Rudder blade flutter suppression device based on particle damping, suppression method thereof and aircraft

Abstract

The present invention discloses a rudder blade flutter suppression device based on particle damping, comprising a plurality of particle dampers, wherein the particle damper comprises a damper housing and a plurality of damping particles, wherein a plurality of cavities are arranged inside the damper housing, and the damping particles are filled in the cavities; wherein a receiving groove is arranged inside the rudder blade, and the damper housing is installed in the rudder blade receiving groove, or the damper housing and the rudder blade receiving groove are integrally formed. The present invention discloses an aircraft using the rudder blade flutter suppression device. The present invention also discloses a rudder blade flutter suppression method, wherein the rudder blade flutter suppression device based on particle damping is installed on the rudder blade, and the installation process comprises the following steps: finite element pre-processing, model establishment, damping ratio calculation, characteristic parameter determination, and particle damper installation. The present invention can effectively improve the flutter suppression capability of the rudder blade structure, and improve the applicability, stability and safety of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of passive vibration control, and more specifically, to a rudder blade flutter suppression device based on the particle damping vibration reduction principle, a suppression method thereof, and an aircraft using the same. Background Art

[0002] With the continuous development of science and technology, higher requirements are put forward for aircraft, requiring lighter structural weight, better flight speed and greater maneuverability. The flutter of the rudder blade is a factor that must be considered in the design of the aircraft. When the flight speed of the aircraft exceeds the critical flutter speed, its amplitude and the aerodynamic force inside the structure may change dramatically. For the problem of flutter, component flutter is an important cause, and the rudder blade is the most important component of the aircraft. It is very important to study the flutter suppression of the rudder blade. The consequences of aircraft flutter caused by rudder blade flutter are often very serious or even catastrophic.

[0003] At present, the flutter suppression methods for rudder blades are: first, by adjusting the mass distribution of the rudder blades, under certain balance conditions, the degree of bending-torsion coupling is minimized; second, by changing the stiffness characteristics of the rudder surface. After adjusting the rudder blades by the above methods, the applicability of the aircraft becomes worse and the stability becomes lower. Therefore, how to provide a method for suppressing the flutter of the rudder blades, which can not only use the optimal design of the rudder blade structure, but also have the ability to suppress the flutter of the rudder blades and improve the stability of the aircraft, is a major technical problem that needs to be solved urgently by those skilled in the art. Summary of the invention

[0004] The purpose of the present invention is to provide a rudder blade flutter suppression device based on particle damping, a suppression method and a high-speed device, so as to increase the structural damping of the rudder blade, thereby effectively improving the flutter suppression ability of the rudder blade. To achieve the above purpose, the present invention adopts the following technical solutions:

[0005] The present invention discloses a rudder blade flutter suppression device based on particle damping, comprising a plurality of particle dampers, wherein the particle dampers comprise a damper shell and a plurality of damping particles, wherein a plurality of cavities are arranged inside the damper shell, and the damping particles are filled in the cavities; a receiving groove is arranged inside the rudder blade, and the damper shell is installed in the rudder blade receiving groove, or the damper shell and the rudder blade receiving groove are integrally formed.

[0006] Furthermore, the edges of the rudder blade are respectively a leading edge, a tip chord, a trailing edge and a root chord, and the particle damper is installed at the junction of the leading edge and the tip chord of the rudder blade.

[0007] The static friction coefficient of the damping particles is in the range of 0-1, the dynamic friction coefficient is in the range of 0-1, the surface recovery coefficient is in the range of 0-1, the Poisson's ratio is in the range of 0-1, and the density is in the range of 0.1-30 g / cm3 The filling rate of the damping particles in the cavity is 5% to 100%, and the damping particles are one or more of iron-based particles, aluminum-based particles, nickel-based particles, tungsten-based particles, chromium-based particles, sodium-based particles, magnesium-based particles, manganese-based particles, calcium-based particles, copper-based particles, zinc-based particles, scandium-based particles, titanium-based particles, glass particles, oxide ceramic particles, carbide ceramic particles, and glass ceramic particles.

[0008] Wherein, the damper housing is made of flexible material.

[0009] Wherein, the damper housing is made of rigid material, and is fixed to the rudder blade receiving groove by threaded connection, key connection, profile connection, expansion connection, pin connection, riveting, welding, bonding or interference connection.

