Adjustable multi-mode cascade oscillation system for aeroelastic experiment
Patent Information
- Application Number
- CN202610382666.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-03-26
- Publication Date
- 2026-07-10
Smart Images
Figure CN122360862A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of aero-engines / gas turbines, and more particularly to an adjustable multimodal blade cascade oscillation system for aeroelastic experiments. Background Technology
[0002] Currently, experimental techniques for realizing blade cascade oscillation mainly rely on piezoelectric ceramic actuators, electromagnetic exciters, etc. Although this experimental method is relatively mature, it has always had the following limitations: (1) The parameter adjustment is complex. When the device adjusts the mixed modes reflecting different proportions of translation and torsion, it often needs to coordinate the adjustment of multiple physical parameters such as frequency, amplitude and mode. These parameters are coupled with each other, the adjustment process is complex and it is difficult to accurately control the target proportion; (2) There is a lack of direct control of core aerodynamic parameters. There is no direct target for the key dimensionless parameters that determine the aeroelastic stability. This invention introduces the translational torsional mode incident ratio PTIR for design. PTIR is a comprehensive aeroelastic design parameter that combines the reduced frequency and mode; (3) The device is complex, the manufacturing cost is high, and it is difficult to guarantee stiffness and motion accuracy under high dynamic loads. In addition to traditional piezoelectric ceramic / electromagnetic exciters, pneumatic and hydraulic exciters have also been proposed. Pneumatic drive uses compressed gas to drive a flexible cavity or structure to generate periodic oscillations, but this requires a stable gas source. Nonlinearity and control accuracy are issues that need to be addressed. Hydraulic drive works on a similar principle to pneumatic drive, using liquid as the working medium, but the system is more complex and bulky, and has sealing and leakage problems.
[0003] In summary, while piezoelectric ceramics and electromagnetic exciters can achieve high-frequency oscillations, they are expensive, have limited output displacement, and are complex to adjust. Pneumatic and hydraulic exciters, on the other hand, suffer from insufficient control precision and difficulty in guaranteeing pure harmonic motion waveforms. Therefore, there is an urgent need in this field for a novel blade cascade oscillation drive scheme that can overcome these shortcomings and combines simple structure, precise motion, and low cost. Summary of the Invention
[0004] In view of this, this application provides an adjustable multimodal blade cascade oscillation system for aeroelasticity experiments, which solves the problems in the prior art and realizes the regular oscillation of the blade cascade through a simple, reliable and low-cost mechanical structure.
[0005] The adjustable multimodal blade cascade oscillation system for aeroelastic experiments provided in this application adopts the following technical solution:
[0006] An adjustable multimodal blade cascade oscillation system for aeroelasticity experiments includes a linear reciprocating motion mechanism and a oscillating motion mechanism; The linear reciprocating motion mechanism includes a drive component and a linear motion component. The drive component drives the moving end of the linear motion component to perform linear reciprocating motion, and the displacement and time relationship of the moving end follows a sine function law. The drive component is also used to adjust the amplitude of the sine function when the moving end performs linear reciprocating motion. The swing motion mechanism includes a hinge seat, a swing linear guide rail, a swing slider, a conversion link, and a locking assembly. The first end of the swing linear guide rail is hinged to the hinge seat, and the swing slider slides on the swing linear guide rail. The swing slider is fixedly connected to the center position of the arc line of the measured leaf cascade. One end of the conversion link is hinged to the moving end, and the other end of the conversion link is hinged to the second end of the swing linear guide rail. The hinge axes at both ends of the conversion link are parallel to each other. The locking assembly is used to lock the position of the swing slider on the swing linear guide rail. The linear reciprocating motion of the moving end drives the swing linear guide rail to swing around the hinge seat.
