame body of this utility model;

[0031] Figure 7 This is an exploded view of the lifting unit of this utility model;

[0032] Figure 8 This is an isometric view of the shock absorber of this utility model;

[0033] Figure 9 This is a cross-sectional view of the shock absorber of this utility model along the axis at the position of the anti-rotation pin;

[0034] Figure 10 This is an isometric view of the motor mount of this utility model from a bottom view.

[0035] Figure 11 This is an isometric view of the motor mount of this utility model from a top perspective;

[0036] Figure 12 This is an isometric view of the bolt of this utility model;

[0037] Figure 13 This is a cross-sectional view of the connection between the motor base and the mounting frame of this utility model at the shock absorber position.

[0038] In the diagram: 1. Lift unit vibration damping structure; 11. Lift unit; 111. Motor; 112. Motor mount; 1121. Vibration damper connection hole; 1122. Anti-rotation pin hole; 1123. Test probe connection hole; 1124. Electrical lap hole; 1125. Motor connection platform; 1126. Reinforcing rib; 1127. Fuse hole one; 113. Vibration damper; 1131. Anti-rotation pin; 1132. Rubber block; 1133. Metal structure; 1134. Gap; 12. Support structure; 121. Mounting frame; 1211. Mounting frame body; 12111. Reinforcing area; 12112. Connecting edge; 12113. Motor wiring hole; 122. Support rib; 13. Fastener; 131. Bolt; 1311. Fuse hole two; 132. Washer; 133. Nut; 2. eVTOL aircraft. Detailed Implementation

[0039] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0040] like Figures 1 to 13 As shown, the present invention provides a lift unit vibration reduction structure for an eVTOL aircraft, including a lift unit vibration reduction structure 1 applied to an eVTOL aircraft 2. The lift unit vibration reduction structure 1 consists of a lift unit 11, a support structure 12 and fasteners 13. The fasteners 13 fix the lift unit 11 on the support structure 12. The support structure 12 is the skeleton structure of the eVTOL aircraft 2 at the position of the lift unit 11, which is used to bear the load of the lift unit 11 and transmit it to the body of the eVTOL aircraft 2.

[0041] The lifting unit 11 includes a motor 111, a motor mount 112, and a shock absorber 113. The motor 111 is mounted on the surface of the motor mount 112. The motor mount 112 is connected to the shock absorber 113 through four lugs. The surface of the motor mount 112 is provided with reinforcing ribs 1126. Each of the four corners of the motor mount 112 is provided with shock absorber connection holes 1121 for mounting the shock absorber 113. The motor mount 112 is made of 2024 aluminum alloy machined parts and has a heat treatment state of T351. The overall shape is a circular "bowl" structure. The motor mount 112 is provided with a fuse hole 1127, an electrical connection hole 1124, a test probe connection hole 1123, and an anti-rotation pin hole 1122.

[0042] The support structure 12 includes a mounting frame 121 and a support rib 122. The mounting frame 121 consists of a mounting frame body 1211 and a steel bushing. The surface of the mounting frame body 1211 is provided with a reinforcing area 12111, a connecting edge 12112 and a motor wire hole 12113. The mounting frame body 1211 is made of 2024 aluminum alloy machined parts and has a heat treatment state of T351. The steel bushing is made of 15-5PH stainless steel and has a heat treatment state of H900. The surface of the support rib 122 is connected to the mounting frame 121 by high-strength bolts. The support rib 122 is made of carbon fiber composite material and has a hollow structure inside. Its surface is connected to the mounting frame 121 by high-strength bolts.

[0043] The fastener 13 includes a bolt 131, a washer 132 and a self-locking nut 133. The surface of the motor base 112 is provided with a fuse hole 1127, and the head of the bolt 131 is provided with a fuse hole 1311. The fuse hole 1311 and the fuse hole 1127 are connected by a fuse to form a locking structure, which together with the self-locking nut 133 constitutes a double locking device.

[0044] refer to Figure 7 , Figure 8 and Figure 9 The shock absorber 113 includes an anti-rotation pin 1131, a rubber block 1132, a metal structure 1133, and a gap 1134. The anti-rotation pin 1131 is positioned on the metal of the shock absorber 113 that is in contact with the motor base 112. The head of the anti-rotation pin 1131 has a conical structure and is adapted to the anti-rotation pin hole 1122 of the motor base 112.

[0045] The rubber block 1132 is vulcanized on the metal structure 1133. Except for the sleeve in the middle that mates with the fastener 13, the rest of the metal structure 1133 is vulcanized and connected to the rubber block 1132. The gap 1134 is located between the rubber block 1132 and the middle metal structure 1133 to provide circumferential deformation space for the rubber block 1132.

