Wallboard flutter test method, device, computer device and readable storage medium

Abstract

The application discloses a wall panel flutter test method and device, computer equipment and a readable storage medium, relates to the field of wind tunnel test, and the wall panel flutter test method is applied to the computer equipment, the computer equipment is electrically connected with a wind tunnel test cavity, the wind tunnel test cavity comprises a wall panel model, and the wall panel flutter test method comprises the following steps: performing static joint debugging on the wall panel model; in response to an input test signal, making the wind tunnel test cavity perform a test according to a preset gradually increasing wind speed, collecting test parameters of the wall panel model; when the preset gradually increasing wind speed reaches a critical speed pressure, stopping the test, and obtaining target parameters according to the test parameters, so that the wall panel flutter test can be reliably completed.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of wind tunnel test, in particular, to a wall panel flutter test method and device, computer equipment and readable storage medium. BACKGROUND

[0002] Wall panel flutter is a kind of aeroelastic instability phenomenon of aircraft skin structure due to the mutual coupling of aerodynamic force, inertial force and elastic force, and is a kind of self-excited vibration of dynamic system. Unlike the classic lift surface flutter system, the aerodynamic load of the wall panel flutter system only acts on one surface of the wall panel, and due to the geometric nonlinearity caused by large deformation of the wall panel structure, the wall panel flutter usually presents as amplitude-limited vibration, and long-term wall panel flutter will cause fatigue failure of the wall panel structure.

[0003] Since the aircraft speed reached supersonic speed in the 1950s, some flight accidents caused by wall panel flutter have occurred, such as the flight accident of German V-2 missile, American X-15 technical verification machine, "Saturn" launch vehicle and Atlas / Centaur launch vehicle in "Apollo" program have also encountered wall panel flutter problems.

[0004] However, in the prior art, the importance of wall panel flutter problem has not been recognized for a long time. Due to insufficient hardware facilities (supersonic and hypersonic wind tunnels), only some preliminary theoretical and numerical calculation research work has been done, and no one has carried out relevant research on supersonic wall panel flutter wind tunnel test. With the development of aerospace vehicles and hypersonic aircraft, the lack of basic research on wall panel flutter problem will be exposed sooner or later.

[0005] Therefore, how to provide a reliable wall panel flutter test scheme is a problem to be solved by those skilled in the art. SUMMARY

[0006] The present application provides a wall panel flutter test method, device, computer equipment and readable storage medium.

[0007] In a first aspect, the present application provides a wall panel flutter test method, applied to a computer equipment, the computer equipment is electrically connected with a wind tunnel test chamber, the wind tunnel test chamber comprises a wall panel model, and the method comprises:

[0008] Performing static joint debugging on the wall panel model;

[0009] Responding to the input test signal to make the wind tunnel test chamber test according to the preset gradually increasing wind speed, and collecting the test parameters of the wall panel model;

[0010] When the preset gradually increasing wind speed reaches a critical speed pressure, the test is stopped, and a target parameter is obtained according to the test parameter.

[0011] Optionally, the step of performing static joint debugging on the wallboard model comprises:

[0012] A preset measurement frequency of the wallboard model is obtained.

[0013] A preset test parameter is obtained, and static joint debugging is completed according to the preset test parameter and the preset measurement frequency.

[0014] Optionally, the wind tunnel test chamber further comprises a first wind tunnel side wall, a second wind tunnel side wall, a flow guide support structure, a strain gauge, a vibration sensor, and a fluctuating pressure sensor, the flow guide support structure is arranged on the first wind tunnel side wall, the wallboard model is arranged on a side of the flow guide support structure away from the first wind tunnel side wall, a cavity is formed between the wallboard model and the flow guide support structure, the strain gauge is arranged on a side of the wallboard model close to the first wind tunnel side wall, the vibration sensor is arranged near the wallboard model, and the fluctuating pressure sensor is arranged between the first wind tunnel side wall and the second wind tunnel side wall.

[0015] The step of collecting the test parameters of the wallboard model comprises:

[0016] The vibration signal of the wallboard model collected by the strain gauge is received.

