Anisotropic flange for realizing energy wave division

Abstract

The invention relates to an anisotropic flange for realizing energy wave division, the flange is used for connecting an engine and a motor of an aerospace craft, the flange comprises a connecting ring, the connecting ring comprises an outer connecting ring and an inner connecting ring, the outer connecting ring is configured to be connected with a shell of the engine, and the inner connecting ring is configured to be connected with the motor; the elastic wave regulation and control assembly array is arranged between the inner connecting ring and the outer connecting ring and comprises a plurality of elastic wave regulation and control assemblies which are sequentially connected end to end; wherein each elastic wave regulation and control assembly comprises multiple layers of microstructure assemblies which are sequentially arranged from an inner connecting ring to an outer connecting ring, and the multiple layers of microstructure assemblies are each provided with at least one microstructure unit; the microstructure units have anisotropic rigidity, so that the flange has anisotropic rigidity, and elastic waves generated by the motor are transmitted in the circumferential direction of the flange.

Description

Technical Field

[0001] The present application relates to the field of flange technology, and in particular to an anisotropic flange for realizing energy wave splitting. Background Art

[0002] Aerospace vehicles are important equipment for space exploration and operation. The noise generated by their engines during operation will have varying degrees of impact on the environment, equipment, and aircraft structure. By effectively controlling the vibration and noise of aircraft engines, it is possible to reduce damage to the aircraft structure, improve its operational stability, and thus improve overall performance.

[0003] At present, the vibration and noise reduction technologies for aerospace aircraft engines mainly include vibration isolation and damping, acoustic sound insulation, active control and other aspects. However, the above-mentioned vibration isolation, damping and acoustic sound insulation methods will increase the weight and volume of the aircraft, while the active control method will be difficult to cope with rapidly changing noise and vibration due to its limited system complexity and response speed. In summary, the existing vibration and noise reduction methods cannot achieve efficient control of engine noise and vibration while taking into account the weight and volume of the aircraft. Summary of the invention

[0004] An anisotropic flange for achieving energy wave splitting provided in an embodiment of the present invention at least solves the problem in the related art 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 wave splitting is provided, wherein the flange is used to connect an engine and a motor of an aerospace vehicle, and the flange comprises:

[0006] A connecting ring, comprising an outer connecting ring and an inner connecting ring, wherein the outer connecting ring is configured to be connected to a housing of the engine, and the inner connecting ring is configured to be connected to the motor;

[0007] An elastic wave control component array is arranged between the inner connecting ring and the outer connecting ring, and includes a plurality of elastic wave control components connected end to end in sequence;

[0008] Among them, each of the elastic wave regulation components includes multiple layers of microstructure components arranged in sequence from the inner connecting ring to the outer connecting ring, and 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, so that the elastic wave generated by the motor is transmitted along the circumferential direction of the flange.

[0009] Optionally, 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 from the inner layer to the outer layer.

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

[0011] Optionally, the microstructure units in two adjacent layers of the microstructure components are arranged in a staggered manner.

[0012] Optionally, the multi-layer elastic wave regulation component includes a primary microstructure component, a secondary microstructure component, a tertiary microstructure component, a quaternary microstructure component and a quintuple microstructure component arranged in sequence from the inner connecting ring to the outer connecting ring.

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

[0014] Optionally, the elastic wave regulation 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 regulating component is connected to the outer connecting ring through the end of the microstructure unit of the five-level microstructure component.

[0016] Optionally, oblique support beams are respectively arranged on both sides of the radial connection beam, and the two oblique support beams are symmetrically arranged relative to the radial connection beam;

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

[0018] Optionally, at least one circumferential connecting beam is arranged between two adjacent elastic wave regulation components, and the circumferential connecting beam is arranged on at least one layer of the elastic wave regulation 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 realizing energy wave separation provided by the embodiment of the present invention can realize efficient control of engine noise and vibration while taking into account the weight and volume of the aircraft. Specifically, by arranging multiple layers of microstructure components containing microstructure units with anisotropic stiffness between the inner connecting ring and the outer connecting ring of the flange, the flange has anisotropic stiffness characteristics, which changes the propagation path and mode of the elastic wave. Since the stiffness of the microstructure units varies in different directions, the elastic wave is regulated when propagating along the circumference of the flange, causing part of the wave energy to be deflected or dispersed, thereby reducing the energy transfer of the elastic wave in the normal direction of the outer shell surface. Based on the above structure, the vibration amplitude and noise of the outer shell can be effectively reduced, while ensuring the lightness of the aircraft structure and improving the overall operating stability of the aircraft, thereby ensuring structural safety.