[0046] As a technical optimization of this utility model, the anti-rotation pin 1131 and the anti-rotation pin hole 1122 are conically matched to achieve precise positioning and installation of the vibration damper 113 and the motor base 112, preventing the vibration damper 113 from rotating axially in a high-vibration environment, ensuring the alignment of the bolt anti-loosening marks, and reducing the frequency of inspection; at the same time, the gap 1134 provides circumferential deformation allowance for the rubber block 1132, preventing the rubber block 1132 from directly rubbing against the central metal sleeve, extending the service life of the vibration damper 113, and the vulcanized metal structure 1133 and the rubber block 1132 can improve the overall rigidity of the vibration damper 113, adapting to the bending moment bearing requirements of the lifting unit 11.

[0047] refer to Figure 10 and Figure 11 The surface of the motor mount 112 is provided with an electrical connection hole 1124, and the electrical connection hole 1124 is connected to the airframe structure of the eVTOL aircraft 2 through a ground wire to discharge the static electricity generated by the motor 111 during operation.

[0048] The test probe connection hole 1123 is used to install the vibration test probe to collect vibration data during the flight of the eVTOL aircraft 2, providing data support for the optimization of the vibration damper 113. This hole can be removed after the motor mount 112 is mass-produced.

[0049] The surface of the motor mount 112 includes a motor connection platform 1125 for mounting the motor 111. The surface of the motor connection platform 1125 has connection holes for fasteners 13 to pass through, as well as through holes for the power supply wiring harness and cooling pipes of the motor 111 to pass through.

[0050] As a technical optimization of this utility model, the electrical connection hole 1124, in conjunction with the grounding wire, breaks the conductive isolation between the motor mount 112 and the fuselage structure caused by the rubber block 1132 of the vibration damper 113, forming an electrostatic conduction path, ensuring that the motor 111 and the fuselage are at the same potential, and avoiding the accumulation of static electricity from affecting the normal operation of the motor 111; the reserved design of the test probe connection hole 1123 can collect flight vibration data in a targeted manner, providing a practical basis for adjusting the parameters of the vibration damper 113, adapting to the vibration optimization requirements of the eVTOL aircraft 2 under complex airflow, and the hole can be flexibly removed after mass production to reduce manufacturing costs; the multi-purpose hole design of the motor connection platform 1125 can integrate the functions of motor fixing, wiring harness and cooling pipe layout, simplifying the structural layout.

[0051] refer to Figure 4 , Figure 5 and Figure 6 The mounting frame 121 includes a connecting edge 12112. The front and rear ends of the connecting edge 12112 are connected to the support rib 122 by high-strength bolts, and the left and right ends of the connecting edge 12112 are connected to the skin of the eVTOL aircraft 2 by high-strength bolts.

[0052] The motor wiring hole 12113 is a hollow area through which the power supply motor 111 wiring harness and cooling pipes pass. The wiring harness and cooling pipes are connected to the battery pack inside the eVTOL aircraft 2 via the hollow structure inside the support rib 122.

[0053] As a technical optimization of this utility model, the connecting edge 12112 is connected to the support rib 122 and the skin with high-locking bolts to form a frame structure with fixed four sides, which improves the overall stability of the mounting frame 121 and can effectively resist the periodic bending moment transmitted by the lifting unit 11. The interference fit between the steel bushing and the mounting frame body 1211 can avoid direct collision and wear between the aluminum alloy mounting frame body 1211 and the bolts 131, and the excellent wear resistance of stainless steel can extend the service life of the mounting frame 121. The cooperation between the motor wire hole 12113 and the hollow structure of the support rib 122 can realize the hidden arrangement of the wiring harness and cooling pipes, avoiding the interference of the external environment on the pipes. At the same time, the carbon fiber composite material of the support rib 122 achieves lightweight design while ensuring structural strength.

[0054] refer to Figure 13 The shock absorber 113 is installed on the outside of the mounting frame 121 in an open layout, which facilitates installation, disassembly and maintenance. The bolt 131 passes through the shock absorber 113 and the mounting frame 121 in sequence. The washer 132 is placed between the lower part of the mounting frame 121 and the self-locking nut 133 to prevent the surface of the mounting frame 121 from being scratched when the self-locking nut 133 is turned.

