Passive nonlinear energy consumption type control structure and method for aircraft wallboard flutter suppression

Abstract

The invention belongs to the technical field of passive vibration reduction, and relates to a passive nonlinear energy consumption type control structure and method for aircraft wallboard flutter suppression, and the passive nonlinear energy consumption type control structure comprises a linear stiffness spring, a movable contact and a static contact; one end of the linear stiffness spring is connected to the inner side wall of a wall plate of the aircraft, the other end of the linear stiffness spring is connected with the movable contact, the movable contact is slidably connected with the static contact, and the static contact is fixedly connected to a rack of the aircraft; coulomb friction exists between the movable contact and the static contact. An included angle is formed between a connecting line of two ends of the linear stiffness spring and a vertical line of the wallboard; the linear stiffness spring is combined with the coulomb friction sliding block, so that when the aircraft wallboard flutters, the linear stiffness spring nonlinearly transmits the flutter of the wallboard to the coulomb friction sliding block for energy consumption, and the sliding block plays a role in damping and inhibiting the flutter of the wallboard; the flutter suppression can be realized by adopting the reliable and common spring and coulomb friction sliding block, so that the flutter suppression device is simple in structure, low in implementation difficulty, high in reliability and low in implementation cost.

Description

Technical Field

[0001] The invention belongs to the technical field of passive vibration reduction, and in particular relates to a passive nonlinear energy dissipation control structure and method for flutter suppression of aircraft wall panels. Background Art

[0002] Technological progress has made aircraft faster and faster, reaching supersonic or hypersonic speeds. As the propulsion component of aircraft, the skin has the typical structural characteristics of light weight, high strength and ultra-thin thickness. Many skins are about 0.5 mm and are usually made into rectangular flat plates or thin plates with a certain curvature. During the flight of the aircraft, due to its ultra-thin thickness and exposure to supersonic airflow, a self-excited vibration is generated under the coupling of inertia force, elastic force and aerodynamic force of airflow flowing through the surface of the skin wall panel. This vibration is usually called flutter. The harm caused by the wall panel flutter includes strong aerodynamic noise and fatigue damage. Therefore, in order to reduce / suppress the wall panel flutter, various vibration reduction measures have been adopted in the prior art, such as the use of composite materials, carbon fiber composite materials or metamaterials with damping and vibration reduction characteristics, as well as other laminated materials that increase viscous damping. The passive control means of wall panel flutter suppression include installing acoustic black hole devices, installing nonlinear energy wells, adding wall panel constrained damping layers, etc.; active control means mostly use piezoelectric materials to bond the wall panel surface.

[0003] However, current chatter suppression technology has the following shortcomings:

[0004] 1. Acoustic black holes can achieve vibration reduction requirements. The variable thickness area of ​​the black hole must satisfy certain mathematical functions, and additional damping materials must be attached. The disadvantage is that the installation is difficult and the additional mass is large;

[0005] 2. Nonlinear energy sinks have unidirectional transmission of vibration energy and usually adopt the structure of nonlinear springs, dampers and mass blocks. The disadvantage is that dampers need to be added, and the additional mass is large;

[0006] 3. The active control method of sticking piezoelectric materials on the surface of the wall panel also has the disadvantages of being difficult to implement and having unsatisfactory control effects.

[0007] Therefore, there is a need for an aircraft wall panel flutter suppression device or method with a simple structure and low implementation difficulty to solve the above technical problems. Summary of the invention

[0008] In order to solve the above technical problems, the present invention adopts a combined structure of a linear spring and coherent friction between a moving contact and a static contact. The linear spring is placed at an angle, and the inclined spring generates nonlinear force components in the horizontal and vertical directions respectively. The nonlinear force component in the vertical direction provides a nonlinear force for the flutter of the wall panel, and the nonlinear force component in the horizontal direction acts on the moving contact to form a nonlinear positive pressure between the moving and static contacts, so that the dry friction between the moving and static contacts also presents nonlinearity. By utilizing the principle of dry friction equivalent viscous damping, the nonlinear dry friction between the moving and static contacts can be equivalent to nonlinear equivalent viscous damping, which provides damping energy dissipation for the flutter of the wall panel. The present invention realizes the flutter suppression of the wall panel from two aspects: providing a nonlinear force to improve the supporting structure of the wall panel and introducing nonlinear dry friction to improve damping energy dissipation and vibration reduction.

