An anisotropic flange for achieving energy splitting

Abstract

This application relates to an anisotropic flange for realizing energy wave division, used to connect an engine and a motor of an aerospace vehicle, comprising: a connecting ring including an outer connecting ring and an inner connecting ring, the outer connecting ring being configured to connect to the housing of the engine, and the inner connecting ring being configured to connect to the motor; an elastic wave control component array disposed between the inner connecting ring and the outer connecting ring, comprising a plurality of elastic wave control components connected end to end; wherein, each elastic wave control component comprises multiple layers of microstructure components arranged sequentially from the inner connecting ring to the outer connecting ring, each of the multiple layers of microstructure components having at least one microstructure unit; the microstructure unit has anisotropic stiffness, so that the flange has anisotropic stiffness, thereby allowing the elastic wave generated by the motor to be transmitted circumferentially along the flange.

Description

Technical Field

[0001] This application relates to the field of flange technology, and in particular to an anisotropic flange for realizing energy splitting. Background Technology

[0002] Aerospace vehicles are crucial equipment for space exploration and operation. The noise generated by their engines during operation can have varying degrees of impact on the environment, equipment, and vehicle structure. By effectively controlling the vibration and noise of aircraft engines, damage to the vehicle structure can be reduced, operational stability can be improved, and overall performance can be enhanced.

[0003] Currently, vibration and noise reduction technologies for aerospace vehicle engines mainly include vibration isolation and damping, acoustic insulation, and active control. However, these methods increase the weight and size of the aircraft, while active control methods are limited by their system complexity and response speed, making them difficult to cope with rapidly changing noise and vibration. In summary, existing vibration and noise reduction methods cannot achieve efficient control of engine noise and vibration while simultaneously considering the weight and size of the aircraft. Summary of the Invention

[0004] The present invention provides an anisotropic flange for realizing energy splitting, which at least solves the problem in related technologies that it is impossible to achieve efficient control of engine noise and vibration while taking into account the weight and volume of the aircraft.

[0005] According to an embodiment of the present invention, an anisotropic flange for realizing energy splitting is provided, characterized in that the flange is used to connect the engine and motor of an aerospace vehicle, and the flange includes:

[0006] A connecting ring, including an outer connecting ring and an inner connecting ring, the outer connecting ring being configured to connect to the housing of the engine, and the inner connecting ring being configured to connect to the motor;

[0007] An elastic wave control component array is disposed between the inner connecting ring and the outer connecting ring, and includes multiple elastic wave control components connected end to end in sequence.

[0008] Each of the elastic wave control components includes multiple layers of microstructure components arranged sequentially from the inner connecting ring to the outer connecting ring. Each of the multiple layers of microstructure components is provided with at least one microstructure unit. The microstructure unit has anisotropic stiffness so that the flange has anisotropic stiffness, thereby allowing the elastic wave generated by the motor to be transmitted along the circumference of the flange.

[0009] Optionally, the number of microstructure units corresponding to each of the multi-layer microstructure components is different, and the number of microstructure units corresponding to each of the multi-layer microstructure components increases sequentially from the inner layer to the outer layer.

[0010] Optionally, the microstructure unit is provided with a crossbeam, and vertical beams are respectively connected to both ends of the crossbeam, with the vertical beams being arranged perpendicular to the crossbeam.

[0011] Optionally, the microstructure units in adjacent layers of the microstructure components are arranged alternately.

[0012] Optionally, the multilayer elastic wave control component includes a first-level microstructure component, a second-level microstructure component, a third-level microstructure component, a fourth-level microstructure component, and a fifth-level microstructure component arranged sequentially from the inner connecting ring to the outer connecting ring.

[0013] Optionally, the first-level microstructure component has one microstructure unit, the second-level microstructure component has two microstructure units, the third-level microstructure component has three microstructure units, the fourth-level microstructure component has four microstructure units, and the fifth-level microstructure component has five microstructure units.

[0014] Optionally, the elastic wave control component is connected to the inner connecting ring via a radial connecting beam, wherein one end of the radial connecting beam is connected to the microstructure unit in the primary microstructure component, and the other end is connected to the inner connecting ring;

[0015] The elastic wave control component is connected to the outer connecting ring through the end of the microstructure unit of the five-level microstructure component.

[0016] Optionally, inclined support beams are provided on both sides of the radial connecting beam, and the two inclined support beams are symmetrically arranged with respect to the radial connecting beam;

[0017] One end of the inclined support beam is fixedly connected to the middle of the radial connecting beam, and the other end is fixedly connected to the inner connecting ring.