[0022] The details of one or more embodiments of the invention are set forth in the following drawings and description so that other features, objects, and advantages of the invention are more readily apparent. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the prior art descriptions. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other embodiments can be obtained based on these drawings without creative work.

[0024] Figure 1 A schematic structural diagram of an anisotropic flange for realizing energy wave splitting provided in an illustrative embodiment of the present invention.

[0025] Figure 2 A schematic structural diagram of an elastic wave control component provided in accordance with an exemplary embodiment of the present invention.

[0026] Figure 3 A schematic structural diagram of a microstructure unit provided for an exemplary embodiment of the present invention.

[0027] Figure 4 A schematic structural diagram of another anisotropic flange for achieving energy wave splitting provided in an illustrative embodiment of the present invention.

[0028] Figure 5 Waveguide diagram of a test set flange provided for an illustrative embodiment of the present invention.

[0029] Figure 6 Waveguide diagram of a control group flange provided for an illustrative embodiment of the present invention.

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

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

[0032] In the figure: 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. primary microstructure component; 10. secondary microstructure component; 11. tertiary microstructure component; 12. quaternary microstructure component; 13. fifth microstructure component; 14. radial connecting beam; 15. circumferential connecting beam; 16. oblique support beam. DETAILED DESCRIPTION

[0033] Embodiments of the present embodiment will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present embodiment are shown in the accompanying drawings, it should be understood that the present embodiment can be implemented in various forms and should not be construed as being limited to the embodiments set forth herein, which are instead provided for a more thorough and complete understanding of the present embodiment. It should be understood that the drawings and embodiments of the present embodiment are only for exemplary purposes and are not intended to limit the scope of protection of the present embodiment.

[0034] Aerospace vehicles are key equipment for space exploration and operation. The noise generated by their engines during operation will have many adverse effects on the environment, equipment and the structure of the aircraft itself. If the vibration and noise of the aircraft engine can be effectively controlled, the damage to the aircraft structure can be reduced, the stability of its operation can be improved, and the overall performance of the aerospace vehicle can be further improved.

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

[0036] Vibration isolation and damping technology usually uses elastic materials such as rubber pads, metal springs and shock absorbers to isolate sensitive equipment from the main structure of the spacecraft to reduce the transmission of mechanical vibrations, but such systems increase the overall weight of the spacecraft, and the damping materials may age over time and environmental changes, affecting performance. Acoustic sound insulation technology uses high-density materials such as lead plates and multi-layer composite materials to shield noise, but their heavy characteristics also increase the weight and volume of the spacecraft, and face space challenges in installation and wiring. Active control technology uses sensors and actuators to adjust sound waves in real time to offset noise through noise elimination, but its high complexity and system response delay have limitations when facing rapidly changing noise. Structural optimization uses finite element analysis to avoid resonant frequencies, or uses lightweight and high-strength materials to reduce the overall mass and improve vibration isolation. In summary, the existing vibration reduction and noise reduction methods cannot achieve efficient control of engine noise and vibration while taking into account the weight and volume of the aircraft.

[0037] Figure 1 A schematic structural diagram of an anisotropic flange for realizing energy wave splitting provided in an illustrative embodiment of the present invention.

[0038] Figure 2 A schematic structural diagram of an elastic wave control component provided in accordance with an exemplary embodiment of the present invention.