[0009] The present invention provides the following technical solution: a passive nonlinear energy dissipation control structure for flutter suppression of aircraft wall panels, comprising: a linear stiffness spring, a moving contact, and a static contact; one end of the linear stiffness spring is connected to the inner wall of the aircraft wall panel, the other end of the linear stiffness spring is connected to the moving contact, the moving contact is slidably connected to the static contact, and the static contact is fixedly connected to the frame of the aircraft;

[0010] There is Coulomb friction between the moving contact and the stationary contact;

[0011] An angle is provided between a connecting line between two ends of the linear stiffness spring and a vertical line of the wall plate.

[0012] Preferably, the sliding direction of the moving contact slidably connected to the static contact is parallel to the wall panel or perpendicular to the wall panel.

[0013] Preferably, the angle between the connecting line of the two ends of the linear stiffness spring and the vertical line of the wall plate is θ;

[0014] When the sliding direction of the moving contact slidingly connecting the static contact is parallel to the wall plate, the value range of the angle θ is: 45°≤θ≤80°;

[0015] When the sliding direction of the moving contact slidingly connected to the static contact is perpendicular to the wall plate, the value range of the angle θ is: 10°≤θ≤60°.

[0016] Preferably, the connection modes of the linear stiffness spring to the inner side wall of the wall panel include: the linear stiffness spring fixedly connects the inner side wall of the wall panel, the linear stiffness spring hingedly connects the inner side wall of the wall panel, and the linear stiffness spring rotationally connects the inner side wall of the wall panel.

[0017] Preferably, a limiting device is provided on the static contact, and the limiting device is used to limit the sliding stroke of the moving contact slidingly connecting the static contact.

[0018] The present invention also discloses a passive nonlinear energy dissipation control method for flutter suppression of aircraft wall panels. The passive nonlinear energy dissipation control method is used for the above-mentioned passive nonlinear energy dissipation control structure. The passive nonlinear energy dissipation control method comprises the following steps:

[0019] Step 1: Establish an equivalent mechanical model of the passive nonlinear energy dissipation structure;

[0020] Step 2, equivalent nonlinear stiffness;

[0021] Step 3, equivalent nonlinear viscous damping;

[0022] Step 4, establishing an equivalent mechanical model of a four-side fixed-support wall panel with a passive nonlinear energy dissipation structure;

[0023] Step 5, establishing a simplified calculation model of nonlinear equivalent viscous damping of the passive nonlinear energy dissipation structure in the fixed-support wall panel;

[0024] Step 6: Determine the installation position and quantity of the passive nonlinear energy dissipation structure in the wall panel.

[0025] Preferably, in step 1, the components of force generated by the linear stiffness spring of the equivalent mechanical model in the X and Z directions are respectively:

[0026]

[0027] In formula (1) and formula (2), k s represents the stiffness of the linear stiffness spring, l0 represents the length of the linear stiffness spring in the free state, θ represents the angle between the linear stiffness spring and the Z direction, l represents the distance between the upper connecting end of the linear stiffness spring and the moving contact in the X direction, z represents the distance between the wall panel and the frame in the Z direction, and z represents the variable that vibrates with the wall panel when the wall panel vibrates.

[0028] More preferably, in step 2, the equivalent nonlinear stiffness is:

[0029] F Z =k1z+k3z 3 (4)

[0030] In formula (4), k1 = 2k s (1-l0 / l), k3=k s l0 / l 3 ;

[0031] In step 3, the equivalent nonlinear viscous damping is:

[0032]

[0033] In formula (6), c erepresents the equivalent viscous damping, μ represents the friction coefficient, N represents the normal pressure between the friction contact surfaces, ω represents the vibration frequency of the structure, and B represents the amplitude of the structure.

[0034] Preferably, in step 5, the nonlinear equivalent viscous damping of the simplified calculation model can be expressed as:

[0035]

[0036] In formula (14) and formula (15), I represents the moment of inertia of the section; k non represents the nonlinear stiffness of the passive nonlinear energy dissipation structure, (x ai ,y bi ) represents the support position, w=w(x,y) represents the wall displacement function, Δp represents the static pressure distribution in the cavity, pp ∞ Indicates pneumatic pressure.