[0055] As a technical optimization of this utility model, the external open installation of the shock absorber 113 allows for the inspection and replacement of the shock absorber 113 without disassembling other parts of the machine body, greatly improving the convenience of maintenance. The setting of the gasket 132 can form a buffer when the self-locking nut 133 is turned, avoiding scratches on the surface of the mounting frame 121, ensuring the integrity and sealing of the structure. At the same time, the connection method of the bolt 131 through the shock absorber 113 and the mounting frame 121 can ensure the effective transmission of force, and the double locking device can improve the reliability of the connection.

[0056] refer to Figure 1 The lift unit vibration reduction structure 1 is installed in eight locations on the eVTOL aircraft 2, and the structure is the same at each location. The top and bottom of the support structure 12 are fixedly connected to a lift unit 11 to form a coaxial structure. The upper and lower lift units 11 have the same structure and are used to filter the vibration generated by the propeller, reducing the vibration level to an acceptable level of less than 10%.

[0057] As a technical optimization of this utility model, the uniform distribution of lift of the eVTOL aircraft 2 can be achieved through the eight symmetrically arranged lift unit vibration reduction structures 1, ensuring attitude stability during vertical take-off and landing and transition flight phases; the design of coaxial dual lift units 11 can improve lift reserve, while the identical vibration reduction structures at the top and bottom can ensure consistent vibration filtering effect, avoiding damage to the airframe structure or passenger discomfort caused by uneven vibration; the vibration level control of less than 10% can meet the dual requirements of equipment operation and passenger comfort.

[0058] The working principle and usage process of this utility model are as follows: First, the lifting unit 11 is assembled. The motor 111 is fixed to the motor connection platform 1125 of the motor base 112 through the connection hole on the motor connection platform 1125 and the fastener 13. Then, the anti-rotation pin 1131 of the shock absorber 113 is aligned with the anti-rotation pin hole 1122 of the motor base 112 and inserted, so that the four lugs of the shock absorber 113 and the motor base 112 are initially aligned through the shock absorber connection hole 1121. Then, the support structure 12 is assembled. The support rib 122 is connected to the front and rear ends of the connection edge 12112 of the mounting frame 121 with high-strength bolts to form a frame structure. At the same time, it is ensured that the motor wire hole 12113 of the mounting frame 121 is connected to the hollow structure of the support rib 122.

[0059] Next, the lifting unit 11 is connected to the support structure 12. The assembled lifting unit 11 is placed outside the mounting frame 121 of the support structure 12, so that the shock absorber 113 is aligned with the mounting frame 121. The bolt 131 is passed through the steel bushing of the shock absorber 113 and the mounting frame 121 in sequence. After the gasket 132 is put on the lower part of the mounting frame 121, the self-locking nut 133 is tightened for initial fixation. Then, the fuse is passed through the fuse hole 1127 of the motor base 112 and the fuse hole 1311 of the bolt 131 and tied to form a double locking device. At the same time, a set of lifting units 11 is installed on each of the upper and lower sides of the support structure 12 to form a coaxial structure.

[0060] After the connection is completed, auxiliary assembly is performed. One end of the ground wire is connected to the electrical connection hole 1124 of the motor mount 112, and the other end is connected to the fuselage structure of the eVTOL aircraft 2. If it is in the flight test stage, the vibration test probe is installed on the test probe connection hole 1123 of the motor mount 112. Then, the wiring harness and cooling pipe of the motor 111 are passed through the through hole of the motor connection platform 1125 of the motor mount 112, the motor wire hole 12113 of the mounting frame 121, and the hollow structure of the support rib 122 in sequence, and finally connected to the battery pack inside the eVTOL aircraft 2.

[0061] Finally, the entire assembly and use are carried out. The eight assembled lift unit vibration damping structures 1 (with identical structures at each location) are installed at the pre-set positions on the eVTOL aircraft 2 lift unit. They are secured to the skin of the eVTOL aircraft 2 using high-strength bolts at both ends of the mounting frame 121 connecting edge 12112. During the eVTOL aircraft 2's vertical takeoff and landing, transition flight, and level flight phases, the motor 111 of the lift unit 11 drives the propeller to rotate, generating lift. The vibration generated by the propeller is transmitted through the motor 111 to the motor mount 112, and then buffered and filtered by the rubber blocks 1132 of the vibration damper 113 (reducing the vibration level to a minimum). (less than 10%), the gap 1134 provides circumferential deformation space for the rubber block 1132 to avoid wear, the anti-rotation pin 1131 prevents the vibration damper 113 from rotating to ensure that the bolt anti-loosening mark is clear, the electrical connection hole 1124 discharges the static electricity of the motor 111 through the ground wire, and the double locking device ensures that the fastener 13 does not loosen. During the test flight stage, vibration data is collected by the probe through the test probe connection hole 1123 for the optimization of the vibration damper 113. After mass production, the test probe connection hole 1123 can be eliminated. During maintenance, the fastener 13 can be removed directly in the open area outside the mounting frame 121 to repair or replace the vibration damper 113 and other components.