[0018] Optionally, at least one circumferential connecting beam is provided between two adjacent elastic wave control components, and the circumferential connecting beam is provided on at least one layer of elastic wave control components among the secondary microstructure component, the tertiary microstructure component, and the quaternary microstructure component.

[0019] Optionally, the diameter of the inner connecting ring is one-third of the diameter of the outer connecting ring, and the length of the vertical beam is one-third of the diameter of the inner connecting ring.

[0020] Beneficial effects of the embodiments of the present invention:

[0021] The anisotropic flange for energy wave splitting provided in this invention can achieve efficient control of engine noise and vibration while considering the weight and volume of the aircraft. Specifically, by setting multiple layers of microstructure components containing microstructure units with anisotropic stiffness between the inner and outer connecting rings of the flange, the flange acquires anisotropic stiffness characteristics, altering the propagation path and mode of elastic waves. Because the stiffness of the microstructure units varies in different directions, the elastic waves are modulated as they propagate along the flange circumferentially, causing some wave energy to be deflected or dispersed, thereby reducing the energy transfer of elastic waves in the normal direction of the outer shell surface. Based on this structure, the vibration amplitude and noise of the outer shell can be effectively reduced, while ensuring the lightweight nature of the aircraft structure and improving the overall operational stability of the aircraft, thus guaranteeing structural safety.

[0022] Details of one or more embodiments of the present invention are set forth in the following drawings and description, so that other features, objects and advantages of the invention will be more readily understood. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other embodiments can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a schematic diagram of an anisotropic flange for realizing energy wave division, provided as an illustrative embodiment of the present invention.

[0025] Figure 2 This is a schematic diagram of the structure of an elastic wave control component provided in an illustrative embodiment of the present invention.

[0026] Figure 3 This is a schematic diagram of a microstructure unit provided in an illustrative embodiment of the present invention.

[0027] Figure 4 This is a schematic diagram of another anisotropic flange for realizing energy wave division, provided as an illustrative embodiment of the present invention.

[0028] Figure 5 The waveguide diagram of the test group flange is provided as an illustrative embodiment of the present invention.

[0029] Figure 6 The waveguide diagram of the control group flange is provided as an illustrative embodiment of the present invention.

[0030] Figure 7This is a comparison diagram of the maximum displacement of the outer ring under 4000Hz excitation, provided as an illustrative embodiment of the present invention.

[0031] Figure 8 This is a comparison diagram of the maximum displacement of the outer ring under 5000Hz excitation, provided as an illustrative embodiment of the present invention.

[0032] In the diagram: 1. Outer connecting ring; 2. Inner connecting ring; 3. Mounting hole; 4. Elastic wave control component array; 5. Elastic wave control component; 6. Microstructure unit; 7. Horizontal beam; 8. Vertical beam; 9. First-level microstructure component; 10. Second-level microstructure component; 11. Third-level microstructure component; 12. Fourth-level microstructure component; 13. Fifth-level microstructure component; 14. Radial connecting beam; 15. Circumferential connecting beam; 16. Diagonal support beam. Detailed Implementation

[0033] Embodiments of this embodiment will now be described in more detail with reference to the accompanying drawings. While some embodiments of this embodiment are shown in the drawings, it should be understood that this embodiment can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of this embodiment. It should be understood that the accompanying drawings and embodiments are for illustrative purposes only and are not intended to limit the scope of protection of this embodiment.

[0034] As key equipment for space exploration and operation, the noise generated by the engines of aerospace vehicles can have various adverse effects on the environment, equipment, and the vehicle's own structure. Effective control of engine vibration and noise can reduce damage to the vehicle's structure, improve operational stability, and ultimately enhance the overall performance of the aerospace vehicle.

[0035] Currently, vibration and noise reduction technologies for aerospace vehicle engines mainly include vibration isolation and damping, acoustic sound insulation, active control, and structural optimization.

[0036] Vibration isolation and damping technologies typically employ elastic materials such as rubber pads, metal springs, and vibration dampers to isolate sensitive equipment from the main structure of the spacecraft, reducing the transmission of mechanical vibrations. However, such systems increase the overall weight of the spacecraft, and damping materials may age over time and with environmental changes, affecting performance. Acoustic sound insulation technologies utilize high-density materials such as lead plates and multi-layered composite materials to shield noise, but their bulkiness also increases the weight and volume of the spacecraft, presenting space challenges for installation and wiring. Active control technologies use sensors and actuators to adjust sound waves in real time to cancel noise through noise cancellation methods, but their high complexity and system response delays limit their effectiveness when dealing with rapidly changing noise. Structural optimization uses finite element analysis to avoid resonant frequencies or uses lightweight, high-strength materials to reduce overall mass and improve vibration isolation. In summary, existing vibration reduction and noise reduction methods cannot achieve efficient control of engine noise and vibration while simultaneously considering the weight and volume of the spacecraft.