[0037] Preferably, the step 6 specifically includes: generating a nonlinear force F according to the passive nonlinear energy dissipation structure Z and the nonlinear equivalent viscous damping c e-non , combined with the vibration frequency ω of the wall panel and the section inertia moment I, the linear stiffness spring stiffness k is obtained s , parameter l, original length of linear stiffness spring l0, installation position (x ai ,y bi ), thereby selecting the linear stiffness spring parameters and installation position.

[0038] The beneficial effects of the present invention are:

[0039] 1. The present invention combines a linear stiffness spring with a Coulomb friction slider, so that when an aircraft panel flutters, the linear stiffness spring nonlinearly transfers the panel flutter to the Coulomb friction slider for energy consumption, and the slider plays a role in damping and suppressing the panel flutter; the present invention adopts reliable and commonly used springs and Coulomb friction sliders to achieve flutter suppression, so the present invention has a simple structure, low implementation difficulty, high reliability and low implementation cost.

[0040] 2. In the present invention, when the wall panel flutters, the upper connecting end of the linear stiffness spring vibrates up and down in the Z direction with the wall panel. Since the lower connecting end and the moving contact are subjected to Coulomb friction in the Z direction, the linear stiffness spring will be compressed or stretched. The linear stiffness spring is placed at an angle, and the upper connecting end of the linear stiffness spring generates component forces in the X direction and the Z direction respectively. Similarly, the lower connecting end of the linear stiffness spring also generates component forces in the X direction and the Z direction of the moving contact respectively, which are equal to the upper connecting end and opposite in direction. Therefore, the present invention has a better effect in suppressing the flutter of the aircraft wall panel.

[0041] 3. The nonlinear equivalent viscous damping of the passive nonlinear energy dissipation structure of the present invention is a nonlinear function of multiple parameters such as linear spring stiffness, parameters, original length of spring, installation position, vibration frequency of wall panel, and section inertia moment. At each installation position, the passive nonlinear energy dissipation structure of the present invention can generate nonlinear force and nonlinear equivalent viscous damping, which together help to suppress the flutter of the wall panel. Therefore, the modeling method of the present invention is helpful for studying the passive control of the flutter of the aircraft wall panel, and can well simulate the passive flutter control characteristics of the spacecraft wall panel structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 It is a structural schematic diagram of a passive nonlinear energy dissipation control structure and method for flutter suppression of aircraft wall panels of the present invention;

[0043] Figure 2 It is a schematic diagram of an equivalent mechanical model of the passive nonlinear energy dissipation structure of the present invention;

[0044] Figure 3 It is a schematic diagram of the connection structure of the present invention;

[0045] Figure 4 is a schematic diagram of the installation position of the wall panel of an embodiment of the present invention;

[0046] Figure 5 is a schematic diagram of the deformation of the wall panel of the present invention after fluttering;

[0047] Figure 6 It is a schematic diagram of an equivalent mechanical model of a passive nonlinear energy dissipation structure wall panel of the present invention;

[0048] Figure 7 It is a schematic diagram of a wall panel model in a high-speed airflow according to the present invention.

[0049] In the figure, 1. linear stiffness spring; 2. moving contact; 3. static contact; 4. frame; 5. wall panel; 6. rivet; 7. cavity; 8. limit device. DETAILED DESCRIPTION

[0050] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the relevant technologies in the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0051] like Figures 1 to 7As shown, the passive nonlinear energy dissipation structure for flutter suppression of aircraft wall panels in this embodiment has the characteristics of simple structure and low implementation difficulty. This embodiment uses nonlinear vibration theory to suppress the flutter behavior of the wall panels by adding nonlinear elastic support to the wall panels and providing nonlinear dry friction energy dissipation.

[0052] 1. Passive nonlinear energy dissipation structure

[0053] The passive nonlinear energy dissipation structure of this embodiment is composed of a linear stiffness spring 1, a moving contact 2 and a static contact 3. The schematic diagram of the structure is shown in FIG. Figure 1 shown.