[0007] Optionally, the driving assembly includes a driving component, a turntable, a first linear guide rail, a first slider, a positioning structure, and a connecting rod; The output shaft of the drive component is connected to the axis of the turntable. The drive component drives the turntable to rotate at a constant speed around the axis. The first linear guide rail is fixed on the turntable along the radial direction of the turntable. The first slider is slidably disposed on the first linear guide rail. The first slider slides on the first linear guide rail along the radial direction of the turntable. The positioning structure is used to lock the position of the first slider on the first linear guide rail. One end of the connecting rod is hinged to the first slider, and the other end of the connecting rod is hinged to the moving end. The hinge axes at both ends of the connecting rod, the axial direction of the turntable, and the hinge axes at both ends of the conversion link are parallel to each other. The straight path of the moving end is set along the radial direction of the turntable. The hinge seat and the drive component are relatively stationary. The turntable rotates, causing the first linear guide rail and the first slider to move in a circular motion around the axis of the turntable. The first slider drives the moving end of the linear motion component to perform linear reciprocating motion through a connecting rod. The displacement and time relationship of the moving end follows a sine function law. By adjusting the position of the first slider on the first linear guide rail, the amplitude of the sine function when the moving end performs linear reciprocating motion is changed.
[0008] Optionally, the expression for the sine function following the displacement-time relationship of the moving end is: ; in, for The displacement of the moving end at any given moment; The amplitude; The angular velocity of the output shaft of the drive component. This refers to the current moment.
[0009] Optionally, the linear motion component includes a second linear guide rail and a second slider, the second slider sliding on the second linear guide rail, the second slider serving as the motion end, and the length direction of the second linear guide rail being arranged along the radial direction of the turntable.
[0010] Optionally, when the first slider is in circular motion, the included angle between the conversion link and the swing linear guide is in the range of 60-150°.
[0011] Optionally, the distance between the swing slider and the axis of the hinge seat on the swing linear guide rail is... According to the required incident ratio of the translational torsional mode The calculation is as follows: ; in, , where is the axial chord length of the blade cascade; For the target reduced frequency, This is the default value; According to the formula Calculate the angular velocity of the output shaft of the drive component. , The chord length of the leaf cascade. The incoming flow velocity.
[0012] Optionally, a scale is provided on the outer surface of the first linear guide rail, and the scale of the first linear guide rail increases from the turntable axis as the zero scale along the length direction of the first linear guide rail towards the outer ring of the turntable.
[0013] Optionally, the outer surface of the swing linear guide is provided with a scale, and the scale of the swing linear guide increases from the axis of the hinge seat as the zero point along the length of the swing linear guide towards the other end.
[0014] In summary, this application includes the following beneficial technical effects: The core advantage of this application lies in its ability to completely decouple the amplitude of the blade cascade oscillation angle and the incident ratio of the translational torsional modes through mechanical means. Furthermore, the mechanical structure design ensures that the waveform of the blade cascade oscillation is a highly accurate sine wave, achieving regular oscillation of the blade cascade. This satisfies the core requirements of the aerodynamic influence coefficient method based on linear theory for input motion, providing a feasible experimental scheme for obtaining reliable and accurate experimental data. Attached Figure Description
[0015] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0016] Figure 1 This is a schematic diagram of the adjustable multimodal cascade oscillation system according to an embodiment of this application; Figure 2 This is a schematic diagram of the adjustable multimodal cascade oscillation system according to an embodiment of this application from another perspective; Figure 3 This is a schematic diagram of the blade cascade motion geometry and modal principle of the adjustable multimodal blade cascade oscillation system according to an embodiment of this application.
[0017] Explanation of reference numerals in the attached drawings: 1. Drive assembly; 11. Turntable; 12. First linear guide rail; 13. First slider; 14. Connecting rod; 2. Linear motion assembly; 21. Second linear guide rail; 22. Second slider; 3. Swinging motion mechanism; 31. Hinge seat; 32. Swinging linear guide rail; 33. Swinging slider; 34. Conversion link; 4. Leaf gate. Detailed Implementation
[0018] The embodiments of this application will now be described in detail with reference to the accompanying drawings.
[0019] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0020] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.
[0021] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The illustrations only show the components related to this application and are not drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.
[0022] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.
[0023] This application provides an adjustable multimodal blade cascade oscillation system for aeroelasticity experiments.