[0037] Figure 1 This is a schematic diagram of an anisotropic flange for realizing energy wave division, provided as an illustrative embodiment of the present invention.

[0038] Figure 2 This is a schematic diagram of the structure of an elastic wave control component provided in an illustrative embodiment of the present invention.

[0039] In this embodiment, the flange is used to connect the engine and motor of an aerospace vehicle. For example... Figure 1 and Figure 2 As shown, the flange includes a connecting ring and an elastic wave control component array 4.

[0040] Specifically, in this embodiment, the connecting ring includes an outer connecting ring 1 and an inner connecting ring 2. The outer connecting ring 1 is configured to connect to the engine housing, and the inner connecting ring 2 is configured to connect to the motor.

[0041] In practical applications, the outer connecting ring 1 and the inner connecting ring 2 are concentrically arranged. To facilitate the connection between the flange and the engine and motor, both the outer connecting ring 1 and the inner connecting ring 2 are provided with multiple mounting holes 3. Based on these mounting holes 3, the outer connecting ring 1 can be rigidly connected to the engine housing with screws, and the inner connecting ring 2 can be rigidly connected to the motor.

[0042] Multiple mounting holes 3 are evenly arranged along the circumference of the flange at a preset angle. For example, 6 mounting holes 3 can be provided on the outer connecting ring 1, and 12 mounting holes 3 can be provided on the inner connecting ring 2. The included angle between adjacent mounting holes 3 is 60°.

[0043] In this embodiment, the elastic wave control component array 4 is disposed between the inner connecting ring 2 and the outer connecting ring 1, and includes multiple elastic wave control components 5 connected end to end in sequence. In this embodiment, the elastic wave control components 5 are arranged end to end in sequence along the circumference of the flange.

[0044] The array structure of the elastic wave control component 5 enables elastic waves to propagate along a specific path within the flange structure, thereby allowing for flexible control of the transmission mode of the elastic waves and preventing vibrations and noise in traditional flange structures from being directly transmitted to the aircraft shell.

[0045] Specifically, each elastic wave control component 5 includes multiple layers of microstructure components arranged sequentially from the inner connecting ring 2 to the outer connecting ring 1. Each of the multiple microstructure components is provided with at least one microstructure unit 6. The microstructure unit 6 has anisotropic stiffness so that the flange has anisotropic stiffness, thereby allowing the elastic wave generated by the motor to be transmitted along the circumference of the flange.

[0046] In this embodiment, the multilayer microstructure component based on the stacked structure can effectively disperse and deflect the propagation path of elastic waves. The layered design of the microstructure component, by changing the geometric properties (e.g., structure, shape, size, etc.), can make the microstructures of different layers exhibit different stiffness characteristics in various directions, thereby achieving anisotropic stiffness.

[0047] Furthermore, each microstructure component includes at least one microstructure unit 6. Each microstructure unit 6 is designed with anisotropic stiffness, meaning it exhibits different elastic responses in different directions. By setting appropriate shapes, sizes, and materials for the microstructure units 6, the flange achieves higher stiffness in specific directions and lower stiffness in others, thereby directionally controlling the propagation path of elastic waves. This anisotropic stiffness design allows elastic waves generated by the motor to propagate circumferentially rather than radially along the flange, confining vibration energy within the flange and reducing the energy transmitted to the aircraft shell, ultimately lowering shell vibration and noise. Based on the above structure, the anisotropic flange for energy-distributed vibration provided in this embodiment of the invention can effectively control engine vibration and noise within a lightweight flange structure. Compared to traditional heavy vibration isolation materials, the microstructure-based flange does not significantly increase aircraft weight and does not require substantial internal space occupation. Therefore, this flange design can efficiently control the elastic waves generated by the engine while maintaining aircraft weight and volume.

[0048] In one optional embodiment, the number of microstructure units 6 corresponding to each multilayer microstructure component is different, and the number of microstructure units 6 corresponding to each multilayer microstructure component increases sequentially from the inner layer to the outer layer.