[0054] Figure 1 In the figure, the upper connecting end of the linear stiffness spring 1 is fixedly connected to the wall plate 5, and the lower connecting end is fixedly connected to the moving contact 2. The moving contact 2 and the static contact 3 are connected by sliding, and the two always keep in contact. There is Coulomb friction between them, and the friction coefficient is μ. The static contact 3 is fixed on the frame 4. In order to prevent the moving contact 2 from separating from the static contact 3, a limiting device 8 is set at the end of the static contact 3.

[0055] When the wall plate 5 vibrates, the upper connecting end of the linear stiffness spring 1 vibrates up and down along with the wall plate 5 in the Z direction. Since the lower connecting end and the moving contact 2 are subjected to Coulomb friction in the Z direction, the linear stiffness spring 1 is compressed or stretched. Since the linear stiffness spring 1 is placed at an angle, the upper connecting end of the linear stiffness spring 1 generates component forces F in the X direction and the Z direction respectively. X and F Z Similarly, the lower connection end of the linear stiffness spring 1 also generates F in the X direction and Z direction of the moving contact 2 respectively. X and F Z Equal and opposite forces.

[0056] 2. Equivalent mechanical model of passive nonlinear energy dissipation structure

[0057] The equivalent mechanical model of passive nonlinear energy dissipation structure is as follows Figure 2 As shown, k non is the equivalent nonlinear stiffness, c e-non is the nonlinear equivalent viscous damping.

[0058] When the wall plate 5 vibrates, the upper connection end of the linear stiffness spring 1 vibrates up and down in the Z direction along with the wall plate 5, causing the lower connection end of the linear stiffness spring 1 and the moving contact 2 to slide back and forth slightly relative to the static contact 3 in the Z direction. Figure 1 , the forces generated by the linear stiffness spring 1 in the X and Z directions are

[0059]

[0060] Among them, k sis the stiffness of the linear stiffness spring 1, l0 is the length of the linear stiffness spring 1 in the free state, θ is the angle between the linear stiffness spring 1 and the Z direction, l is the distance between the upper connecting end of the linear stiffness spring 1 and the moving contact 2 in the X direction, z is the distance between the wall panel 5 and the frame 4 in the Z direction, when the wall panel 5 vibrates, z becomes a variable that vibrates with the wall panel 5; wherein, when the moving contact 2 slides back and forth horizontally relative to the static contact 3, the value range of θ is: 45°≤θ≤60° is preferred; when the moving contact 2 slides back and forth vertically relative to the static contact 3, the value range of θ is: 30°≤θ≤60° is preferred.

[0061] In order to suppress the vibration of the wall panel 5, the passive nonlinear energy dissipation structure of this embodiment has two functions: (1) the upper connecting end of the linear stiffness spring 1 is connected to the wall panel 5, and during the vibration of the wall panel 5, a nonlinear force F is provided for suppressing the vibration of the wall panel 5. Z ; (2) F X When applied to the moving contact 2, reciprocating dry friction occurs between the moving contact 2 and the stationary contact 3. The reciprocating dry friction motion has an energy dissipation effect, providing a damping effect for the suppression of chatter.

[0062] 2.1 Equivalent nonlinear stiffness

[0063] Taylor expansion is performed on equation (2) and the first two terms are taken, then equation (2) becomes

[0064] F Z =2k s (1-l0 / l)z+k s l0 / l 3 z 3 (3)

[0065] Or abbreviated as

[0066] F Z =k1z+k3z 3 (4)

[0067] or

[0068] F Z =k non z=(k1+k3z 2 )z (5)

[0069] Where k1 = 2k s (1-l0 / l), k3=k s l0 / l 3 Obviously, formula (3) is a nonlinear function of the flutter displacement z of the wall panel 5. Since the cubic power of displacement z appears in formula (3), it means that the larger the displacement z, the greater the nonlinear force applied to the wall panel.