[0010] The invention also discloses an aircraft, comprising a rudder blade, on which the rudder blade flutter suppression device based on particle damping is installed.

[0011] The present invention also discloses a method for suppressing the flutter of a rudder blade. The rudder blade flutter suppression device based on particle damping is installed on the rudder blade. The installation process includes the following steps.

[0012] S1. The finite element method is used to perform finite element analysis on the rudder blade structure, and a finite element model of the rudder blade is established. The modal analysis of the rudder blade structure is performed to obtain the flutter coupling curve of the rudder blade. The flutter coupling curve of the rudder blade includes the first-order bending node line of the rudder blade and the second-order torsion node line of the rudder blade. At least one node line position where the bending-torsion modal coupling is the weakest is determined as the target installation position of the particle damper on the rudder blade.

[0013] S2. A discrete element model of the damping particle contact surface is established, and the rudder blade finite element model is coupled with the discrete element model of the damping particle to obtain a discrete element-finite element coupling model. The contact position and contact force between the damping particle and the coupling surface are obtained by solving the discrete element-finite element coupling model, and are transferred to the finite element model of the rudder blade structure as the boundary condition of the load.

[0014] S3. The shape function method is used to realize the conversion of contact force from discrete element contact points to finite element unit nodes, calculate the harmonic response of the rudder structure, and obtain the damping ratios of each order of the rudder structure.

[0015] S4. Based on the damping ratio of the rudder blade structure, the damping effect of the rudder blade after installing the particle damper is solved to determine the characteristic parameters of the damping particles.

[0016] S5. Setting the particle damper according to the determined characteristic parameters of the damping particles, and installing the obtained particle damper at the target installation position of the rudder blade.

[0017] Preferably, the process method of using the shape function method in step S3 to realize the conversion of the contact force from the discrete element contact point to the finite element unit node is as follows: based on the connection relationship between the triangular facets constituting the surface in the discrete element and the finite element mesh, the discrete element software is used to output the contact force of the damping particle in the triangular boundary unit. When the finite element mesh is extremely small and different from the discrete element boundary mesh, the equivalent concentrated load of the finite element analysis is applied to the unit node, the damping particle contact point is selected as the unit node, and the shape function method is used to convert the force acting on the damping particle and the contact structure into the equivalent node force of each unit node.

[0018] Preferably, the equivalent nodal force of each unit is used as a virtual load for calculating the harmonic response of the rudder blade structure, and the damping ratios of each order of the rudder blade structure are calculated using the half-power bandwidth method. In step S4, the damping effect of the rudder blade after the particle damper is installed is solved by calculating the response curves of the rudder blade structure under different virtual loads when the particle damper is installed at different target positions, and the characteristic parameters of the damping particles that enhance the damping effect of the rudder blade under the structure are determined.

[0019] Preferably, the characteristic parameters include: particle material, target particle size, target particle filling rate and target particle density. The process of determining the target particle material, target particle size, target particle filling rate and target particle density for improving the damping of the rudder blade structure under this structure is independent of each other and does not interfere with each other. After determining any one of the above variables, the remaining variables can be determined based on the determined variables.

[0020] Due to the adoption of the above technical solution, the present invention has the following beneficial effects:

[0021] 1. The particle damping-based rudder flutter suppression device provided by the present invention is suitable for high-speed aircraft, so that the damping ratio of the rudder structure is effectively improved, and the rudder flutter suppression capability is improved, and it has the advantages of high stability, good performance and suitability for harsh environments. And because the particle damper is light in weight, the weight of the rudder does not change much after the particle damper is installed, so that the flight speed and maneuverability of the aircraft are not affected.

[0022] 2. The present invention determines the target installation position of the particle damper based on the first-order bending node line and the second-order torsion node line of the rudder blade, obtains the optimal characteristic parameters corresponding to the particle damper, so as to achieve the optimal design of the rudder blade structure, and has the ability to suppress the flutter of the rudder blade, so that the damping ratio of the rudder blade structure is greatly improved, thereby improving the overall stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of embodiment 1.

[0024] Figure 2 It is a schematic diagram of the installation of the particle damper of the first embodiment.