[0049] In this embodiment, by adjusting the number of microstructural units 6 in the microstructural component, a progressive distribution with distinct layers is achieved, resulting in a different number of microstructural units 6 in each layer. The inner layer has fewer microstructural units 6, which gradually increase towards the outer layers. This structure results in uneven distribution of structural stiffness between the inner and outer layers, thereby enhancing the anisotropic characteristics of the flange and contributing to the layer-by-layer attenuation or dispersion effect of elastic waves between different layers.

[0050] Specifically, the number of microstructural units increases progressively from the inner to the outer layer, meaning that the outer layer has greater stiffness and wave-bearing capacity. This allows the microstructural components at different levels to gradually absorb and guide the elastic wave energy as it propagates from the inner ring to the outer ring. By increasing the number of units layer by layer, the outer layer components provide a larger area and higher stiffness, enabling them to more effectively block or deflect wave energy transmitted to the outer ring, thereby preventing wave energy from being directly transmitted to the connection area between the engine and the motor.

[0051] The progressively increasing number of microstructural units (6) in each layer leads to a gradual increase in the difference in circumferential and radial stiffness among the microstructural components in each layer. This hierarchical variation in stiffness further enhances the anisotropy effect, enabling the flange to achieve different stiffness responses in different directions. The smaller number of microstructural units (6) in the inner layer helps to form a flexible connection, preventing the initial elastic wave energy from being completely reflected after entering the flange; as the wave energy propagates to the outer layers, the number of microstructural units increases layer by layer, and the stiffness increases accordingly, thereby achieving layer-by-layer blocking and dissipation of waves.

[0052] The number of microstructural units 6 increases layer by layer, causing the elastic wave to gradually deflect to the circumferential path of the flange during its outward propagation. Due to the guiding and dispersing effect of the microstructural components in each layer on the elastic wave, the energy of the elastic wave in the normal direction is gradually weakened and redirected circumferentially, thereby reducing the normal energy transmitted to the outer shell surface. In summary, based on the above structure, the elastic wave energy within the flange can be effectively controlled, further reducing the normal impact on the aircraft shell, thus reducing the probability of vibration being transmitted to the aircraft surface.

[0053] Furthermore, based on the structure of the aforementioned microstructure components, unnecessary materials and weight are reduced while maintaining structural stiffness and anisotropic fluctuation control capabilities. The progressively increasing number of microstructure units allows the flange to achieve a balance between local and global stiffness, satisfying the requirements for efficient vibration and noise reduction without increasing the flange's volume and weight, thus optimizing the overall structural efficiency of the spacecraft.

[0054] In summary, by employing an increasing number of microstructural units (6) in the multi-layered microstructural assembly, the anisotropic stiffness and elastic wave control capability of the flange are further enhanced. Through the hierarchical variation in the number of microstructural units (6), the elastic waves are effectively split and deflected layer by layer during propagation, achieving suppression of vibration energy on the outer shell surface while simultaneously ensuring the structure's lightweight and compact design.

[0055] Figure 3 This is a schematic diagram of a microstructure unit provided in an illustrative embodiment of the present invention.

[0056] In an alternative embodiment, such as Figure 3 As shown, the microstructure unit 6 is provided with a horizontal beam 7, and vertical beams 8 are connected to both ends of the horizontal beam 7. The vertical beams 8 are set perpendicular to the horizontal beam 7.

[0057] In this embodiment, the crossbeam 7 serves as the main component of the microstructure unit 6, providing horizontal support within the microstructure unit 6, while the vertical beam 8 is perpendicular to the crossbeam 7. This beam structure results in a significant difference in stiffness between the horizontal and vertical directions in the microstructure unit 6, effectively guiding and controlling the propagation characteristics of elastic waves in different directions.

[0058] The structure of the horizontal beam 7 and the vertical beam 8 creates an imbalance in the stiffness of the microstructural unit 6 in different directions, thereby enhancing its anisotropic stiffness characteristics. Specifically, the presence of the horizontal beam 7 gives the microstructural unit 6 higher stiffness in the horizontal (circumferential) direction, while the vertical beam 8 provides relatively lower stiffness in the vertical direction. This anisotropic stiffness design causes elastic waves to tend to propagate circumferentially rather than radially when transmitted to the microstructural unit 6, thus guiding and dispersing the wave energy and preventing energy from propagating directly radially to the outer shell.