[0017] The vibration signal in the wind tunnel test chamber collected by the vibration sensor is received.

[0018] The pressure fluctuation signal in the wind test chamber collected by the fluctuating pressure sensor is received.

[0019] The vibration signal of the wallboard model, the vibration signal in the wind tunnel test chamber, and the pressure fluctuation signal in the wind test chamber are taken as the test parameters.

[0020] Optionally, the step of obtaining a target parameter according to the test parameter comprises:

[0021] According to a preset flow field speed pressure step signal, the vibration signal of the wallboard model, the vibration signal in the wind tunnel test chamber, and the pressure fluctuation signal in the wind test chamber are segmented and intercepted to obtain effective test signals.

[0022] According to a preset vibration frequency range and power spectrum display of the wallboard model, a band-pass filter frequency range is set, and the effective test signals are digitally filtered according to the band-pass filter frequency range.

[0023] Random attenuation marks are extracted from the effective test signals.

[0024] According to the random attenuation mark, random interference responses generated by vibration signals in the hole test cavity and pressure fluctuation signals in the wind test cavity in the effective test signal are removed by a random attenuation method, and effective vibration responses generated by vibration signals of the wallboard model are reserved;

[0025] Target parameters are extracted from the effective vibration responses by a matrix pencil method.

[0026] Optionally, the wallboard model is obtained by the following manner:

[0027] An initial model structure size and a preset unsteady aerodynamic force model are obtained.

[0028] The initial model structure size and the preset unsteady aerodynamic force model are input into a preset wallboard flutter equation to obtain a target amplitude.

[0029] According to the target amplitude, a critical speed pressure is obtained by a peak value extraction method.

[0030] When the critical speed pressure is equal to a preset given speed pressure, the size of the wallboard model is determined.

[0031] In a second aspect, an embodiment of the present application provides a wallboard flutter test device, applied to a computer device, the computer device being electrically connected with a wind tunnel test cavity, the wind tunnel test cavity including a wallboard model, and the device including:

[0032] An adjustment module, configured to perform static joint debugging on the wallboard model.

[0033] A test module, configured to respond to an input test signal, so that the wind tunnel test cavity performs a test according to a preset gradually increasing wind speed, and collects a test parameter of the wallboard model.

[0034] An acquisition module, configured to stop the test when the preset gradually increasing wind speed reaches a critical speed pressure, and acquire a target parameter according to the test parameter.

[0035] Optionally, the adjustment module is specifically configured to:

[0036] Acquire a preset measurement frequency of the wallboard model, acquire a preset test parameter, and complete the static joint debugging according to the preset test parameter and the preset measurement frequency.

[0037] Optionally, the wind tunnel test cavity further comprises a first wind tunnel sidewall, a second wind tunnel sidewall, a flow guide support structure, a strain gauge, a vibration sensor and a fluctuating pressure sensor, the flow guide support structure is arranged on the first wind tunnel sidewall, the panel model is arranged on a side of the flow guide support structure away from the first wind tunnel sidewall, a cavity is formed between the panel model and the flow guide support structure, the strain gauge is arranged on a side of the panel model close to the first wind tunnel sidewall, the vibration sensor is arranged near the panel model, and the fluctuating pressure sensor is arranged between the first wind tunnel sidewall and the second wind tunnel sidewall.

[0038] The test module is specifically used for

[0039] receiving the vibration signal of the panel model collected by the strain gauge, receiving the vibration signal in the wind tunnel test cavity collected by the vibration sensor, receiving the pressure fluctuation signal in the wind test cavity collected by the fluctuating pressure sensor, and taking the vibration signal of the panel model, the vibration signal in the wind tunnel test cavity and the pressure fluctuation signal in the wind test cavity as the test parameters.

[0040] In a third aspect, an embodiment of the present application provides a computer device, which comprises a processor and a non-volatile memory storing computer instructions, and when the computer instructions are executed by the processor, the computer device executes the panel flutter test method in the first aspect.

[0041] In a fourth aspect, an embodiment of the present application provides a readable storage medium, which comprises a computer program, and when the computer program is executed, the readable storage medium controls a computer device where the readable storage medium is located to execute the panel flutter test method in the first aspect.