[0025] Figure 3 It is a schematic diagram of the second embodiment.

[0026] Figure 4 It is a partial schematic diagram of the tail section of the aircraft in the third embodiment.

[0027] Figure 5 It is a schematic diagram of the finite element model of the rudder blade.

[0028] Figure 6 It is a schematic diagram of the first-order mode bending node line.

[0029] Figure 7 It is a schematic diagram of the second-order mode torsion node line.

[0030] Figure 8 It is a schematic diagram of the damping particle discrete element model of the rudder structure.

[0031] Fig. 9 It is a schematic diagram of the harmonic response curve of the rudder blade structure.

[0032] Fig.10 It is a schematic diagram of the transfer function amplitude curve before and after the particle damper is installed on the rudder structure.

[0033] Main component symbols:

[0034] 1: rudder blade, 2: particle damper, 3: damper housing, 4: damping particles, 5: containing groove, 6: leading edge, 7: tip chord, 8: trailing edge, 9: root chord, 10: bolt, 11: weight reduction groove. DETAILED DESCRIPTION

[0035] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0036] Embodiment 1

[0037] like Figures 1-2As shown, this embodiment discloses a rudder blade flutter suppression device based on particle damping, including a plurality of particle dampers 2, which are installed on a rudder blade 1. The rudder blade 1 includes a rudder blade body and a cover plate (not shown in the figure). The shape of the rudder blade 1 can be square, round or polygonal. As shown in the figure of this embodiment, four particle dampers 2 are installed. The particle damper 2 includes a damper housing 3 and a plurality of damping particles 4. A cavity is provided inside the damper housing 3, and the damping particles 4 are filled in the cavity. A receiving groove 5 is provided on the rudder blade body, and the damper housing 3 is installed on the receiving groove 5. The damper housing 3 can be made of rigid material or flexible material: such as a frame welded with thin steel, or made into a flexible rubber bag. When the damper housing 3 is made of rigid material, the damper housing 3 is directly fixed in the receiving groove 5, and the fixing method can be threaded connection, key connection, profile connection, expansion connection, pin connection, riveting, welding, bonding or interference connection, or the damper housing 3 can also be integrally formed with the receiving groove 5. When the damper housing 3 is a rubber bag, the damping material is directly filled in the rubber bag and then placed in the accommodating groove 5. After the installation is completed, cover plates are placed on both sides of the rudder body.

[0038] The static friction coefficient of the damping particles 4 is in the range of 0 to 1, the dynamic friction coefficient is in the range of 0 to 1, the surface recovery coefficient is in the range of 0 to 1, the Poisson's ratio is in the range of 0 to 1, the density is 0.1 to 30 g / cm3, and the filling rate of the damping particles 4 in the cavity is 5% to 100%. The damping particles 4 are one or more of iron-based particles, aluminum-based particles, nickel-based particles, tungsten-based particles, chromium-based particles, sodium-based particles, magnesium-based particles, manganese-based particles, calcium-based particles, copper-based particles, zinc-based particles, scandium-based particles, titanium-based particles, glass particles, oxide ceramic particles, carbide ceramic particles, and glass ceramic particles.

[0039] The shape of the damping particles 4 can be set to be spherical, ellipsoidal, triangular or polygonal. The diameter of the spherical damping particles 4 is 0.1 mm-200 mm, and the side length of the polygonal damping particles 4 is 0.1 mm-200 mm.

[0040] The present invention fills damping particles 4 in the cavity of the damper shell 3. When the structure vibrates, the damping particles 4 and the damping particles 4 and the wall of the damper shell 3 continuously collide and rub against each other, exchange momentum, and consume the energy of the structural vibration, thereby increasing the damping of the rudder blade structure, reducing the vibration amplitude of the rudder blade structure, and further improving the dynamic characteristics of the rudder blade 1.

[0041] Embodiment 2

[0042] like Figure 3As shown, this embodiment discloses a rudder blade flutter suppression device based on particle damping, including a plurality of particle dampers 2, which are installed on the rudder blade 1. In this embodiment, three particle dampers 2 are installed. The particle damper 2 includes a damper housing 3 and a plurality of damping particles 4. The damper housing 3 is a square frame made of thin steel. Four cavities are arranged inside the square frame. The damping particles 4 are evenly distributed and filled in the four cavities. Three receiving grooves 5 are arranged on the rudder blade 1. The three damper housings 3 are arranged in the receiving grooves 5 and are fixedly connected to the rudder blade 1 by bolts 10.