[0024] like Figure 1 and Figure 2 As shown, an adjustable multimodal blade cascade oscillation system for aeroelasticity experiments includes a linear reciprocating motion mechanism and a oscillating motion mechanism 3.
[0025] The linear reciprocating motion mechanism includes a drive component 1 and a linear motion component 2. The drive component 1 drives the moving end of the linear motion component 2 to perform linear reciprocating motion, and the displacement and time relationship of the moving end follows a sine function law. The drive component 1 is also used to adjust the amplitude of the sine function when the moving end performs linear reciprocating motion.
[0026] The swing motion mechanism 3 includes a hinge seat 31, a swing linear guide rail 32, a swing slider 33, a conversion link 34, and a locking assembly. The first end of the swing linear guide rail 32 is hinged to the hinge seat 31. The swing slider 33 slides on the swing linear guide rail 32 and is fixedly connected to the center position of the arc of the measured leaf cascade 4. One end of the conversion link 34 is hinged to the moving end, and the other end of the conversion link 34 is hinged to the second end of the swing linear guide rail 32. The hinge axes at both ends of the conversion link 34 are parallel to each other. The locking assembly is used to lock the position of the swing slider 33 on the swing linear guide rail 32. The linear reciprocating motion of the moving end drives the swing linear guide rail 32 to swing around the hinge seat 31. In this embodiment, the locking assembly is a locking bolt that passes through the side wall of the swing linear guide rail 32 and is threadedly connected to it. The bolt end of the locking bolt abuts against the swing slider 33 to lock its position. Loosening the locking bolt allows adjustment of the position of the swing slider 33.
[0027] In this application, the amplitude of the swing angle of the swing linear guide 32 is adjusted by adjusting the amplitude of the moving end, thereby adjusting the amplitude of the swing angle of the blade cascade 4; the distance between the center position of the arc in the blade cascade 4 and the rotation axis of the swing of the blade cascade 4 is adjusted by adjusting the distance between the swing slider 33 and the hinge seat 31, thereby adjusting the incident ratio of the translational torsional mode.
[0028] The driving assembly 1 includes a driving component, a turntable 11, a first linear guide rail 12, a first slider 13, a positioning structure, and a connecting rod 14. The output shaft of the driving component is connected to the axis of the turntable 11, and the driving component drives the turntable 11 to rotate uniformly around the axis. The first linear guide rail 12 is fixed on the turntable 11 along the radial direction of the turntable 11. The first slider 13 is slidably disposed on the first linear guide rail 12 and slides along the radial direction of the turntable 11 on the first linear guide rail 12. The positioning structure is used to lock the position of the first slider 13 on the first linear guide rail 12. One end of the connecting rod 14 is hinged to the first slider 13, and the other end of the connecting rod 14 is connected to the moving end. The hinge is formed by the hinge axes at both ends of the connecting rod 14, the axis of the turntable 11, and the hinge axes at both ends of the conversion link 34 being parallel to each other. The linear path of the moving end is set along the radial direction of the turntable 11, and the hinge seat 31 and the driving component are relatively stationary. The turntable 11 rotates, causing the first linear guide rail 12 and the first slider 13 to perform circular motion around the axis of the turntable 11. The first slider 13 drives the moving end of the linear motion assembly 2 to perform linear reciprocating motion via the connecting rod 14. The displacement and time relationship of the moving end follow a sine function law. By adjusting the position of the first slider 13 on the first linear guide rail 12, the amplitude of the sine function during the linear reciprocating motion of the moving end can be changed. In this embodiment, the driving component is a motor, and the positioning structure is a positioning bolt that passes through the side wall of the first linear guide rail 12 and is threadedly connected to the first linear guide rail 12. The screw end of the positioning bolt abuts against the first slider 13 to lock the position of the first slider 13. Loosening the positioning bolt allows adjustment of the position of the first slider 13. In one embodiment, the distance between the two hinge points of the connecting rod 14 is greater than or equal to five times the radial distance from the first slider 13 to the axis of the turntable 11.