[0042] Compared with the prior art, the beneficial effects of the present application include: the panel model is statically debugged, then the wind tunnel test cavity is tested according to a preset gradually increasing wind speed in response to an input test signal, and test parameters of the panel model are collected, the test is stopped when the preset gradually increasing wind speed reaches a critical speed pressure, and target parameters are obtained according to the test parameters, so that the panel flutter test can be reliably implemented. BRIEF DESCRIPTION OF DRAWINGS

[0043] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments. It should be understood that the following drawings only show some embodiments of the present application, and therefore should not be considered as limiting the scope. For those skilled in the art, other related drawings can also be obtained without creative labor on the basis of these drawings.

[0044] Figure 1A structural schematic block diagram of a wallboard flutter test system provided by an embodiment of the present application is shown in FIG. 1.

[0045] Figure 2 A step flowchart of a wallboard flutter test method provided by an embodiment of the present application is shown in FIG. 2.

[0046] Figure 3 A structural schematic block diagram of a wind tunnel test cavity provided by an embodiment of the present application is shown in FIG. 3.

[0047] Figure 4 A structural schematic diagram of a displacement direction definition coordinate provided by an embodiment of the present application is shown in FIG. 4.

[0048] Figure 5 A structural schematic diagram of a wallboard model from one perspective provided by an embodiment of the present application is shown in FIG. 5.

[0049] Figure 6 A structural schematic diagram of a wallboard model from another perspective provided by an embodiment of the present application is shown in FIG. 6.

[0050] Figure 7 A structural schematic block diagram of a wallboard flutter test device provided by an embodiment of the present application is shown in FIG. 7.

[0051] Figure 8 A structural schematic block diagram of a computer device provided by an embodiment of the present application is shown in FIG. 8.

[0052] Icon: 100-computer device; 110-wallboard flutter test device; 1101-adjustment module; 1102-test module; 1103-acquisition module; 111-memory; 112-processor; 113-communication unit; 200-wind tunnel test cavity; 210-first wind tunnel side wall; 220-second wind tunnel side wall; 230-flow guide support structure; 300-wallboard model; 400-cavity. DETAILED DESCRIPTION

[0053] In order to make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings can be arranged and designed in various different configurations.

[0054] Therefore, the detailed description of the embodiments of the present application provided in the drawings below is not intended to limit the scope of the claimed present application, but only represents selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art without creative labor based on the embodiments in the present application are within the scope of protection of the present application.

[0055] It should be noted that similar reference numerals and letters refer to like items throughout the accompanying drawings, and once an item is defined in one drawing, it is not necessary to further define and explain it in subsequent drawings.

[0056] In addition, the terms "first", "second", and the like are used only to distinguish descriptions, and cannot be understood as indicating or implying relative importance.

[0057] In the description of the present application, it should also be noted that, unless otherwise specified and limited, the terms "set", "connected" and the like should be understood broadly, for example, "connected" can be fixedly connected, or detachably connected, or integrally connected; can be mechanically connected, or electrically connected; can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0058] The specific embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0059] Please refer to Figure 1 The wall panel flutter test method provided by the embodiments of the present application is applied to a computer device 100, the computer device 100 is electrically connected with a wind tunnel test chamber 200, the wind tunnel test chamber 200 includes a wall panel model 300, as shown in Figure 2 The wall panel flutter test method is realized through steps 201 to 203.

[0060] Step 201, static joint debugging is performed on the wall panel model 300.

[0061] Step 202, in response to the input test signal, the wind tunnel test chamber 200 is tested according to the preset gradually increasing wind speed, and the test parameters of the wall panel model 300 are collected.

[0062] Step 203, when the preset gradually increasing wind speed reaches the critical speed pressure, the test is stopped, and the target parameters are obtained according to the test parameters.