[0043] Embodiment 3

[0044] like Figure 4 As shown, this embodiment discloses an aircraft, the tail of the aircraft includes a rudder blade 1 with an elevator and a rudder, and the rudder blade 1 is installed with a flutter suppression device of the present invention. The flutter suppression device includes a particle damper 2 installed on the rudder blade, and the structure of the particle damper 2 is the same as that of the first or second embodiment.

[0045] Embodiment 4

[0046] The present invention discloses a method for suppressing the flutter of a rudder blade, and a rudder blade flutter suppression device based on particle damping is installed on a rudder blade 1. Taking the rudder blade structure of embodiment 1 as an example, the steps of the design and installation process are described in detail as follows.

[0047] S1. Finite element pre-processing

[0048] like Figure 5 As shown, the finite element method is used to perform finite element analysis on the rudder blade structure, a finite element model of the rudder blade is established, and a modal analysis is performed on the rudder blade structure to obtain the flutter coupling curve of the rudder blade. The flutter coupling curve of the rudder blade includes the first-order bending node line of the rudder blade and the second-order torsion node line of the rudder blade.

[0049] Adding counterweights at different positions of the rudder structure has different effects on increasing the critical dynamic pressure of the rudder structure, such as Figure 1 The edges of the middle rudder blade 1 are respectively the leading edge 6, the tip chord 7, the trailing edge 8, and the root chord 9. Through modal analysis, a number of weight-reducing grooves 11 and accommodating grooves 5 are arranged on the rudder blade body to adjust the mass distribution of the rudder blade. Figure 6 , Figure 7 As shown, through analysis, it can be known that at the junction of the leading edge 6 and the tip chord 7 of the rudder blade 1, the vibration mode of the rudder blade structure is close to the first order close to pure bending and the second order close to pure torsion state, and the degree of bending-torsion mode coupling is the weakest at this time. At least one node line position where the degree of bending-torsion mode coupling is the weakest is determined as the target installation position of the particle damper 2 on the rudder blade 1. In this embodiment, in addition to this position, the other three node line positions with weaker bending-torsion mode coupling are also determined as the target installation positions.

[0050] Installing the particle damper 2 at different positions has different effects on improving the damping ratio of the rudder structure. The farther the particle damping target setting position is from the bending node line, the better the improvement effect on the first-order bending damping ratio of the rudder structure; the farther the particle damping target setting position is from the torsional node line, the better the improvement effect on the second-order torsional damping ratio of the rudder structure.

[0051] S2. Model building

[0052] like Figure 8 As shown, when the damping particle 4 receives external excitation inside the rudder blade structure, friction and collision are generated in the cavity of the rudder blade structure through the damping particle 4, and a discrete element model of the damping particle and the contact surface is established by using the discrete element method. The rudder blade finite element model is coupled with the damping particle discrete element model to obtain a discrete element-finite element coupling model. The contact position and contact force between the damping particle 4 and the coupling surface are obtained in the model, and are transferred to the finite element model of the rudder blade structure as the boundary condition of the load. During the contact process, the position where the damping particle 4 contacts the coupling surface is random, and the contact force of the coupling surface is obtained by solving the discrete element-finite element coupling model.

[0053] S3. Calculate the damping ratio

[0054] The shape function method is used to realize the conversion of contact force from discrete element contact points to finite element unit nodes, calculate the harmonic response of the rudder structure, and obtain the damping ratios of each order of the rudder structure.

[0055] The process of using the shape function method to realize the conversion of contact force from discrete element contact points to finite element unit nodes is as follows: based on the connection between the triangular facets constituting the surface in the discrete element and the finite element mesh, the discrete element software is used to output the contact force of the damping particle on the triangular boundary unit. When the finite element mesh is extremely small and different from the discrete element boundary mesh, the equivalent concentrated load (force and torque) of the finite element analysis is applied to the unit node, the damping particle contact point is selected as the unit node, and the shape function method is used to convert the damping particle action and the force on the contact structure into the equivalent nodal force of each unit node. The equivalent nodal force of each unit is used as a virtual load to calculate the harmonic response of the rudder blade structure, and the damping ratio of each order of the rudder blade structure is calculated using the half-power bandwidth method.