[0059] Due to the stiffness difference between the crossbeam 7 and the vertical beam 8, the elastic wave is directionally restricted within the microstructural unit 6, tending to propagate along the direction of higher stiffness (the direction of the crossbeam 7). By consistently arranging the crossbeam 7 and vertical beam 8 in multiple microstructural units 6, the microstructural components throughout the flange can form a relatively stable circumferential propagation path, allowing the elastic wave to propagate circumferentially within the flange and reducing radial propagation. The structure of the crossbeam 7 and vertical beam 8 reduces the impact of the elastic wave on the normal direction of the aircraft's outer shell surface, helping to reduce the energy of vibration transmitted to the outer shell surface, thereby achieving vibration reduction and noise reduction effects.

[0060] The structural design of the horizontal beam 7 and the vertical beam 8 not only enhances the stiffness characteristics of the microstructural unit 6 but also simplifies its construction. This simplified structure reduces manufacturing difficulty and material costs while ensuring functionality and stability. Furthermore, the perpendicular connection between the horizontal beam 7 and the vertical beam 8 gives the microstructural unit 6 higher structural strength, enabling it to adapt to different stress conditions during flange operation and improving the overall fatigue resistance and durability of the flange.

[0061] Furthermore, the combination of the horizontal beam 7 and the vertical beam 8 achieves a lightweight design for the microstructure unit 6. Compared with traditional vibration reduction methods that use heavy vibration isolation materials or complex structures, this microstructure unit 6 controls the propagation path of elastic waves through a simple beam structure, effectively reducing the amount of material used and the weight burden on the flange. This allows the flange provided in this embodiment of the invention to maintain the overall lightweight and compactness of the spacecraft while reducing vibration and noise.

[0062] In summary, the design of the horizontal beam 7 and vertical beam 8 in the microstructural unit 6 enhances the anisotropic stiffness of the microstructural unit 6, achieving directional control of elastic waves. This not only improves the vibration reduction and noise reduction effect of the flange but also provides advantages in terms of lightweighting and structural simplification, thereby further enhancing the practical application value and manufacturing feasibility of the flange.

[0063] In an alternative embodiment, such as Figure 1 and Figure 2 As shown, the microstructure units 6 in the adjacent two layers of microstructure components are arranged alternately.

[0064] In this embodiment, by staggering the microstructure units 6 in adjacent layers of microstructure components, overlapping distribution of each layer of microstructure units 6 in the radial direction is avoided. This staggered design can effectively change the propagation path of elastic waves in the flange structure, causing the elastic waves to undergo more path dispersion and deflection between layers, thereby weakening their energy transfer.

[0065] The staggered arrangement of microstructural units 6 causes more structural interference to the elastic wave during its propagation, which helps to further dissipate the wave energy. In other words, the staggered arrangement of microstructural units 6 increases the complexity of the propagation path of the elastic wave between different layers, so that the wave energy is gradually reduced layer by layer as it is transmitted to the outer ring, thereby further reducing the normal impact of the wave energy transmitted to the aircraft shell.

[0066] The staggered arrangement of the structure not only improves energy dissipation but also enhances anisotropic stiffness, enabling the flange to better control the directional propagation of elastic waves. The microstructural units 6 of adjacent layers are not arranged in the same direction; this dispersed stiffness layout better guides the elastic waves to propagate circumferentially, effectively reducing normal energy.

[0067] In summary, the staggered arrangement of adjacent microstructural units 6 effectively enhances the energy dispersion and dissipation of elastic waves, further improving the vibration reduction and noise reduction capabilities of the flange while maintaining its lightweight structural characteristics.

[0068] Figure 4 This is a schematic diagram of another anisotropic flange for realizing energy wave division, provided as an illustrative embodiment of the present invention.

[0069] like Figure 3 and Figure 4 As shown, the flange in this embodiment is the same as the flange provided in the above embodiments, both of which are provided with a connecting ring and an elastic wave control component array 4. The flange material in this embodiment may include stainless steel, titanium alloy, magnesium alloy, aluminum alloy, carbon fiber, etc.

[0070] Unlike the above embodiments, the multilayer elastic wave control component 5 in this embodiment includes a first-level microstructure component 9, a second-level microstructure component 10, a third-level microstructure component 11, a fourth-level microstructure component 12, and a fifth-level microstructure component 13 arranged sequentially from the inner connecting ring 2 to the outer connecting ring 1.