[0070] 2.2 Equivalent nonlinear viscous damping

[0071] According to the equivalence principle of energy method in vibration mechanics, Coulomb friction (dry friction) can be equivalent to the viscous damping coefficient, that is,

[0072]

[0073] Among them, c e is the equivalent viscous damping, μ is the friction coefficient, N is the normal pressure between the friction contact surfaces, ω is the vibration frequency of the structure (in this embodiment, it is the vibration frequency of the wall panel), and B is the amplitude of the structure (in this embodiment, it can be replaced by the vibration displacement w of the wall panel).

[0074] 3. Installation location and quantity of passive nonlinear energy dissipation structures in the wall panels

[0075] The actual engineering structure of aircraft panels mostly adopts riveted connection structure, which is usually simplified as follows in the theoretical study of aeroelastic dynamics of panels: Figure 3 (a) shows a schematic diagram of the connection structure. After the wall plate 5 and the frame 4 are riveted together with rivets 6, a cavity 7 is formed between the two. From the perspective of mechanical modeling, Figure 3 The wall panel with riveted connection structure shown in (a) can be simplified into a mechanical model of a four-side clamped plate, as shown in Figure 3 (b) as shown.

[0076] In order to facilitate viewing of the installation position of the device in the wall panel in this embodiment, it is assumed that the wall panel is transparent and two energy dissipation devices are used as an example for explanation. Figure 4 As shown, the control Figure 3 From the perspective of this embodiment, the device is installed in Figure 3 In the hollow cavity 7.

[0077] Figure 4 In the embodiment, the upper connection end of the passive nonlinear energy dissipation structure of the present embodiment is connected to the lower surface of the wall plate 5, the lower connection end of the passive nonlinear energy dissipation control structure of the present embodiment is connected to the dynamic contact point 2, the static contact point 3 is connected to the frame 4, and the dynamic contact point 2 and the static contact point 3 always maintain dry friction contact. The present embodiment is described by taking the installation of two vibration suppression devices as an example. The two passive nonlinear energy dissipation structures of the present embodiment are respectively installed at (a / 3, b / 2) and (2a / 3, b / 2) of the wall plate, as shown in FIG. Figure 4 shown.

[0078] 4. Equivalent mechanical model of four-side clamped wall panels with passive nonlinear energy dissipation structure

[0079] The schematic diagram of the deformation of the wall panel 5 after flutter is as follows: Figure 5 As shown, Figure 5In the embodiment, due to the structural limitation of the moving contact 2 and the static contact 3, the moving contact 2 can only slide back and forth along the Z direction. After the wall plate 5 vibrates and deforms, the wall plate 5 drives the upper connection end of the linear stiffness spring 1 to move up and down, and the linear stiffness spring 1 is pulled / compressed. At the same time, the lower connection end of the linear stiffness spring 1 and the moving contact 2 and the static contact 3 slide back and forth with dry friction. Figure 2 The equivalent mechanical model of the passive nonlinear energy dissipation structure wall is as follows: Figure 6 shown.

[0080] 5. Simplified calculation model of nonlinear equivalent viscous damping of passive nonlinear energy dissipation structure in fixed-support wall panels

[0081] Taking the installation of two passive nonlinear energy dissipation structures as an example, the wall panel model in high-speed airflow is as follows: Figure 7 As shown, the installation position of the passive nonlinear energy dissipation structure is referenced to Figure 4 (a).

[0082] Based on the two-dimensional wall plate motion equation, the three-dimensional wall plate motion differential equation can be obtained.

[0083]

[0084] and deformation compatibility equation

[0085]

[0086] Among them, w = w (x, y) is the displacement function of the wall plate, Φ = Φ (x, y) is the stress function, and The in-plane forces in the x and y directions are respectively, Δp is the static pressure distribution in the cavity, h is the thickness of the wall, and D = Eh 3 / 12(1-ν 2 ), E is the Young's modulus of elasticity of the panel material, ν is the Poisson's ratio, pp ∞ is the pneumatic pressure, ρ m is the density of the siding material, F non Nonlinear external forces introduced into passive nonlinear energy dissipation structures.

[0087] In order to facilitate the solution, the Galekin method is usually used to transform the motion differential equation (7) and deformation coordination equation (8) of the three-dimensional wall into a set of ordinary differential equations. The Galekin function is taken as a double sine function, that is,

[0088]

[0089] Equation (7) and equation (8) are coupled with each other, the solution process is complicated, and it is difficult to obtain an analytical solution. The numerical solution is more suitable for studying the influence of parameters.