[0029] The first-order bending mode of blade cascade 4 can be decomposed into translational and torsional modes. The translational mode vibrates circumferentially along blade cascade 4, exhibiting overall translational vibration, with the maximum modal displacement being globally uniform. The torsional mode vibrates rotationally around the center of the arc in blade cascade 4, with the maximum modal displacement located at both ends of blade cascade 4. The incident ratio of translational and torsional modes is a core dimensionless aeroelastic design parameter that links structural dynamics with aerodynamics and reflects the ratio of translational to torsional modes. Its construction process is as follows: (1) Combination Figure 3 The relationship between the angle and the length, It can be represented as:
[0030] in, This represents the rotational angular displacement of the blade cascade 4 about the hinge seat 31. The distance between the center of the arc in blade cascade 4 and the axis of hinge seat 31. The axial chord length of blade cascade 4, Let be the radian value of the rotational angular displacement of the blade cascade 4 about the hinge seat 31. For the rotation of the blade cascade 4 around the hinge seat 31 The displacement at the center of the arc in the blade cascade after angular displacement. For the rotation of the blade cascade 4 around the hinge seat 31 The displacement of the leading edge of the cascade after angular displacement. For the rotation of the blade cascade 4 around the hinge seat 31 The displacement of the trailing edge of the cascade after angular displacement. It is the sum of the distance between the center position of the arc in the blade cascade 4 and the axis of the hinge seat 31 and half the axial chord length of the blade cascade 4.
[0031] (2) Changes in incident torsional mode Depends on angular rotational displacement Changes in the incident translational mode It depends on the translational velocity. and incoming flow velocity :
[0032] In equations (3) and (4), For the reduced frequency, For the reduced frequency, For time, The angular velocity of the output shaft of the drive component. This is the first derivative of the displacement at the center of the arc in the cascade with respect to time. Furthermore... and The following relationships also exist:
[0033] (3) Finally, the aeroelastic design parameter, the incident ratio of the translational torsional mode, is defined as:
[0034] Among them, in calculation During the process, In and In Periodic changes within a cycle, for The ratios are averaged over time, thus eliminating their influence. Only static proportional relationships remain in the ratio relationships.
[0035] The core principle of this application is to allow independent adjustment of angular amplitude and reduced frequency. And modalities, to achieve the incident ratio of translational to torsional modes for core design parameters. Precise and decoupled control provides unprecedented convenience for flutter stability research. If unchanged, then The changes depend entirely on . When the value is small, it indicates that the vibration mode of the blade cascade 4 is dominated by the torsional mode; When the value is large, it indicates that the vibration mode of the blade cascade 4 is mainly translational.
[0036] In this application, the sinusoidal function expression governing the displacement and time relationship of the moving end is as follows: ; in, for The displacement of the moving end at any given moment; The amplitude; This refers to the angular velocity of the output shaft of the driving component. This refers to the current moment.
[0037] Oscillation function of oscillating linear guide 32 ;in, for The angular displacement of the oscillating linear guide 32 at constant intervals. This represents the maximum angular displacement amplitude of the oscillating linear guide rail.
[0038] The linear motion component 2 includes a second linear guide rail 21 and a second slider 22. The second slider 22 slides on the second linear guide rail 21 and serves as the moving end. In this embodiment, to ensure that the first linear guide rail 12, the second linear guide rail 21, and the swing linear guide rail 32 do not interfere with each other, the first linear guide rail 12, the second linear guide rail 21, and the swing linear guide rail 32 are designed in different planes. The length direction of the second linear guide rail 21 is arranged along the radial direction of the turntable 11.
[0039] When the first slider 13 is in circular motion, the included angle between the conversion link 34 and the swing linear guide 32 is in the range of 60-150°.