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

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

[0041] In actual 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 the motor, multiple mounting holes 3 are arranged on the outer connecting ring 1 and the inner connecting ring 2. Based on the mounting holes 3, the outer connecting ring 1 can be rigidly connected to the engine housing and the inner connecting ring 2 can be rigidly connected to the motor by screws.

[0042] The plurality of mounting holes 3 are evenly arranged at a preset angle along the circumference of the flange. For example, six mounting holes 3 may be arranged on the outer connecting ring 1, and twelve mounting holes 3 may be arranged on the inner connecting ring 2. The angle between adjacent mounting holes 3 is 60°.

[0043] The elastic wave control component array 4 in this embodiment is arranged between the inner connection ring 2 and the outer connection ring 1, and includes a plurality of elastic wave control components 5 connected end to end. The elastic wave control components 5 in this embodiment are connected end to end along the circumference of the flange.

[0044] The array structure of the elastic wave control component 5 enables the elastic wave to propagate along a specific path in the flange structure, thereby flexibly controlling the transmission mode of the elastic wave and preventing the vibration and noise in the traditional flange structure from being directly transmitted to the aircraft shell.

[0045] Specifically, each elastic wave regulation component 5 includes multiple layers of microstructure components arranged in sequence from the inner connecting ring 2 to the outer connecting ring 1, and each of the multiple layers of 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, so that the elastic waves generated by the motor are transmitted along the circumferential direction of the flange.

[0046] In this embodiment, based on the multi-layer microstructure component of the stacked structure, each layer of the microstructure component can effectively disperse and deflect the transmission path of the elastic wave. The layered design of the microstructure component can make the microstructures of different layers show different stiffness characteristics in various directions by changing the geometric characteristics (such as structure, shape, size, etc.), thereby achieving anisotropic stiffness.

[0047] Furthermore, each layer of microstructure components includes at least one microstructure unit 6. Each microstructure unit 6 is designed with anisotropic stiffness, that is, the microstructure unit 6 has different elastic responses in different directions. By setting the reasonable shape, size and material of the microstructure unit 6, the stiffness of the flange in a specific direction is higher, while the stiffness in other directions is lower, so as to directionally control the propagation path of the elastic wave. This anisotropic stiffness design enables the elastic wave generated by the motor to be transmitted along the circumference of the flange rather than radially, and controls the vibration energy inside the flange, thereby reducing the energy transmitted to the outer shell of the aircraft, and finally reducing the vibration and noise of the outer shell. Based on the above structure, the anisotropic flange for realizing energy wave splitting provided by the embodiment of the present invention can effectively control the vibration and noise of the engine in a lightweight flange structure. Compared with traditional heavy vibration isolation materials, the flange based on the microstructure will not significantly increase the weight of the aircraft, and there is no need to occupy a large amount of internal space. Therefore, the flange design can efficiently regulate the elastic waves generated by the engine while maintaining the weight and volume of the aircraft.

[0048] In an optional embodiment, the number of microstructure units 6 corresponding to each of the multi-layer microstructure components is different, and the number of microstructure units 6 corresponding to each of the multi-layer microstructure components increases from the inner layer to the outer layer.

[0049] In this embodiment, by adjusting the number of microstructure units 6 of the microstructure assembly, the number of microstructure units 6 in each layer is different, and a clear-cut progressive distribution is achieved. Among them, the number of microstructure units 6 in the inner layer is relatively small, and gradually increases toward the outer layer. The above structure makes the structural stiffness of the inner and outer layers unevenly distributed, thereby enhancing the anisotropic properties of the flange, which helps the elastic wave to produce a layer-by-layer attenuation or dispersion effect between different layers.

[0050] Specifically, the number of microstructure units 6 increases from the inner layer to the outer layer, which means that the outer layer has stronger stiffness and wave bearing capacity, so that when the elastic wave propagates from the inner ring to the outer ring, the microstructure components at different levels can gradually absorb and guide the elastic wave energy. By increasing the number of units layer by layer, the outer layer components provide a larger area and higher stiffness in the structure, which can more effectively block or deflect the wave energy transmitted to the outer ring, thereby preventing the wave energy from being directly transmitted to the connection area between the engine and the motor.