[0063] In the embodiments of the present application, in order to realize the test according to the preset gradually increasing wind speed, the wind tunnel test chamber 200 capable of realizing a large Mach number and a speed pressure range (for example, the wall panel flutter test from subsonic speed to Mach 4.0 can be realized in FL-23 wind tunnel) can be used, the target parameters can be characteristic parameters such as frequency and critical speed pressure of the wall panel model 300, and after the target parameters are obtained, reference and verification and confirmation basis can be provided for the wall panel flutter prevention design and numerical calculation of high-speed aircraft.

[0064] On the basis of the foregoing, an example of static joint debugging of the wall panel model 300 is provided in the embodiments of the present application, which can be realized through the following steps.

[0065] A preset measurement frequency of the wallboard model 300 is obtained.

[0066] Pre-set test parameters are obtained, and static joint debugging is completed according to the pre-set test parameters and the preset measurement frequency.

[0067] Before the test, a pretreatment operation can be performed on the wallboard model 300. According to the requirements of the flutter measurement frequency range (i.e., the preset measurement frequency) of the wallboard model 300, and by correctly selecting the filter, gain, and sampling frequency settings (i.e., the pre-set test parameters) of the signal acquisition system, a certain signal can be obtained by knocking the wallboard model 300 to check whether each channel has a problem, and the pretreatment (i.e., static joint debugging) of the wallboard model 300 is completed.

[0068] On this basis, please refer to Figure 3 , the wind tunnel test chamber 200 further comprises a first wind tunnel side wall 210, a second wind tunnel side wall 220, a flow guide support structure 230, a strain gauge, a vibration sensor, and a fluctuating pressure sensor. The flow guide support structure 230 is arranged on the first wind tunnel side wall 210, the wallboard model 300 is arranged on the side of the flow guide support structure 230 away from the first wind tunnel side wall 210, a cavity 400 is formed between the wallboard model 300 and the flow guide support structure 230, the strain gauge is arranged on the side of the wallboard model 300 close to the first wind tunnel side wall 210, the vibration sensor is arranged near the wallboard model 300, and the fluctuating pressure sensor is arranged between the first wind tunnel side wall 210 and the second wind tunnel side wall 220. The present application embodiment further provides an example of collecting test parameters of the wallboard model 300, which can be realized by the following steps.

[0069] The vibration signal of the wallboard model 300 collected by the strain gauge is received.

[0070] The vibration signal in the wind tunnel test chamber 200 collected by the vibration sensor is received.

[0071] The pressure fluctuation signal in the wind test chamber collected by the fluctuating pressure sensor is received.

[0072] The vibration signal of the wallboard model 300, the vibration signal in the wind tunnel test chamber 200, and the pressure fluctuation signal in the wind test chamber are taken as test parameters.

[0073] In the embodiment of the present application, the wallboard model 300 is installed on the side wall (i.e. the first wind tunnel side wall 210) of the wind tunnel test section (i.e. the wind tunnel test chamber 200) and protrudes from the side wall by a certain height to eliminate the influence of the wind tunnel boundary layer, a certain number of strain gauges are attached to the side of the wallboard model 300 (i.e. close to the first wind tunnel side wall 210) for collecting the vibration signals of the wallboard model 300; a vibration sensor is installed on the side wall of the wind tunnel test section close to the wallboard model 300 for measuring the vibration signals of the test section (i.e. the first wind tunnel side wall 210 and the second wind tunnel side wall 220) during the test; and a fluctuating pressure sensor is installed at the center position of the flow field of the test section to obtain the pressure fluctuation signals of the incoming flow during the test. It should be understood that in the embodiment of the present application, the signals of the strain gauges, the vibration sensor, the fluctuating pressure sensor and the like can be received by a dedicated acquisition device, i.e. the physical parameters collected are converted into digital signals, and then the digital signals are sent to the computer device 100 for analysis to obtain the frequency and other characteristic parameters of the wallboard flutter.

[0074] On this basis, the embodiment of the present application provides an example of obtaining target parameters according to test parameters, which can be realized by the following steps.

[0075] The vibration signals of the wallboard model 300, the vibration signals in the wind tunnel test chamber 200 and the pressure fluctuation signals in the wind tunnel test chamber are segmented and intercepted according to the preset flow field speed pressure step signal to obtain effective test signals.