[0062] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0063] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A lift unit vibration reduction structure for an eVTOL aircraft, comprising a lift unit vibration reduction structure (1) applied to an eVTOL aircraft (2), characterized in that: The lifting unit vibration reduction structure (1) consists of a lifting unit (11), a support structure (12) and fasteners (13). The fasteners (13) fix the lifting unit (11) on the support structure (12). The support structure (12) is the skeleton structure of the eVTOL aircraft (2) at the position of the lifting unit (11). The lifting unit (11) includes a motor (111), a motor mount (112), and a shock absorber (113). The motor (111) is mounted on the surface of the motor mount (112). The motor mount (112) is connected to the shock absorber (113) through four lugs. The surface of the motor mount (112) is provided with reinforcing ribs (1126). Each of the four corners of the motor mount (112) is provided with a shock absorber connection hole (1121) for mounting the shock absorber (113). The motor mount (112) is provided with a fuse hole (1127), an electrical connection hole (1124), a test probe connection hole (1123), and an anti-rotation pin hole (1122). The support structure (12) includes a mounting frame (121) and a support rib (122). The mounting frame (121) is composed of a mounting frame body (1211) and a steel bushing. The surface of the mounting frame body (1211) is provided with a reinforcing area (12111), a connecting edge (12112) and a motor wire hole (12113). The steel bushing is interference-fitted with the hole of the mounting frame body (1211). The surface of the support rib (122) is connected to the mounting frame (121) by a high-strength bolt. The fastener (13) includes a bolt (131), a washer (132), and a self-locking nut (133). The surface of the motor base (112) is provided with a fuse hole (1127), and the head of the bolt (131) is provided with a fuse hole (1311). The fuse hole (1311) and the fuse hole (1127) are connected by a fuse to form a locking structure, which together with the self-locking nut (133) constitutes a double locking device.

2. The lift unit vibration reduction structure for an eVTOL aircraft according to claim 1, characterized in that: The shock absorber (113) includes an anti-rotation pin (1131), a rubber block (1132), a metal structure (1133), and a gap (1134). The anti-rotation pin (1131) is positioned on the metal where the shock absorber (113) and the motor base (112) are in contact. The head of the anti-rotation pin (1131) is tapered and is adapted to the anti-rotation pin hole (1122) of the motor base (112). The rubber block (1132) is vulcanized on the metal structure (1133). Except for the sleeve in the middle that mates with the fastener (13), the rest of the metal structure (1133) is vulcanized and connected to the rubber block (1132). The gap (1134) is located between the rubber block (1132) and the middle metal structure (1133).

3. The lift unit vibration reduction structure for an eVTOL aircraft according to claim 1, characterized in that: The surface of the motor mount (112) is provided with an electrical connection hole (1124), and the electrical connection hole (1124) is connected to the body structure of the eVTOL aircraft (2) through a ground wire; The surface of the motor mount (112) includes a motor connection platform (1125) for mounting the motor (111). The surface of the motor connection platform (1125) is provided with connection holes for fasteners (13) to pass through, as well as through holes for the power supply (111) wiring harness and cooling pipes to pass through.

4. The lift unit vibration reduction structure for an eVTOL aircraft according to claim 1, characterized in that: The mounting frame (121) includes a connecting edge (12112), the front and rear ends of which are connected to the support rib (122) by high-strength bolts, and the left and right ends of which are connected to the skin of the eVTOL aircraft (2) by high-strength bolts. The motor wiring hole (12113) is a hollow area through which the motor (111) wiring harness and cooling pipes pass. The wiring harness and cooling pipes are connected to the battery pack inside the eVTOL aircraft (2) through the hollow structure inside the support rib (122).

5. The lift unit vibration reduction structure for an eVTOL aircraft according to claim 1, characterized in that: The shock absorber (113) is installed on the outside of the mounting frame (121) in an open layout. The bolt (131) passes through the shock absorber (113) and the mounting frame (121) in sequence. The washer (132) is located between the lower part of the mounting frame (121) and the self-locking nut (133).

6. The lift unit vibration reduction structure for an eVTOL aircraft according to claim 1, characterized in that: The lifting unit vibration reduction structure (1) is set in eight locations on the eVTOL aircraft (2), and the structure of each location is the same. The top and bottom of the support structure (12) are fixedly connected to a lifting unit (11) to form a coaxial structure. The upper and lower lifting units (11) have the same structure.

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