[0051] The increasing number of microstructure units 6 layer by layer makes the difference in circumferential stiffness and radial stiffness of each layer of microstructure components gradually increase. This hierarchical change in stiffness further enhances the anisotropy effect, enabling the flange to achieve different stiffness responses in different directions. The fewer microstructure units 6 in the inner layer help to form a flexible connection, so that the initial elastic wave energy is not completely reflected after entering the flange; and as the wave energy propagates to the outer layer, the number of microstructures increases layer by layer, and the stiffness increases accordingly, thereby achieving layer-by-layer blocking and dissipation of the wave.

[0052] The number of microstructure units 6 increases layer by layer, so that the elastic wave is gradually deflected to the circumferential path of the flange during the outward propagation process. Due to the guiding and dispersing effect of the microstructure components of each layer on the elastic wave, the energy of the elastic wave in the normal direction is gradually weakened and turned to the circumferential direction, thereby reducing the normal energy transmitted to the shell surface. In summary, based on the above structure, the elastic wave energy in the flange can be effectively controlled, and the normal impact on the aircraft shell can be further reduced, thereby reducing the probability of vibration transmission to the aircraft surface.

[0053] In addition, based on the structure of the above-mentioned microstructure components, unnecessary materials and weight are reduced while maintaining structural stiffness and anisotropic fluctuation control capabilities. Due to the gradual increase in the number of microstructure units 6, the flange can achieve a balance between local stiffness and global stiffness, which not only meets the needs of efficient vibration reduction and noise reduction, but also does not increase the volume and weight of the flange, thereby optimizing the overall structural efficiency of the spacecraft.

[0054] In summary, the anisotropic stiffness and elastic wave control capability of the flange are further enhanced by designing an increasing number of microstructure units 6 in the multi-layer microstructure assembly. Through the hierarchical change of the number of microstructure units 6, the elastic wave is effectively divided and deflected layer by layer during the propagation process, achieving the suppression of the vibration energy on the shell surface while taking into account the lightweight and compactness of the structure.

[0055] Figure 3 A schematic structural diagram of a microstructure unit provided for an exemplary embodiment of the present invention.

[0056] In an alternative embodiment, if Figure 3 As shown, the microstructure unit 6 is provided with a cross beam 7 , both ends of the cross beam 7 are respectively connected with vertical beams 8 , and the vertical beams 8 are arranged perpendicular to the cross beam 7 .

[0057] In this embodiment, the cross beam 7 is the main component of the microstructure unit 6, providing support in the horizontal direction inside the microstructure unit 6, while the vertical beam 8 is perpendicular to the cross beam 7. This beam structure makes the microstructure unit 6 have a significant difference in stiffness in the horizontal and vertical directions, and can effectively guide and control the propagation characteristics of elastic waves in different directions.

[0058] The structure of the horizontal beam 7 and the vertical beam 8 makes the stiffness of the microstructure unit 6 in different directions uneven, thereby enhancing the anisotropic stiffness characteristics of the microstructure unit 6. Specifically, the presence of the horizontal beam 7 makes the microstructure unit 6 have a higher stiffness in the horizontal (circumferential) direction, while the vertical stiffness provided by the vertical beam 8 is relatively low. This anisotropic stiffness design makes the elastic wave more inclined to propagate in the circumferential direction rather than in the radial direction when it is transmitted to the microstructure unit 6, thereby achieving the guidance and wave division of the wave energy and preventing the energy from directly propagating in the radial direction to the shell.

[0059] Due to the difference in stiffness between the cross beam 7 and the vertical beam 8, the elastic wave is directionally restricted in the microstructure unit 6 and tends to propagate in the direction of higher stiffness (the direction of the cross beam 7). By consistently setting the cross beam 7 and the vertical beam 8 in multiple microstructure units 6, the microstructure components in the entire flange can form a relatively stable circumferential propagation path, so that the elastic wave is transmitted in the circumferential direction inside the flange, reducing radial transmission. The structure of the cross beam 7 and the vertical beam 8 can reduce the impact of the elastic wave on the normal direction of the aircraft shell surface, which helps to reduce the energy transmitted from the vibration to the shell surface, thereby achieving the effect of reducing vibration and noise.