[0076] According to the vibration frequency range and the power spectrum display of the wallboard model 300 obtained in advance, the band-pass filter frequency range is set, and the effective test signals are digitally filtered according to the band-pass filter frequency range.

[0077] Random attenuation markers are extracted from the effective test signals.

[0078] According to the random attenuation markers, the random interference response generated by the vibration signals in the test chamber and the pressure fluctuation signals in the test chamber is removed from the effective test signals by the random attenuation method, and the effective vibration response generated by the vibration signals of the wallboard model 300 is retained.

[0079] The target parameters are extracted from the effective vibration response by the matrix pencil method.

[0080] The data can be pre-processed first. After obtaining the vibration signal of the wallboard model 300, the vibration signal in the wind tunnel test chamber 200 and the pressure fluctuation signal in the wind test chamber, the original test data (i.e., the vibration signal of the wallboard model 300, the vibration signal in the wind tunnel test chamber 200 and the pressure fluctuation signal in the wind test chamber) can be segmented and effective data can be intercepted according to the flow field speed pressure step signal, the pre-trend item can be removed, and the band-pass filtering frequency range can be set according to the model vibration frequency range determined by the ground vibration test and the power spectrum display, and digital filtering and other pre-processing can be performed. Random attenuation markers can be extracted, and random attenuation method can be used to remove random interference responses caused by wind tunnel airflow fluctuation, tunnel vibration and the like in the pre-processed test data, and effective physical vibration responses (i.e., effective vibration responses generated by the vibration signal of the wallboard model 300) caused by initial conditions can be retained. Modal parameter identification or characteristic variable extraction can be performed, such as frequency and other characteristic parameters (i.e., target parameters) extraction using the matrix pencil method. In other embodiments of the application, other parameter identification methods can also be used to extract frequency and other characteristic parameters.

[0081] On the basis of the foregoing, the application further provides an example of obtaining a wallboard model 300.

[0082] An initial model structure size and a preset unsteady aerodynamic force model are obtained.

[0083] The initial model structure size and the preset unsteady aerodynamic force model are input into a pre-set wallboard flutter equation to obtain a target amplitude.

[0084] According to the target amplitude, a critical speed pressure is obtained by a peak value extraction method.

[0085] When the critical speed pressure is equal to the preset given speed pressure, the size of the wallboard model 300 is determined.

[0086] The Reissner-Mindlin theory (thick plate theory) can be used to convert the solution of the displacement field inside the wallboard model 300 to the neutral surface displacement field for solution, and the formula can be obtained:

[0087]

[0088] Wherein, u, v, w are displacement functions at any point in the plate; u0, v0, w0 are neutral surface displacements; θ x , θ y are the rotation angles of the neutral surface of the plate around the x and y axes, respectively, and the direction is defined as Figure 4 z is the relative thickness of the arbitrary point to the neutral surface of the plate.

[0089] On this basis, the three-node triangular Mindlin plate element (MIN3 element) can be used to discretize the wallboard structure, and the displacement field of the element can be obtained by interpolation of the nodal displacements:

[0090]

[0091] where w b , θ, w m are the nodal displacements of the MIN3 element, [H u ], [H v ], [H w ], [H wθ ], [H θx ] and [H θy ] are the displacement interpolation functions (shape functions) of the element.

[0092] Further, the von Karman strain-displacement relationship considering transverse shear deformation can be considered, and the in-plane strain of the wallboard is composed of three parts:

[0093] ε = ε m + ε mb + zκ

[0094] where ε m is the membrane strain caused by the in-plane displacement of the neutral surface; ε mb is the additional in-plane strain of the wallboard caused by the deflection w when considering large deformation; κ is the curvature of the neutral surface, and

[0095]

[0096] On the basis of the above, based on the Reissner-Mindlin theory, the transverse shear strain is not zero, and the strain includes the transverse shear strain:

[0097] The linear constitutive relation of the material is:

[0098]

[0099] where σ is the in-plane stress of the wallboard, τ is the in-plane shear stress of the wallboard, [Q] and [Q s ] are the elastic modulus matrix and the shear modulus matrix, respectively.