[0090] The variation curve of the wall panel vibration displacement w=w(x,y) can be obtained by equations (7) to (9). Further, according to the equivalent viscous damping expression (6), the simplified expression for the nonlinear equivalent viscous damping calculation of this embodiment can be obtained, that is,

[0091]

[0092] According to the nonlinear vibration theory of the plate, the vibration of the wall panel 5 under supersonic airflow is a typical fluid-solid coupling vibration, and its dynamic mathematical model is a nonlinear partial differential equation. The vibration frequency ω of the wall panel 5 is related to the section inertia moment I and the nonlinear stiffness k of the passive nonlinear energy dissipation structure. non and support position (x ai ,y bi ) and other parameters, namely

[0093] ω=ω(I,k non ,x ai ,y bi ) x ai ∈(0,a),y bi ∈(0,b) (11)

[0094] In addition, the vibration displacement of the wall panel 5 is also related to the parameters of the wall panel structure parameters, aerodynamic pressure, static pressure distribution in the cavity, etc. The vibration displacement of the wall panel 5 at the first installation position can be simplified into a functional expression, that is,

[0095] w1(a / 3,b / 2)=w(ω,I,pp ∞ ,Δp,a / 3,b / 2) (12)

[0096] The vibration displacement of the wall panel 5 at the second installation position can be simplified into a functional expression, that is,

[0097] w2(2a / 3,b / 2)=w(ω,I,pp ∞ ,Δp,2a / 3,b / 2) (13)

[0098] Therefore, the nonlinear equivalent viscous damping generated by the passive nonlinear energy dissipation structure of this embodiment at the two positions can be expressed as follows:

[0099]

[0100] The nonlinear equivalent viscous damping of the passive nonlinear energy dissipation structure of this embodiment is the linear spring stiffness k s , parameter l, original length of spring l0, installation position (x ai ,y bi), the vibration frequency ω of the wall panel, the section inertia moment I and other nonlinear functions. At each installation position, the passive nonlinear energy dissipation structure of this embodiment can generate a nonlinear force F Z and the nonlinear equivalent viscous damping c e-non , the two combined help to suppress the wall panel flutter.

[0101] In summary, the present invention combines a linear stiffness spring with a Coulomb friction slider, so that when the aircraft wall panel flutters, the linear stiffness spring nonlinearly transfers the wall panel flutter to the Coulomb friction slider for energy consumption, and the slider plays a role in damping and suppressing the wall panel flutter; the present invention adopts reliable and commonly used springs and Coulomb friction sliders to achieve flutter suppression, so the present invention has a simple structure, low implementation difficulty, high reliability and low implementation cost.

[0102] It should be emphasized that the above are only preferred embodiments of the present invention and do not limit the present invention in any form. Any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention are still within the scope of the technical solution of the present invention.

Claims

1. A passive nonlinear energy dissipation control structure for flutter suppression of aircraft panels, characterized in that: include: A linear stiffness spring (1), a moving contact (2), and a static contact (3); one end of the linear stiffness spring (1) is connected to the inner wall of a wall panel (5) of an aircraft, the other end of the linear stiffness spring (1) is connected to the moving contact (2), the moving contact (2) is slidably connected to the static contact (3), and the static contact (3) is fixedly connected to a frame (4) of the aircraft; Coulomb friction exists between the moving contact (2) and the stationary contact (3); An angle is provided between a line connecting two ends of the linear stiffness spring (1) and a vertical line of the wall plate (5).

2. The passive nonlinear energy dissipation control structure for flutter suppression of aircraft panels according to claim 1, characterized in that: The sliding direction of the moving contact (2) for sliding connection with the static contact (3) is parallel to the wall plate (5) or perpendicular to the wall plate (5).

3. The passive nonlinear energy dissipation control structure for flutter suppression of aircraft wall panels according to claim 1, characterized in that: The angle between the connecting line of the two ends of the linear stiffness spring (1) and the vertical line of the wall plate (5) is θ; When the sliding direction of the moving contact (2) slidingly connected to the static contact (3) is parallel to the wall plate (5), the value range of the angle θ is: 45°≤θ≤80°; When the sliding direction of the moving contact (2) for sliding connection with the static contact (3) is perpendicular to the wall plate (5), the value range of the angle θ is: 10°≤θ≤60°.