[0060] The structural design of the horizontal beam 7 and the vertical beam 8 not only improves the rigidity characteristics of the microstructure unit 6, but also relatively simplifies the structure of the microstructure unit 6. This simplified structure can reduce the manufacturing difficulty and material cost while ensuring functionality and stability. In addition, the vertical connection between the horizontal beam 7 and the vertical beam 8 enables the microstructure unit 6 to have a higher structural strength, which can adapt to different stress conditions of the flange during operation and improve the overall fatigue resistance and durability of the flange.

[0061] In addition, the combination of the horizontal beam 7 and the vertical beam 8 realizes the lightweight design of the microstructure unit 6. Compared with the traditional vibration reduction method using heavy vibration isolation materials or complex structures, the microstructure unit 6 controls the propagation path of the elastic wave through a simple beam structure, effectively reducing the amount of material used and the weight burden of the flange, so that the flange provided in the embodiment of the present invention can reduce vibration and noise while still maintaining the overall lightweight and compactness of the spacecraft.

[0062] In summary, the design of the cross beam 7 and the vertical beam 8 in the microstructure unit 6 enhances the anisotropic stiffness of the microstructure unit 6 and realizes the directional control of the elastic wave. This not only improves the vibration and noise reduction effect of the flange, but also provides advantages in terms of lightweight and structural simplification, thereby further improving the practical application value and manufacturing feasibility of the flange.

[0063] In an alternative embodiment, if Figure 1 and Figure 2 As shown, the microstructure units 6 in two adjacent layers of microstructure components are arranged in a staggered manner.

[0064] In this embodiment, the microstructure units 6 in two adjacent layers of microstructure components are staggered to avoid overlapping distribution of the microstructure units 6 in each layer in the radial direction. This staggered design can effectively change the propagation path of the elastic wave in the flange structure, so that the elastic wave is dispersed and deflected more times between layers, thereby weakening its energy transfer.

[0065] The staggered arrangement of the microstructure units 6 causes the elastic wave to be disturbed by more structures during the transmission process, which helps to further dissipate the wave energy. In other words, the staggered arrangement of the microstructure units 6 increases the complexity of the propagation path of the elastic wave between the layers, so that the wave energy is reduced layer by layer during the process of being transmitted to the outer ring, thereby further reducing the normal impact of the wave energy transmitted to the outer shell of the aircraft.

[0066] The staggered structure not only improves the energy dissipation effect, but also further enhances the anisotropic stiffness, enabling the flange to better control the directional propagation of elastic waves. The microstructure units 6 of adjacent layers are not arranged in the same direction. This dispersed stiffness layout can better guide the elastic wave to propagate in the circumferential direction and effectively reduce the normal energy.

[0067] In summary, the staggered arrangement of the adjacent layer microstructure units 6 effectively enhances the energy dispersion and dissipation effect of the elastic wave, further improves the vibration and noise reduction capabilities of the flange, and at the same time maintains the lightweight structural characteristics.

[0068] Figure 4 A schematic structural diagram of another anisotropic flange for achieving energy wave splitting provided in 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 embodiment, and both are provided with a connecting ring and an elastic wave control component array 4. Among them, the material of the flange in this embodiment can include stainless steel, titanium alloy, magnesium alloy, aluminum alloy, carbon fiber, etc.

[0070] Different from the above-mentioned embodiments, the multilayer elastic wave control component 5 in this embodiment includes a primary microstructure component 9, a secondary microstructure component 10, a tertiary microstructure component 11, a fourth microstructure component 12 and a fifth microstructure component 13 arranged in sequence from the inner connecting ring 2 to the outer connecting ring 1.