[0071] In this embodiment, a five-layer elastic wave control assembly 5 is designed between the inner connecting ring 2 and the outer connecting ring 1, comprising a first-level microstructure assembly 9, a second-level microstructure assembly 10, a third-level microstructure assembly 11, a fourth-level microstructure assembly 12, and a fifth-level microstructure assembly 13. These microstructure assemblies are arranged in order from the inside out, with each layer consisting of microstructure units 6. Through this multi-level structure arranged layer by layer, the elastic wave is gradually controlled and dispersed between different layers. The multi-layer structure allows each layer of components to exert its specific stiffness characteristics, thereby more accurately guiding the propagation path of the elastic wave and achieving progressive attenuation and control, effectively preventing the wave energy from being radially transmitted to the outer shell.

[0072] Among them, the first-level microstructure component 9 is provided with one microstructure unit 6, the second-level microstructure component 10 is provided with two microstructure units 6, the third-level microstructure component 11 is provided with three microstructure units 6, the fourth-level microstructure component 12 is provided with four microstructure units 6, and the fifth-level microstructure component 13 is provided with five microstructure units 6.

[0073] The increasing number of units gives the outer layer components higher stiffness, thus more effectively blocking and deflecting elastic waves. The progressively increasing number of microstructure units makes the inner layer more elastic, facilitating the guidance of wave energy; the gradually increasing stiffness of the outer layer enhances the absorption and confinement of elastic waves, thereby optimizing the anisotropic stiffness characteristics of the flange and effectively achieving wave splitting and attenuation of vibration and noise.

[0074] In this embodiment, the diameter of the inner connecting ring 2 is one-third of the diameter of the outer connecting ring 1, and the length of the vertical beam 8 is one-third of the diameter of the inner connecting ring 2.

[0075] In an optional embodiment, the length of the vertical beam 8 of each microstructure unit 6 in the first-level microstructure component 9, second-level microstructure component 10, third-level microstructure component 11, fourth-level microstructure component 12, and fifth-level microstructure component 13 can be kept consistent. The length of the horizontal beam 7 of each microstructure unit 6 in the first-level microstructure component 9, second-level microstructure component 10, third-level microstructure component 11, fourth-level microstructure component 12, and fifth-level microstructure component 13 can be adjusted in detail according to actual usage needs, thereby allowing for adjustment of the lateral stiffness of the microstructure unit 6 within a wide range.

[0076] In an alternative embodiment, such as Figure 4 As shown, the elastic wave control component 5 is connected to the inner connecting ring 2 via a radial connecting beam 14. One end of the radial connecting beam 14 is connected to the microstructure unit 6 in the first-level microstructure component 9, and the other end is connected to the inner connecting ring 2. The elastic wave control component 5 is connected to the outer connecting ring 1 via the end of the microstructure unit 6 in the fifth-level microstructure component 13.

[0077] The radial connecting beam 14 makes the elastic wave control component 5 more robust in the radial direction. Specifically, the radial connecting beam 14 combines the structural strength of each layer of microstructure components with the inner and outer connecting rings 1, making the transmission path of the elastic wave in the flange more stable, effectively avoiding the disorderly diffusion of vibration and noise, and improving the wave splitting effect and control accuracy of the elastic wave.

[0078] Further optional, such as Figure 4 As shown, inclined support beams 16 are respectively provided on both sides of the radial connecting beam 14, and the two inclined support beams 16 are symmetrically arranged with respect to the radial connecting beam 14; one end of the inclined support beam 16 is fixedly connected to the middle part of the radial connecting beam 14, and the other end is fixedly connected to the inner connecting ring 2.

[0079] The diagonal support beams 16 are symmetrically distributed on both sides of the radial connecting beam 14, providing additional support and further enhancing the stiffness of the radial connecting beam 14. One end of the diagonal support beam 16 is connected to the middle of the radial connecting beam 14, and the other end is connected to the inner connecting ring 2. This support structure helps to balance and disperse stresses from different directions, thereby improving the stability of the flange in the radial connection.

[0080] Further optional, such as Figure 4As shown, at least one circumferential connecting beam 15 is provided between two adjacent elastic wave control components 5. The circumferential connecting beam 15 is provided on at least one layer of elastic wave control components 5 among the secondary microstructure component 10, the tertiary microstructure component 11, and the quaternary microstructure component 12. In this embodiment, it is taken as an example that circumferential connecting beams 15 are provided on the secondary microstructure component 10, the tertiary microstructure component 11, and the quaternary microstructure component 12.

[0081] Circumferential connecting beams 15 are arranged on at least one layer of the secondary, tertiary, and quaternary microstructure components 12 of the elastic wave control assembly 5, connecting adjacent elastic wave control assemblies 5 circumferentially. This connection method effectively enhances the circumferential structural stability of the flange, enabling the elastic wave to form a continuous propagation path among multiple microstructure components and reducing the disordered diffusion of wave energy.