[0100] For a wallboard with a thickness of h, the internal force is:

[0101]

[0102] {R} = [A s ]{γ}

[0103] where:

[0104]

[0105] The quasi-steady aerodynamic force of the first-order piston theory without considering the angle of attack of the airflow is:

[0106]

[0107] Where q = p a V 2 / 2 is the dynamic pressure of the airflow; p a is the atmospheric density; V is the airflow velocity; and M is the Mach number of the incoming airflow.

[0108] On the basis of the above, the strain energy variation of the panel unit is derived from the Hamilton principle:

[0109]

[0110] Where Sur is the unit area; and a s is the lateral shear correction factor.

[0111] The kinetic energy variation of the panel unit is:

[0112]

[0113] The total work done by the aerodynamic load on the panel unit is:

[0114]

[0115] By expanding the above three equations and assembling the unit matrix, the overall strain energy variation, kinetic energy variation, and total work variation of the panel can be obtained:

[0116] The overall strain energy variation of the panel is

[0117]

[0118] The overall kinetic energy variation of the panel is

[0119]

[0120] The total work variation done by the aerodynamic load on the panel is

[0121]

[0122] The Hamilton variation principle is

[0123]

[0124] Thus, the flutter motion equation of the panel can be obtained:

[0125]

[0126] Wherein, W is the displacement vector of the wallboard structure, K0 is the elastic stiffness under the small deflection deformation of the wallboard, N1 Nm , N1 Nb is the first nonlinear stiffness matrix, N2 is the second nonlinear stiffness matrix, M is the mass matrix of the wallboard structure, C a is the aerodynamic damping matrix, K a is the aerodynamic stiffness matrix.

[0127] Through the above steps, the wallboard flutter equation of the wallboard can be obtained, and after inputting the initial model structure size and the preset unsteady aerodynamic force model into the preset wallboard flutter equation, the target amplitude can be solved, the critical speed pressure can be obtained by the peak extraction method, and when the critical speed pressure is equal to the preset given speed pressure, the size of the wallboard model 300 is determined. If the critical speed pressure is not equal to the preset given speed pressure, it indicates that the size of the wallboard model 300 does not meet the requirements, and the size needs to be changed, and then the wallboard flutter equation is inputted again for solving until the critical speed pressure is equal to the preset given speed pressure, so that the size of the wallboard model 300 can be obtained. Please refer to Figure 5 and Figure 6 .

[0128] The embodiment of the application provides a wallboard flutter test device 110, which is applied to a computer device 100, the computer device 100 is electrically connected with a wind tunnel test cavity 200, the wind tunnel test cavity 200 includes a wallboard model 300, as shown in Figure 7 The device includes:

[0129] The adjusting module 1101 is used for static joint debugging of the wallboard model 300.

[0130] The test module 1102 is used for responding to the input test signal, so that the wind tunnel test cavity 200 tests according to the preset gradually increasing wind speed, and collects the test parameters of the wallboard model 300.

[0131] The acquisition module 1103 is used for stopping the test when the preset gradually increasing wind speed reaches the critical speed pressure, and acquiring the target parameters according to the test parameters.

[0132] Further, the adjusting module 1101 is specifically used for:

[0133] Acquiring the preset measurement frequency of the wallboard model 300; acquiring the preset test parameters, and completing the static joint debugging according to the preset test parameters and the preset measurement frequency.

[0134] Further, the wind tunnel test cavity 200 further comprises a first wind tunnel side wall 210, a second wind tunnel side wall 220, a flow guide support structure 230, a strain gauge, a vibration sensor and a fluctuating pressure sensor, the flow guide support structure 230 is arranged on the first wind tunnel side wall 210, the wallboard model 300 is arranged on the side of the flow guide support structure 230 away from the first wind tunnel side wall 210, a cavity 400 is formed between the wallboard model 300 and the flow guide support structure 230, the strain gauge is arranged on the side of the wallboard model 300 close to the first wind tunnel side wall 210, the vibration sensor is arranged near the wallboard model 300, and the fluctuating pressure sensor is arranged between the first wind tunnel side wall 210 and the second wind tunnel side wall 220. The test module 1102 is specifically used for;

[0135] receiving the vibration signal of the wallboard model 300 collected by the strain gauge; receiving the vibration signal in the wind tunnel test cavity 200 collected by the vibration sensor; receiving the pressure fluctuation signal in the wind test cavity collected by the fluctuating pressure sensor; and taking the vibration signal of the wallboard model 300, the vibration signal in the wind tunnel test cavity 200 and the pressure fluctuation signal in the wind test cavity as test parameters.