[0071] In this embodiment, a five-layer elastic wave control component 5 is designed between the inner connecting ring 2 and the outer connecting ring 1, including a primary microstructure component 9, a secondary microstructure component 10, a tertiary microstructure component 11, a quaternary microstructure component 12 and a quintuple microstructure component 13. These microstructure components are arranged in order from the inside to the outside, and each layer of components is composed of microstructure units 6. Through this layer-by-layer multi-level structure, the elastic wave is gradually regulated and dispersed between different layers. The multi-layer structure enables the components of each layer to exert their own specific stiffness characteristics, thereby more accurately guiding the propagation path of the elastic wave, and realizing step-by-step 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 makes the outer layer components have higher rigidity, thus more effectively blocking and deflecting elastic waves. The gradually increasing number of microstructure units 6 makes the inner layer more elastic, which is convenient for guiding wave energy into; the outer layer rigidity is gradually increased, which enhances the absorption and restriction of elastic waves, thereby optimizing the anisotropic rigidity characteristics of the flange and effectively realizing the separation 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 primary microstructure assembly 9, the secondary microstructure assembly 10, the tertiary microstructure assembly 11, the quaternary microstructure assembly 12, and the quintuple microstructure assembly 13 can be kept consistent. The length of the crossbeam 7 of each microstructure unit 6 in the primary microstructure assembly 9, the secondary microstructure assembly 10, the tertiary microstructure assembly 11, the quaternary microstructure assembly 12, and the quintuple microstructure assembly 13 can be adjusted in detail according to actual use needs, thereby adjusting the lateral stiffness of the microstructure unit 6 in a wide range.

[0076] In an alternative embodiment, if Figure 4 As shown, the elastic wave regulation component 5 is connected to the inner connection ring 2 via a radial connection beam 14, wherein one end of the radial connection 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 connection ring 2. The elastic wave regulation component 5 is connected to the outer connection ring 1 via the end of the microstructure unit 6 of the fifth-level microstructure component 13.

[0077] The elastic wave control component 5 can be made more secure in the radial direction based on the radial connection beam 14. Specifically, through the radial connection beam 14, the structural strength of each layer of microstructure components and the inner and outer connection rings 1 are combined, so that the transmission path of the elastic wave in the flange is more stable, the disordered diffusion of vibration and noise is effectively avoided, and the wave separation effect and control accuracy of the elastic wave are improved.

[0078] Further optionally, if Figure 4 As shown, oblique support beams 16 are respectively arranged on both sides of the radial connecting beam 14, and the two oblique support beams 16 are symmetrically arranged relative to the radial connecting beam 14; one end of the oblique 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 oblique support beams 16 are symmetrically distributed on both sides of the radial connection beam 14, which can provide additional support and further improve the rigidity of the radial connection beam 14. One end of the oblique support beam 16 is connected to the middle of the radial connection beam 14, and the other end is connected to the inner connection 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 optionally, if Figure 4As shown, at least one circumferential connecting beam 15 is provided between two adjacent elastic wave regulating components 5, and the circumferential connecting beam 15 is provided on at least one layer of the elastic wave regulating components 5 among the secondary microstructure component 10, the tertiary microstructure component 11 and the quaternary microstructure component 12. In this embodiment, the circumferential connecting beam 15 is provided on the secondary microstructure component 10, the tertiary microstructure component 11 and the quaternary microstructure component 12 as an example.

[0081] The circumferential connecting beam 15 is arranged on at least one layer of the secondary, tertiary and quaternary microstructure components 12 of the elastic wave regulation component 5, and connects adjacent elastic wave regulation components 5 in the circumferential direction. This connection method effectively enhances the structural stability of the flange in the circumferential direction, enables the elastic wave to form a continuous propagation path between multiple microstructure components, and reduces the disordered diffusion of wave energy.

[0082] Through the connection of the circumferential connecting beam 15, the adjacent microstructure components can work together to form a more orderly wave guiding channel, which helps to guide the elastic wave along the circumferential direction. This control design of the transmission path 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 and noise reduction performance of the flange.

[0083] In addition, the circumferential connecting beam 15 not only enhances the structural rigidity between the microstructure components, but also improves the anti-interference ability of the flange in the circumferential direction. In this way, the flange can maintain structural stability under different environmental stresses, thereby improving the overall durability and vibration control effect of the flange.