4. The passive nonlinear energy dissipation control structure for flutter suppression of aircraft panels according to claim 1, characterized in that: The connection modes of the linear stiffness spring (1) to the inner side wall of the wall panel (5) include: the linear stiffness spring (1) is fixedly connected to the inner side wall of the wall panel (5), the linear stiffness spring (1) is hingedly connected to the inner side wall of the wall panel (5), and the linear stiffness spring (1) is rotatably connected to the inner side wall of the wall panel (5).

5. The passive nonlinear energy dissipation control structure for flutter suppression of aircraft wall panels according to claim 1, characterized in that: The static contact (3) is provided with a limiting device (8), and the limiting device (8) is used to limit the sliding stroke of the moving contact (2) slidingly connecting the static contact (3).

6. A passive nonlinear energy dissipation control method for flutter suppression of aircraft wall panels, characterized in that: The passive nonlinear energy dissipation control method is used for the passive nonlinear energy dissipation control structure according to any one of claims 1 to 5, and the passive nonlinear energy dissipation control method comprises the following steps: Step 1: Establish an equivalent mechanical model of the passive nonlinear energy dissipation structure; Step 2, equivalent nonlinear stiffness; Step 3, equivalent nonlinear viscous damping; Step 4, establishing an equivalent mechanical model of a four-side fixed-support wall panel with a passive nonlinear energy dissipation structure; Step 5, establishing a simplified calculation model of nonlinear equivalent viscous damping of the passive nonlinear energy dissipation structure in the fixed-support wall panel; Step 6: Determine the installation position and quantity of the passive nonlinear energy dissipation structure in the wall panel.

7. A passive nonlinear energy dissipation control method for flutter suppression of aircraft wall panels according to claim 6, characterized in that: In step 1, the components of force generated by the linear stiffness spring of the equivalent mechanical model in the X and Z directions are: In formula (1) and formula (2), k s represents the stiffness of the linear stiffness spring, l0 represents the length of the linear stiffness spring in the free state, θ represents the angle between the linear stiffness spring and the Z direction, l represents the distance between the upper connecting end of the linear stiffness spring and the moving contact in the X direction, z represents the distance between the wall panel and the frame in the Z direction, and z represents the variable that vibrates with the wall panel when the wall panel vibrates.

8. The passive nonlinear energy dissipation control method for flutter suppression of aircraft wall panels according to claim 7, characterized in that: In step 2, the equivalent nonlinear stiffness is: F Z =k1z+k3z 3 (4) In formula (4), k1 = 2k s (1-l0 / l), k3=k s l0 / l 3 ; In step 3, the equivalent nonlinear viscous damping is: In formula (6), c e represents the equivalent viscous damping, μ represents the friction coefficient, N represents the normal pressure between the friction contact surfaces, ω represents the vibration frequency of the structure, and B represents the amplitude of the structure.

9. The passive nonlinear energy dissipation control method for flutter suppression of aircraft wall panels according to claim 8, characterized in that: In step 5, the nonlinear equivalent viscous damping of the simplified calculation model can be expressed as: In formula (14) and formula (15), I represents the moment of inertia of the section; k non represents the nonlinear stiffness of the passive nonlinear energy dissipation structure, (x ai ,y bi ) represents the support position, w=w(x,y) represents the wall displacement function, Δp represents the static pressure distribution in the cavity, pp ∞ Indicates pneumatic pressure.

10. The passive nonlinear energy dissipation control method for flutter suppression of aircraft wall panels according to claim 6, characterized in that: The step 6 specifically includes: generating a nonlinear force F according to the passive nonlinear energy dissipation structure Z and the nonlinear equivalent viscous damping c e-non , combined with the vibration frequency ω of the wall panel and the section inertia moment I, the linear stiffness spring stiffness k is obtained s , parameter l, original length of linear stiffness spring l0, installation position (x ai ,y bi ), thereby selecting the linear stiffness spring parameters and installation position.

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