[0056] S4. Determine characteristic parameters

[0057] Based on the damping ratio of the rudder blade structure, the damping effect of the rudder blade 1 after the particle damper 2 is installed is solved, so as to determine the characteristic parameters of the damping particles 4.

[0058] By calculating the response curves of the rudder blade structure under different virtual loads when the particle damper is installed at different target positions, the damping effect of the rudder blade after the particle damper is installed is solved, and the characteristic parameters of the damping particles that enhance the damping effect of the rudder blade under this structure are determined. The characteristic parameters of the damping particles include: particle material, target particle size, target particle filling rate, and target particle density. The specific determination method is described in detail in the following steps.

[0059] S41. taking one of the characteristic parameters as the first variable, inputting the other three characteristic parameters into the discrete element software, ensuring that the other three characteristic parameters remain unchanged, performing finite element-discrete element coupling by changing the first variable, calculating the harmonic response curve of the rudder structure, and solving the effect of improving the damping ratio of each order of the rudder structure under different first variables by the half-power method to determine the characteristic parameter of the first variable under the rudder structure, and obtaining the first target value of the characteristic parameter of the first variable;

[0060] S42. Based on the first target value obtained by solving, one of the three characteristic parameters other than the characteristic parameter of the first target value is used as the second variable, and the other two characteristic parameters are ensured to remain unchanged. The first target value and the two unchanged characteristic parameters are input into the discrete element software, and the finite element-discrete element coupling is performed by changing the second variable to calculate the harmonic response curve of the rudder structure. The improvement effect of each order damping ratio of the rudder structure under different second variables is solved by the half-power method to determine the characteristic parameter of the second variable under the rudder structure, and obtain the second target value of the characteristic parameter of the second variable;

[0061] S43. Based on the first target value and the second target value obtained by solving, one of the two characteristic parameters other than the characteristic parameters of the first target value and the second target value is used as the third variable, and the remaining characteristic parameter is ensured to be unchanged. The first target value, the second target value and the unchanged characteristic parameter are input into the discrete element software, and the finite element-discrete element coupling is performed by changing the third variable to calculate the harmonic response curve of the rudder structure. The improvement effect of each order damping ratio of the rudder structure under different third variables is solved by the half-power method to determine the characteristic parameter of the third variable under the rudder structure, and obtain the third target value of the characteristic parameter of the third variable;

[0062] S44. Based on the first target value, the second target value and the third target value obtained by solving, the remaining characteristic parameter is used as the fourth variable. The first target value, the second target value and the third target value are input into the discrete element software. By changing the fourth variable, finite element-discrete element coupling is performed, and the harmonic response curve of the rudder structure is calculated. The improvement effect of each order damping ratio of the rudder structure under different fourth variables is solved by the half-power method to determine the characteristic parameter of the fourth variable under the rudder structure, and obtain the fourth target value of the characteristic parameter of the fourth variable.

[0063] The above method determines the target particle material, target particle size, target particle filling rate and target particle density of the structure under the structure to improve the damping of the rudder blade, which are independent of each other and do not interfere with each other. After determining any one of the above variables, the remaining variables can be determined based on the determined variables.

[0064] For example, the same particle material, the same particle size, the same particle density, and different same particle filling rates (the first variable) are input through the discrete element software, and the finite element-discrete element coupling is performed to calculate the harmonic response curve of the rudder structure. The half-power method is used to solve the improvement effect of each order damping ratio of the rudder structure under different particle filling rates to determine the target particle filling rate under the rudder structure. The schematic diagram of the harmonic response curve of the rudder structure is shown in Fig. 9 .

[0065] Then, based on the target particle filling rate (first target value) obtained by the solution, the same particle material, the same particle density, and different particle sizes (second variable) are input through the discrete element software, and finite element-discrete element coupling is performed to calculate the harmonic response curve of the rudder structure. The half-power method is used to solve the improvement effect of each order damping ratio of the rudder structure under different particle sizes to determine the target particle size (second target value) under the rudder structure.