[0084] It should be noted that the energy wave splitting in this embodiment refers to dispersing the transmitted vibration energy step by step in the structure through a specific design, thereby gradually reducing the energy density in the main propagation direction to achieve the effect of noise reduction and vibration reduction. For example, through a multi-level structure, the energy is dispersed between each level of the structure, so that the energy of the vibration in the normal direction (perpendicular to the structure) is gradually weakened.

[0085] Specifically, in this embodiment, when excitation is applied to the inner connecting ring 2 of the flange, the elastic wave is first transmitted to the radial connecting beam 14, so that the cross beam 7 of the microstructure unit 6 of the primary microstructure component 9 bears more energy distribution. Subsequently, the energy continues to be transmitted to the secondary microstructure component 10 in sequence. Due to the superposition of the same-phase waves transmitted in the previous stage, the normal energy on the vertical beam 8 between the two microstructure units 6 of the secondary microstructure component 10 is more concentrated (wave crest), and after the vertical beams 8 on both sides are dissipated by wave splitting, the normal energy is significantly reduced, and more energy is dispersed to the cross beam.

[0086] The step-by-step wave splitting design results in the gradual dissipation and dispersion of the normal energy of the vertical beam 8 transmitted to each level, and the energy is effectively weakened in the transmission path. This wave splitting method ensures that the normal energy density of each level is reduced, so that the vibration and noise finally transmitted to the outer ring are significantly reduced, thereby achieving the purpose of vibration reduction and noise reduction.

[0087] The following describes in detail an anisotropic flange for realizing energy wave separation provided by an embodiment of the present invention in conjunction with specific embodiments.

[0088] In this embodiment, the elastic wave regulation effect of the flange provided by the embodiment of the present invention is described by setting up an experimental group and a control group. Among them, the experimental group is an anisotropic flange for realizing energy wave separation provided by the embodiment of the present invention, and the flange includes an inner connecting ring, an outer connecting ring, and a multilayer elastic wave regulation component arranged therebetween. Each elastic wave regulation component includes a primary microstructure component, a secondary microstructure component, a tertiary microstructure component, a quaternary microstructure component, and a quintuple microstructure component, wherein the primary microstructure component is provided with one microstructure unit, the secondary microstructure component is provided with two microstructure units, the tertiary microstructure component is provided with three microstructure units, the quaternary microstructure component is provided with four microstructure units, and the quintuple microstructure component is provided with five microstructure units. Circumferential connecting beams are provided on the secondary microstructure component, the tertiary microstructure component, and the quaternary microstructure component. The control group is a flange of homogeneous material.

[0089] In the specific implementation, a shear wave excitation with an amplitude of 0.5 cm was applied to the inner ring of the flange of the test group and the control group, from 1000 Hz to 10000 Hz, and the maximum displacement of the outer ring was recorded every 1000 Hz. A low-reflection boundary was set on the outer ring to observe the effect of the microstructure on the propagation of elastic waves. Among them, the waveguide diagram of the flange of the test group is shown in Figure 5 As shown, the waveguide diagram of the control group flange is as follows Figure 6 shown.

[0090] The experimental results show that compared with the homogeneous material flange of the control group, the flange of the test group containing microstructure units can effectively disperse energy inside the structure, so that the vibration energy is transmitted in the beam in the circumferential direction. This wave-splitting design allows the energy to be dispersed more in the opposite direction under 4000Hz excitation, while the energy is dispersed more to both sides of the flange under 5000Hz excitation. This result proves that the flange of the present invention can effectively dissipate the energy inside the structure, realize wave splitting and energy deflection, thereby significantly reducing the vibration and noise transmitted to the aircraft shell and improving the overall stability of the aircraft. Among them, the comparison diagram 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 maximum displacement comparison of the outer ring under 5000Hz excitation is as follows Figure 8 shown.