[0040] In one embodiment, the first linear guide 12, the second linear guide 21, and the swing linear guide 32 are T-shaped grooves, and the first slider 13, the second slider 22, and the swing slider 33 are T-shaped sliders that cooperate with the T-shaped grooves. Scales can also be provided on the outer surfaces of the first linear guide 12 and the swing linear guide 32. The scale of the first linear guide 12 increases along the length of the turntable 12 towards the outer ring of the turntable 11 with the axis of the turntable 11 as the zero point. The scale of the swing linear guide 32 increases along the length of the swing linear guide 32 towards the other end with the axis of the hinge seat 31 as the zero point.
[0041] When conducting the experiment, first determine three core target parameters according to the experimental outline: reduced frequency. According to the incoming flow velocity chord length of leaf grating 4 The calculation formula is as follows: This parameter determines the angular velocity of the output shaft of the subsequent drive component. Target angle amplitude of blade cascade 4 This refers to the maximum angle at which the blade cascade 4 swings around the hinge seat 31. The incident ratio of the target's translational torsional mode. : These are the core aeroelastic design parameters, derived from the reduced frequency. The distance between the center of the arc in the cascade 4 and the hinge seat 31 A joint decision.
[0042] After determining the core target parameters, the target angular amplitude of the swing linear guide 32 is adjusted by adjusting the radial distance between the first slider 13 and the axis of the turntable 11. The target angular amplitude of the swing linear guide 32 is the swing angular amplitude γ of the blade cascade 4. Generally, the swing angular amplitude γ of the blade cascade 4 is designed so that the straight-line distance between the center position of the arc in the blade cascade 4 and the blade cascade 4 at the extreme positions on both sides is less than or equal to 1% of the chord length of the blade cascade 4. The distance between the swing slider 33 and the axis of the hinge seat 31 on the swing linear guide 32 is calculated according to the incident ratio of the target translational torsional mode. Specifically: the distance between the swing slider 33 and the axis of the hinge seat 31 on the swing linear guide 32. According to the required incident ratio of the translational torsional mode The calculation is as follows: ,in, The axial chord length of blade cascade 4; change It can achieve the incident ratio of translational to torsional modes. Stepless adjustment.
[0043] For different experimental cascades 4, the target angle amplitude needs to be adjusted accordingly. Only the radial distance between the first slider 13 and the axis of the turntable 11 needs to be readjusted after stopping the machine; if the folding frequency is fixed, only the incident ratio of the target translational torsional mode needs to be changed. After stopping the machine, it is only necessary to readjust the position of the blade 4, that is, the distance between the swing slider 33 and the axis of the hinge seat 31 on the swing linear guide 32. If the refraction frequency needs to be changed, only the rotational speed of the output shaft of the drive component needs to be changed. If it is necessary to maintain the incident ratio of the translational torsional mode at this time The position of blade cascade 4 needs to be adjusted synchronously according to the formula, while the position remains unchanged. This application can independently change the oscillation parameters of blade cascade 4 to study amplitude nonlinear effects or match different dynamic pressure conditions. By adjusting different parameters according to experimental requirements, a series of aeroelastic experiments under different combinations of incident ratios and angular amplitudes of translational torsional modes can be completed efficiently, thereby systematically revealing the influence of different vibration modes on the flutter stability of blade cascade 4.
[0044] This decoupling design makes the experimental process extremely efficient and flexible, and can systematically map the aeroelastic stability characteristics throughout the entire parameter space.
[0045] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. An adjustable multimodal blade cascade oscillation system for aeroelasticity experiments, characterized in that, Including linear reciprocating motion mechanism and oscillating motion mechanism (3); The linear reciprocating motion mechanism includes a drive component (1) and a linear motion component (2). The drive component (1) drives the motion end of the linear motion component (2) to perform linear reciprocating motion, and the displacement and time relationship of the motion end follows a sine function law. The drive component (1) is also used to adjust the amplitude of the sine function when the motion end performs linear reciprocating motion. The swing motion mechanism (3) includes a hinge seat (31), a swing linear guide rail (32), a swing slider (33), a conversion link (34), and a locking assembly. The first end of the swing linear guide rail (32) is hinged to the hinge seat (31), and the swing slider (33) slides on the swing linear guide rail (32). The swing slider (33) is used to fix the center position of the middle arc of the measured leaf cascade (4). One end of the conversion link (34) is hinged to the moving end, and the other end of the conversion link (34) is hinged to the second end of the swing linear guide rail (32). The hinge axes at both ends of the conversion link (34) are parallel to each other. The locking assembly is used to lock the position of the swing slider (33) on the swing linear guide rail (32). The linear reciprocating motion of the moving end drives the swing linear guide rail (32) to swing around the hinge seat (31).