[0136] In the embodiments of the present application, the implementation principle of the wallboard flutter test device 110 is the same as or similar to the experimental principle of the foregoing wallboard flutter test method, and will not be described here.

[0137] The embodiments of the present application provide a computer device 100, which comprises a processor and a non-volatile memory storing computer instructions, and when the computer instructions are executed by the processor, the computer device 100 executes the foregoing wallboard flutter test method. As shown in Figure 8 Figure 8 The computer device 100 provided by the embodiments of the present application is a structural block diagram. The computer device 100 comprises a wallboard flutter test device 110, a memory 111, a processor 112 and a communication unit 113.

[0138] The memory 111, the processor 112 and the communication unit 113 are directly or indirectly electrically connected to each other to realize the transmission or interaction of data. For example, these elements can be electrically connected to each other through one or more communication buses or signal lines. The wallboard flutter test device 110 comprises at least one software function module stored in the memory 111 in the form of software or firmware or solidified in the operating system (operating system, OS) of the computer device 100. The processor 112 is used to execute the executable modules stored in the memory 111, such as the software function modules and computer programs included in the wallboard flutter test device 110.

[0139] ​The memory 111 can be, but is not limited to, a random access memory (RAM), a read only memory (ROM), a programmable read-only memory (PROM), an erasable programmable read-only memory (EPROM), an electrically erasable programmable read-only memory (EEPROM), and the like.

[0140] The embodiment of the present application provides a readable storage medium, the readable storage medium includes a computer program, the computer program controls a computer device where the readable storage medium executes the wallboard flutter test method.

[0141] In conclusion, the embodiment of the present application provides a wallboard flutter test method, device, computer device and readable storage medium, through static joint debugging of the wallboard model; then, in response to the input test signal, the wind tunnel test chamber tests according to the preset gradually increasing wind speed, and collects the test parameters of the wallboard model; when the preset gradually increasing wind speed reaches the critical speed pressure, the test is stopped, and the target parameters are obtained according to the test parameters, so that the wallboard flutter test can be reliably realized, and reliable reference and verification and confirmation basis can be provided for the design and numerical calculation of a high-speed aircraft.

[0142] The above merely describes the preferred embodiments of the present application, but is not intended to limit the present application. The present application can have various modifications and changes for those skilled in the art. Any modification, equivalent replacement, improvement, etc. within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A wallboard chattering test method characterized by, The method is applied to a computer device electrically connected with a wind tunnel test cavity including a wallboard model, and comprises the following steps: statically debugging the wallboard model; in response to an input test signal, making the wind tunnel test cavity test according to a preset gradually increasing wind speed, and collecting test parameters of the wallboard model; when the preset gradually increasing wind speed reaches a critical speed pressure, stopping the test, and obtaining target parameters according to the test parameters; the wind tunnel test cavity further comprises a first wind tunnel side wall, a second wind tunnel side wall, a flow guide support structure, a strain gauge, a vibration sensor and a fluctuating pressure sensor, the flow guide support structure is arranged on the first wind tunnel side wall, the wallboard model is arranged on a side of the flow guide support structure away from the first wind tunnel side wall, a cavity is formed between the wallboard model and the flow guide support structure, the strain gauge is arranged on a side of the wallboard model close to the first wind tunnel side wall, the vibration sensor is arranged near the wallboard model, and the fluctuating pressure sensor is arranged between the first wind tunnel side wall and the second wind tunnel side wall; the step of collecting the test parameters of the wallboard model comprises: receiving a vibration signal of the wallboard model collected by the strain gauge; receiving a vibration signal in the wind tunnel test cavity collected by the vibration sensor; receiving a pressure fluctuation signal in the wind tunnel test cavity collected by the fluctuating pressure sensor; the vibration signal of the wallboard model, the vibration signal in the wind tunnel test cavity and the pressure fluctuation signal in the wind tunnel test cavity are taken as the test parameters.