[0091] It should be noted that the term "including" and its variations used in the embodiments of the present invention are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other 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 rather than restrictive. Those skilled in the art should understand that unless the context clearly indicates otherwise, it 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, and the collection, use and processing of relevant data must comply with relevant laws, regulations and standards of relevant countries and regions, and provide corresponding operation entrances for users to choose to authorize or refuse.

[0093] The various steps described in the method implementation methods provided in the embodiments of the present invention may be performed in different orders and / or in parallel. In addition, the method implementation methods may include additional steps and / or omit the steps shown. The scope of protection of the present invention is not limited in this respect.

[0094] The term "embodiment" in this specification refers to specific features, structures or characteristics described in conjunction with the embodiment that can be included in at least one embodiment of the present invention. The appearance of this phrase in various places in the specification does not necessarily mean the same embodiment, nor does it mean that it is mutually exclusive with other embodiments and is independent or optional. The various embodiments in this specification are described in a related manner, and the same or similar parts between the various embodiments refer to each other. In particular, for the device, equipment, and system embodiments, since they are basically similar to the method embodiments, the description is relatively simple, and the relevant parts refer to the partial description of the method embodiment.

[0095] The above-mentioned embodiments only express several implementation methods of the present invention, and the description thereof is relatively specific and detailed, but it cannot be understood as limiting the scope of patent protection. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present invention, and these all belong to the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be subject to the attached claims.

Claims

1. An anisotropic flange for realizing energy wave splitting, characterized in that: The flange is used to connect the engine and the motor of an aerospace vehicle, and the flange comprises: A connecting ring, comprising an outer connecting ring and an inner connecting ring, wherein the outer connecting ring is configured to be connected to a housing of the engine, and the inner connecting ring is configured to be connected to the motor; An elastic wave control component array is arranged between the inner connecting ring and the outer connecting ring, and includes a plurality of elastic wave control components connected end to end in sequence; Among them, each of the elastic wave regulation components includes multiple layers of microstructure components arranged in sequence from the inner connecting ring to the outer connecting ring, and 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, so that the elastic wave generated by the motor is transmitted along the circumferential direction of the flange.

2. The flange according to claim 1, characterized in that: 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 from the inner layer to the outer layer.

3. The flange according to claim 1, characterized in that: The microstructure unit is provided with a crossbeam, both ends of the crossbeam are respectively connected with vertical beams, and the vertical beams are arranged perpendicular to the crossbeam.

4. The flange according to claim 1, characterized in that: The microstructure units in two adjacent layers of the microstructure components are arranged in a staggered manner.

5. The flange according to claim 1, characterized in that: The multi-layer elastic wave regulation component includes a primary microstructure component, a secondary microstructure component, a tertiary microstructure component, a quaternary microstructure component and a quintuple microstructure component which are arranged in sequence from the inner connecting ring to the outer connecting ring.

6. The flange according to claim 5, characterized in that: The first-level microstructure component is provided with one microstructure unit, the second-level microstructure component is provided with two microstructure units, the third-level microstructure component is provided with three microstructure units, the fourth-level microstructure component is provided with four microstructure units, and the fifth-level microstructure component is provided with five microstructure units.

7. The flange according to claim 5, characterized in that: The elastic wave regulation component is connected to the inner connection ring through a radial connection beam, wherein one end of the radial connection beam is connected to the microstructure unit in the primary microstructure component, and the other end is connected to the inner connection ring; The elastic wave regulating component is connected to the outer connecting ring through the end of the microstructure unit of the five-level microstructure component.

8. The flange according to claim 7, characterized in that: Oblique support beams are respectively arranged on both sides of the radial connection beam, and the two oblique support beams are symmetrically arranged relative to the radial connection beam; One end of the oblique support beam is fixedly connected to the middle portion of the radial connection beam, and the other end is fixedly connected to the inner connection ring.

9. The flange according to claim 4, characterized in that: At least one circumferential connecting beam is arranged between two adjacent elastic wave regulating components, and the circumferential connecting beam is arranged on at least one layer of the elastic wave regulating components among the secondary microstructure component, the tertiary microstructure component and the quaternary microstructure component.

10. The flange according to claim 5, 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.

Images