[0082] By connecting the circumferential connecting beams 15, adjacent microstructure components can work together to form a more ordered wave guiding channel, which helps to guide the elastic wave circumferentially. This controlled transmission path design reduces the tendency of the wave to diffuse radially, thereby reducing the normal energy transmitted to the outside of the flange and improving the vibration reduction and noise reduction performance of the flange.

[0083] Furthermore, the circumferential connecting beam 15 not only enhances the structural stiffness between microstructure components but also improves the flange's circumferential resistance to disturbances. This allows the flange to maintain structural stability under varying environmental stresses, improving its overall durability and vibration control.

[0084] It should be noted that energy dispersion in this embodiment refers to the gradual reduction of energy density in the main propagation direction by dispersing the transmitted vibration energy in stages through specific design within the structure, thereby achieving noise reduction and vibration damping effects. For example, through a multi-stage structure, energy is dispersed between each stage, causing the energy of the vibration in the normal direction (perpendicular to the structure) to weaken step by step.

[0085] Specifically, in this embodiment, when an excitation is applied to the inner connecting ring 2 of the flange, the elastic wave is first transmitted to the radial connecting beam 14, causing the crossbeam 7 of the microstructure unit 6 of the first-level microstructure component 9 to bear more energy distribution. Subsequently, the energy continues to be transmitted sequentially to the second-level microstructure component 10. Due to the superposition of the in-phase waves transmitted from the previous level, the normal energy on the vertical beam 8 between the two microstructure units 6 of the second-level microstructure component 10 is more concentrated (wave crest), while the normal energy on both sides of the vertical beam 8 is significantly reduced after wave splitting dissipation, and more energy is dispersed to the crossbeam.

[0086] This step-by-step wave division design causes the normal energy transmitted to the vertical beam 8 at each stage to be gradually dissipated and dispersed, effectively weakening the energy along the transmission path. This wave division method ensures that the normal energy density of each stage is reduced, significantly reducing the vibration and noise ultimately transmitted to the outer ring, thereby achieving the purpose of vibration reduction and noise reduction.

[0087] The following detailed description, in conjunction with specific embodiments, illustrates an anisotropic flange for energy splitting provided by an embodiment of the present invention.

[0088] In this embodiment, the elastic wave control effect of the flange provided by the present invention is illustrated by setting up an experimental group and a control group. The experimental group consists of an anisotropic flange for energy splitting provided by the present invention, which includes an inner connecting ring, an outer connecting ring, and a multi-layer elastic wave control assembly disposed between the two. Each elastic wave control assembly includes a primary microstructure assembly, a secondary microstructure assembly, a tertiary microstructure assembly, a quaternary microstructure assembly, and a quinary microstructure assembly. The primary microstructure assembly has one microstructure unit, the secondary microstructure assembly has two microstructure units, the tertiary microstructure assembly has three microstructure units, the quaternary microstructure assembly has four microstructure units, and the quinary microstructure assembly has five microstructure units. Circumferential connecting beams are provided on the secondary, tertiary, and quaternary microstructure assemblies. The control group consists of a homogeneous material flange.

[0089] In practice, a transverse wave with an amplitude of 0.5 cm was applied to the inner ring of the flanges in both the experimental and control groups. The maximum displacement of the outer ring was recorded every 1000 Hz, from 1000 Hz to 10000 Hz. A low-reflection boundary was set on the outer ring to observe the effect of the microstructure on the propagation of the elastic wave. The waveguide diagram of the experimental group flange is shown below. Figure 5 As shown, the waveguide diagram of the control group flange is as follows. Figure 6 As shown.

[0090] Experimental results show that, compared to the homogeneous material flange of the control group, the flange in the experimental group containing microstructural units can effectively disperse energy within the structure, allowing vibration energy to propagate within the crossbeam in the circumferential direction. This wave-splitting design allows more energy to be dispersed in the opposite direction under 4000Hz excitation, while under 5000Hz excitation, more energy is dispersed to both sides of the flange. This result proves that the flange of the present invention can effectively dissipate energy within the structure, achieving wave-splitting and energy deflection, thereby significantly reducing vibration and noise transmitted to the aircraft shell and improving the overall stability of the aircraft. The comparison of the maximum displacement of the outer ring under 4000Hz excitation is shown in the figure below. Figure 7 As shown in the figure, the comparison diagram of the maximum displacement of the outer ring under 5000Hz excitation is as follows. Figure 8 As shown.