2. The method of claim 1, wherein, the step of statically debugging the wallboard model comprises: obtaining a preset measurement frequency of the wallboard model; obtaining a preset test parameter, and completing static debugging according to the preset test parameter and the preset measurement frequency.

3. The method of claim 1, wherein, the step of obtaining target parameters according to the test parameters comprises: segmenting and intercepting the vibration signal of the wallboard model, the vibration signal in the wind tunnel test cavity and the pressure fluctuation signal in the wind tunnel test cavity to obtain effective test signals according to a preset flow field speed pressure step signal; setting a band-pass filter frequency range according to a previously obtained vibration frequency range and power spectrum display of the wallboard model, and performing digital filtering on the effective test signals according to the band-pass filter frequency range; extracting a random attenuation mark from the effective test signals; according to the random attenuation mark, removing random interference responses generated by the vibration signal in the wind tunnel test cavity and the pressure fluctuation signal in the wind tunnel test cavity from the effective test signals by a random attenuation method, and retaining effective vibration responses generated by the vibration signal of the wallboard model; extracting target parameters from the effective vibration responses by a matrix pencil method.

4. The method of claim 1, wherein, the wallboard model is obtained by the following method: obtaining an initial model structure size and a preset unsteady aerodynamic model; inputting the initial model structure size and the preset unsteady aerodynamic model into a preset wallboard flutter equation to obtain a target amplitude; obtaining a critical speed pressure by a peak value extraction method according to the target amplitude; when the critical speed pressure is equal to a preset given speed pressure, the size of the wallboard model is determined.

5. A wallboard chattering test apparatus characterized by, The application is applied to a computer device electrically connected with a wind tunnel test cavity including a panel model, and the device comprises: an adjusting module for static joint debugging of the panel model; a test module for responding to input test signals to make the wind tunnel test cavity test according to preset gradually increasing wind speed and collect test parameters of the panel model; an acquisition module for stopping the test when the preset gradually increasing wind speed reaches critical speed pressure and acquiring target parameters according to the test parameters; The wind tunnel test cavity further comprises a first wind tunnel side wall, a second wind tunnel side wall, a flow guide support structure, a strain gauge, a vibration sensor and a fluctuating pressure sensor, the flow guide support structure is arranged on the first wind tunnel side wall, the panel model is arranged on a side of the flow guide support structure away from the first wind tunnel side wall, a cavity is formed between the panel model and the flow guide support structure, the strain gauge is arranged on a side of the panel model close to the first wind tunnel side wall, the vibration sensor is arranged near the panel model, and the fluctuating pressure sensor is arranged between the first wind tunnel side wall and the second wind tunnel side wall. The test module is specifically used for; receiving vibration signals of the panel model collected by the strain gauge, receiving vibration signals in the wind tunnel test cavity collected by the vibration sensor, receiving pressure fluctuation signals in the wind tunnel test cavity collected by the fluctuating pressure sensor, and taking the vibration signals of the panel model, the vibration signals in the wind tunnel test cavity and the pressure fluctuation signals in the wind tunnel test cavity as the test parameters.

6. The apparatus of claim 5, wherein, The adjusting module is specifically used for: acquiring a preset measurement frequency of the panel model and acquiring pre-set test parameters, and completing static joint debugging according to the pre-set test parameters and the preset measurement frequency.

7. A computer device, comprising: The computer device comprises a processor and a non-volatile memory storing computer instructions, and the computer instructions are executed by the processor to execute the panel flutter test method in any one of claims 1-4.

8. A readable storage medium, characterized by, The readable storage medium comprises a computer program, and the computer program controls the computer device where the readable storage medium is located to execute the panel flutter test method in any one of claims 1-4 when running.

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