2. The adjustable multimodal blade cascade oscillation system for aeroelasticity experiments according to claim 1, characterized in that, The drive assembly (1) includes a drive component, a turntable (11), a first linear guide rail (12), a first slider (13), a positioning structure, and a connecting rod (14); The output shaft of the drive member is connected to the axis of the turntable (11). The drive member drives the turntable (11) to rotate at a constant speed around the axis. The first linear guide rail (12) is fixed on the turntable (11) in the radial direction. The first slider (13) is slidably disposed on the first linear guide rail (12). The first slider (13) slides on the first linear guide rail (12) in the radial direction of the turntable (11). The positioning structure is used to lock the position of the first slider (13) on the first linear guide rail (12). One end of the connecting rod (14) is hinged to the first slider (13). The other end of the connecting rod (14) is hinged to the moving end. The hinge shafts at both ends of the connecting rod (14), the axial direction of the turntable (11), and the hinge shafts at both ends of the conversion link (34) are parallel to each other. The straight path of the moving end is set in the radial direction of the turntable (11). The hinge seat (31) and the drive member are relatively stationary. The turntable (11) rotates, causing the first linear guide rail (12) and the first slider (13) to move in a circular motion around the axis of the turntable (11). The first slider (13) drives the moving end of the linear motion component (2) to perform linear reciprocating motion through the connecting rod (14). The displacement and time relationship of the moving end follow the law of sine function. By adjusting the position of the first slider (13) on the first linear guide rail (12), the amplitude of the sine function when the moving end performs linear reciprocating motion is changed.
3. The adjustable multimodal blade cascade oscillation system for aeroelasticity experiments according to claim 2, characterized in that, The expression for the sine function that governs the relationship between displacement and time at the moving end is: ； in, for The displacement of the moving end at any given moment; The amplitude; The angular velocity of the output shaft of the drive component. This refers to the current moment.
4. The adjustable multimodal blade cascade oscillation system for aeroelasticity experiments according to claim 2, characterized in that, The linear motion component (2) includes a second linear guide rail (21) and a second slider (22). The second slider (22) slides on the second linear guide rail (21) and serves as the motion end. The length direction of the second linear guide rail (21) is arranged along the radial direction of the turntable (11).
5. The adjustable multimodal blade cascade oscillation system for aeroelasticity experiments according to claim 4, characterized in that, When the first slider (13) is in circular motion, the included angle between the conversion link (34) and the swing linear guide (32) is 60-150°.
6. The adjustable multimodal blade cascade oscillation system for aeroelasticity experiments according to claim 2, characterized in that, The distance between the swing slider (33) and the axis of the hinge seat (31) on the swing linear guide (32) According to the required incident ratio of the translational torsional mode The calculation is as follows: ； in, , where is the axial chord length of the blade cascade; For the target reduced frequency, This is the default value; According to the formula Calculate the angular velocity of the output shaft of the drive component. , The chord length of the leaf cascade. The incoming flow velocity.
7. The adjustable multimodal blade cascade oscillation system for aeroelasticity experiments according to claim 2, characterized in that, The outer surface of the first linear guide (12) is provided with a scale. The scale of the first linear guide (12) increases along the length direction of the first linear guide (12) towards the outer ring of the turntable (11) with the axis of the turntable (11) as the zero scale.
8. The adjustable multimodal blade cascade oscillation system for aeroelasticity experiments according to claim 1, characterized in that, The outer surface of the swing linear guide (32) is provided with a scale, and the scale of the swing linear guide (32) increases from the axis of the hinge seat (31) as the zero scale along the length direction of the swing linear guide (32) to the other end.