[0091] It should be noted that the term "comprising" and its variations used in the embodiments of the present invention are open-ended, meaning "including but not limited to". The term "based on" means "at least partially based on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments". The modifications of "one" and "multiple" mentioned in the embodiments of the present invention are illustrative and not restrictive. Those skilled in the art should understand that, unless explicitly indicated otherwise in the context, they should be understood as "one or more".

[0092] The user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, stored data, displayed data, etc.) involved in the embodiments of the present invention are all information and data authorized by the user or fully authorized by all parties. Furthermore, the collection, use and processing of the relevant data must comply with the relevant laws, regulations and standards of the relevant countries and regions, and corresponding operation entry points are provided for users to choose to authorize or refuse.

[0093] The steps described in the method embodiments provided by this invention can be performed in different orders and / or in parallel. Furthermore, the method embodiments may include additional steps and / or omit the steps shown. The scope of protection of this invention is not limited in this respect.

[0094] The term "embodiment" in this specification refers to a specific feature, structure, or characteristic described in connection with an embodiment that may be included in at least one embodiment of the invention. The appearance of this phrase in various places in the specification does not necessarily imply the same embodiment, nor does it imply independence or alternativeity from other embodiments. The various embodiments in this specification are described in a related manner, with reference to each other for similar or identical parts. In particular, for apparatus, device, and system embodiments, since they are substantially similar to method embodiments, the description is relatively simple, and relevant details are referred to in the description of the method embodiments.

[0095] The embodiments described above are merely illustrative of several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of patent protection. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the appended claims.

Claims

1. An anisotropic flange for achieving energy splitting, characterized in that, The flange is used to connect the engine and motor of an aerospace vehicle, and the flange includes: A connecting ring, including an outer connecting ring and an inner connecting ring, the outer connecting ring being configured to connect to the housing of the engine, and the inner connecting ring being configured to connect to the motor; An array of elastic wave control components is disposed between the inner connecting ring and the outer connecting ring, comprising multiple elastic wave control components connected end to end in sequence. The elastic wave control components are connected to the inner connecting ring through radial connecting beams, and at least one circumferential connecting beam is provided between two adjacent elastic wave control components. Each of the elastic wave control components includes multiple layers of microstructure components arranged sequentially from the inner connecting ring to the outer connecting ring. Each of the multiple layers of microstructure components has at least one microstructure unit. The microstructure unit has anisotropic stiffness, so that the flange has anisotropic stiffness, thereby allowing the elastic wave generated by the motor to be transmitted along the circumferential direction of the flange. The number of microstructure units corresponding to each of the multiple layers of microstructure components is different, and the number of microstructure units corresponding to each of the multiple layers of microstructure components increases sequentially from the inner layer to the outer layer. The microstructure unit is provided with a horizontal beam, and vertical beams are connected to both ends of the horizontal beam. The vertical beams are arranged perpendicular to the horizontal beams, and the microstructure units in adjacent layers of the microstructure assembly are arranged alternately.

2. The flange according to claim 1, characterized in that, The multilayer elastic wave control component includes a first-level microstructure component, a second-level microstructure component, a third-level microstructure component, a fourth-level microstructure component, and a fifth-level microstructure component arranged sequentially from the inner connecting ring to the outer connecting ring.

3. The flange according to claim 2, characterized in that, The first-level microstructure component has one microstructure unit, the second-level microstructure component has two microstructure units, the third-level microstructure component has three microstructure units, the fourth-level microstructure component has four microstructure units, and the fifth-level microstructure component has five microstructure units.

4. The flange according to claim 2, characterized in that, One end of the radial connecting beam is connected to the microstructure unit in the primary microstructure assembly, and the other end is connected to the inner connecting ring; The elastic wave control component is connected to the outer connecting ring through the end of the microstructure unit of the five-level microstructure component.

5. The flange according to claim 4, characterized in that, An inclined support beam is provided on each side of the radial connecting beam, and the two inclined support beams are symmetrically arranged with respect to the radial connecting beam. One end of the inclined support beam is fixedly connected to the middle of the radial connecting beam, and the other end is fixedly connected to the inner connecting ring.

6. The flange according to claim 2, characterized in that, The circumferential connecting beam is disposed on at least one layer of the elastic wave control component among the secondary microstructure component, the tertiary microstructure component, and the quaternary microstructure component.

7. The flange according to claim 1, characterized in that, The diameter of the inner connecting ring is one-third of the diameter of the outer connecting ring, and the length of the vertical beam is one-third of the diameter of the inner connecting ring.

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