[0066] Then, based on the target particle filling rate (first target value) and target particle size (second target value) obtained by solving the solution, the same particle density and different particle materials (third variable) are input through the discrete element software, and the finite element-discrete element coupling is performed to calculate the harmonic response curve of the rudder structure. The half-power method is used to solve the improvement effect of each order damping ratio of the rudder structure under different particle materials to determine the target particle material (third target value) under the rudder structure.

[0067] Finally, based on the target particle filling rate (first target value), target particle size (second target value), and target particle material (third target value) obtained by solving the solution, different particle densities (fourth variable) are input through the discrete element software, and finite element-discrete element coupling is performed to calculate the harmonic response curve of the rudder structure. The half-power method is used to solve the improvement effect of each order damping ratio of the rudder structure under different particle materials to determine the target particle density (fourth target value) under the rudder structure.

[0068] S5. Install particle damper

[0069] The particle damper 2 is set according to the determined characteristic parameters of the damping particles, and the obtained particle damper 2 is installed at the target installation position of the rudder blade 1. Before and after the particle damper 2 is installed at the target position, the transfer function amplitude curve of the rudder blade structure is as follows: Fig.10As shown in the figure, it can be seen that after the particle damper 2 is installed, the transfer function amplitude of the rudder blade 1 is greatly reduced.

[0070] In summary, the present invention can effectively improve the flutter suppression capability of the rudder blade structure, improve the applicability, stability and safety of the aircraft, and has good practicality.

[0071] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A method for suppressing rudder blade flutter, characterized in that: A rudder blade flutter suppression device based on particle damping is installed on the rudder blade; the rudder blade flutter suppression device based on particle damping includes a plurality of particle dampers, the particle dampers include a damper shell and a plurality of damping particles, a plurality of cavities are arranged inside the damper shell, and the damping particles are filled in the cavities; a receiving groove is arranged inside the rudder blade, the damper shell is installed in the rudder blade receiving groove, or the damper shell and the rudder blade receiving groove are integrally formed; The installation process includes the following steps, S1. The finite element method is used to perform finite element analysis on the rudder blade structure, and a finite element model of the rudder blade is established. The modal analysis of the rudder blade structure is performed to obtain the flutter coupling curve of the rudder blade. The flutter coupling curve of the rudder blade includes the first-order bending node line of the rudder blade and the second-order torsion node line of the rudder blade. At least one node line position where the bending-torsion modal coupling degree is the weakest is determined as the target installation position of the particle damper on the rudder blade; S2. Establish a discrete element model of the contact surface of the damping particle, couple the rudder blade finite element model with the discrete element model of the damping particle to obtain a discrete element-finite element coupling model, solve the discrete element-finite element coupling model to obtain the contact position and contact force between the damping particle and the coupling surface, and transfer them to the finite element model of the rudder blade structure as the boundary condition of the load; S3. Use the shape function method to realize the conversion of contact force from discrete element contact points to finite element unit nodes, calculate the harmonic response of the rudder structure, and obtain the damping ratio of each order of the rudder structure; S4. Based on the damping ratio of the rudder structure, the damping effect of the rudder after the particle damper is installed is solved, so as to determine the characteristic parameters of the damping particles; S5. Setting the particle damper according to the determined characteristic parameters of the damping particles, and installing the obtained particle damper at the target installation position of the rudder blade.

2. The method for suppressing rudder blade flutter according to claim 1, characterized in that: The edges of the rudder blade are respectively a leading edge, a tip chord, a trailing edge and a root chord, and the particle damper is installed at the junction of the leading edge and the tip chord of the rudder blade.

3. The method for suppressing rudder blade flutter according to claim 1, characterized in that: The static friction coefficient of the damping particles is in the range of 0-1, the dynamic friction coefficient is in the range of 0-1, the surface recovery coefficient is in the range of 0-1, the Poisson's ratio is in the range of 0-1, and the density is in the range of 0.1-30 g / cm 3 The filling rate of the damping particles in the cavity is 5% to 100%, and the damping particles are one or more of iron-based particles, aluminum-based particles, nickel-based particles, tungsten-based particles, chromium-based particles, sodium-based particles, magnesium-based particles, manganese-based particles, calcium-based particles, copper-based particles, zinc-based particles, scandium-based particles, titanium-based particles, glass particles, oxide ceramic particles, carbide ceramic particles, and glass ceramic particles.

4. The method for suppressing rudder blade flutter according to claim 1, characterized in that: The damper housing is made of flexible material.

5. The method for suppressing rudder blade flutter according to claim 1, characterized in that: The damper housing is made of a rigid material, and is fixed to the rudder blade receiving groove by threaded connection, key connection, profile connection, expansion connection, pin connection, riveting, welding, bonding or interference connection.

6. The method for suppressing rudder blade flutter according to claim 1, characterized in that: The process method of using the shape function method in step S3 to realize the conversion of the contact force from the discrete element contact point to the finite element unit node is as follows: based on the connection relationship between the triangular facets constituting the surface in the discrete element and the finite element mesh, the discrete element software is used to output the contact force of the damping particle in the triangular boundary unit. When the finite element mesh is extremely small and different from the discrete element boundary mesh, the equivalent concentrated load of the finite element analysis is applied to the unit node, the damping particle contact point is selected as the unit node, and the shape function method is used to convert the force acting on the damping particle and the contact structure into the equivalent node force of each unit node.

7. The method for suppressing rudder blade flutter according to claim 6, characterized in that: The equivalent nodal force of each unit is used as a virtual load for calculating the harmonic response of the rudder blade structure, and the damping ratios of each order of the rudder blade structure are calculated using the half-power bandwidth method. In step S4, the damping effect of the rudder blade after the particle damper is installed is solved by calculating the response curves of the rudder blade structure under different virtual loads when the particle damper is installed at different target positions, and the characteristic parameters of the damping particles that enhance the damping effect of the rudder blade under the structure are determined.

8. The method for suppressing rudder blade flutter according to claim 7, characterized in that: The characteristic parameters include particle material, target particle size, target particle filling rate and target particle density, and the specific determination method is as follows: S41. taking one of the characteristic parameters as the first variable, inputting the other three characteristic parameters into the discrete element software, ensuring that the other three characteristic parameters remain unchanged, performing finite element-discrete element coupling by changing the first variable, calculating the harmonic response curve of the rudder structure, and solving the effect of improving the damping ratio of each order of the rudder structure under different first variables by the half-power method to determine the characteristic parameter of the first variable under the rudder structure, and obtaining the first target value of the characteristic parameter of the first variable; S42. Based on the first target value obtained by solving, one of the three characteristic parameters other than the characteristic parameter of the first target value is used as the second variable, and the other two characteristic parameters are ensured to remain unchanged. The first target value and the two unchanged characteristic parameters are input into the discrete element software, and the finite element-discrete element coupling is performed by changing the second variable to calculate the harmonic response curve of the rudder structure. The improvement effect of each order damping ratio of the rudder structure under different second variables is solved by the half-power method to determine the characteristic parameter of the second variable under the rudder structure, and obtain the second target value of the characteristic parameter of the second variable; S43. Based on the first target value and the second target value obtained by solving, one of the two characteristic parameters other than the characteristic parameters of the first target value and the second target value is used as the third variable, and the remaining characteristic parameter is ensured to be unchanged. The first target value, the second target value and the unchanged characteristic parameter are input into the discrete element software, and the finite element-discrete element coupling is performed by changing the third variable to calculate the harmonic response curve of the rudder structure. The improvement effect of each order damping ratio of the rudder structure under different third variables is solved by the half-power method to determine the characteristic parameter of the third variable under the rudder structure, and obtain the third target value of the characteristic parameter of the third variable; S44. Based on the first target value, the second target value and the third target value obtained by solving, the remaining characteristic parameter is used as the fourth variable. The first target value, the second target value and the third target value are input into the discrete element software. By changing the fourth variable, finite element-discrete element coupling is performed, and the harmonic response curve of the rudder structure is calculated. The improvement effect of each order damping ratio of the rudder structure under different fourth variables is solved by the half-power method to determine the characteristic parameter of the fourth variable under the rudder structure, and obtain the fourth target value of the characteristic parameter of the fourth variable.

9. An aircraft, characterized in that: It comprises a rudder blade, and a rudder blade flutter suppression device based on particle damping is installed on the rudder blade according to the method for suppressing rudder blade flutter according to any one of claims 1 to 8.

Images