CN114608795B - Method for determining resonance boundary of wind tunnel system for airplane blowing test - Google Patents
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
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- G06F30/15—Vehicle, aircraft or watercraft design
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
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- G—PHYSICS
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- G06F2113/00—Details relating to the application field
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
The invention relates to the technical field of airplane testing, in particular to a method for determining a resonance boundary of a wind tunnel system for airplane blowing testing, which mainly takes a lifting wind tunnel system as a research object, determines the resonance boundary of the lifting wind tunnel system by establishing a kinetic equation of the lifting wind tunnel system → constructing a finite element model of the lifting wind tunnel system → calculating the inherent frequency of the lifting wind tunnel system → determining the excitation frequency of the lifting wind tunnel system → determining the resonance boundary of the lifting wind tunnel system and combining a simulation calculation and test mode, so that the problem of resonance caused by high complexity of the lifting wind tunnel system is solved, and a safe wind speed index is provided for safe and efficient operation of the test system for airplane blowing testing.
Description
Technical Field
The invention relates to the technical field of airplane testing, in particular to a method for determining a resonance boundary of a wind tunnel system for airplane blowing testing.
Background
The wind tunnel is used as an important test device for aerodynamic research and aircraft development in the air blowing test of the airplane, and the development of any novel aircraft needs to pass numerous air blowing tests in the wind tunnel to research the aerodynamic layout, the streaming mechanism and the like.
The traditional wind tunnel system mostly adopts a structure with unadjustable height for the stability of the whole device, so that when the weather tests such as wind-rain blowing, wind-snow blowing and the like are simulated for an aircraft in a climate laboratory, the available area of a wind tunnel test section is very small, and the constraint on the weather tests is large.
In order to solve the problems, the unit designs a wind tunnel system with a lifting function, and the height between the center of the wind tunnel and the ground can be increased through an adjusting structure, so that the available area of a wind tunnel test section is greatly increased.
However, as the structure of the wind tunnel system becomes complex, the number of the connecting devices becomes large, so that the risk of resonance of the whole wind tunnel system is increased; once the fan running at high speed in the wind tunnel system resonates in the climate laboratory, the fan will cause great damage to the laboratory maintenance structure, facilities and workers.
In order to not only use the lifting wind tunnel system, but also avoid the resonance of the wind tunnel system, the natural frequency of the lifting wind tunnel system needs to be calculated; however, the main object of the current domestic wind tunnel natural frequency calculation method is a wind tunnel system with a fixed position, the kinetic equation and the related calculation method of the wind tunnel natural frequency calculation method cannot deal with the wind tunnel system with high complexity in the invention, and the calculation result and the actual test result are too large to be used as the safe wind speed index of the airplane blowing test system.
Therefore, the invention designs a resonance boundary determining method which can be suitable for the lifting wind tunnel system in a mode of simulation calculation and test, provides a safety index for a subsequent airplane blowing test system, and provides a theoretical basis for the structure optimization of the axial flow fan of the system.
Disclosure of Invention
In order to achieve the purpose, the invention provides a wind tunnel system resonance boundary determining method for an airplane blowing test, which mainly determines the resonance boundary of a lifting wind tunnel system in a simulation calculation and test mode so as to solve the problem of resonance caused by high complexity of the lifting wind tunnel system and provide a safe wind speed index for safe and efficient operation of an airplane blowing test system.
The invention discloses a method for determining a resonance boundary of a wind tunnel system for airplane blowing test, which comprises the steps of constructing a wind tunnel system kinetic equation, constructing a finite element model of the wind tunnel system, calculating natural frequency of the wind tunnel system, determining excitation frequency of the wind tunnel system and determining the resonance boundary of the wind tunnel system, wherein all the methods are around a lifting wind tunnel system and comprise the following specific contents:
s1, according to the traditional rotation disturbance motion theory, after reasonable correction, the invention establishes a dynamic equation suitable for a lifting wind tunnel system:
M * [X] + (Sc+ Sg- Se) * [X] = F(t)
in the formula: m is a mass matrix, ScIs a matrix of elastic stiffness, SgIs a gravity stress stiffness matrix; seIs a centrifugal stiffness matrix, [ X ]]F (t) is a displacement response vector of each point of the lifting wind tunnel system, and F (t) is an excitation force vector of each point of the lifting wind tunnel system;
s2, constructing a finite element model of the lifting wind tunnel system
S2-1, constructing numerical model of lifting wind tunnel system
Establishing a fan module digital model based on a lifting wind tunnel system, measuring module parameters and determining material parameters;
s2-2, constructing finite element model and meshing
Defining boundary conditions of the lifting wind tunnel system based on the displacement and the load of the lifting wind tunnel system at the lifting moment to obtain a finite element model of the lifting wind tunnel system; selecting a mesh division mode of a finite element model attached to an actual structure of the lifting wind tunnel system;
s3, calculating the natural frequency of the lifting wind tunnel system
Analyzing and calculating the ten-order natural frequency of the lifting wind tunnel system through the natural frequency in the limited state, and setting the calculation frequency range to be 0-100 Hz;
s4, determining the excitation frequency of the lifting wind tunnel system
Connecting a fan module of the lifting wind tunnel system with a frequency converter, and establishing a relation between the airflow speed and the excitation frequency of the fan module;
s5, determining resonance boundary of lifting wind tunnel system
By comparing the range of the tenth-order natural frequency of the lifting wind tunnel system, the range of the excitation frequency of the fan module and the range of the airflow wind speed, the airflow wind speed boundary capable of preventing the lifting wind tunnel system from generating resonance when the airplane is subjected to blowing test is obtained.
Furthermore, the lifting wind tunnel system consists of two vertically combined fan modules and a lifting support positioned below the fan modules;
the fan module comprises a hole body, a structural support formed by a main rib plate and an auxiliary rib plate is arranged on the inner cavity wall of the hole body, a motor with the axis of an output shaft consistent with the axis of the hole body is arranged on the structural support, the output shaft of the motor is connected with a fan arranged on one side of the hole body, and the other side, far away from the fan, of the hole body is connected with a fairing; the liftable support comprises a base and a tool joint, wherein the base is composed of square pipes, and the tool joint is used for connecting the fan module and the base.
Further, in step S2-1, the fan module digifax includes a hole body digifax, a main rib plate digifax, an auxiliary rib plate digifax, a fan digifax, a fairing digifax, a motor digifax and a liftable support digifax.
Further, in step S2-1, the module parameters include: fan module quality, fan module barycentric coordinate and fan module moment of inertia.
Further, in step S2-1, the material parameters: the model material is 304 type steel, and the density is as follows: 7930 kg/m3The modulus of elasticity: 2e11 Pa, Poisson's ratio: 0.3, base temperature: 20 ℃, thermal expansion system: 1e-5/° C;
the above material parameters were applied in and set for the following structures: a hole body: the thickness is 6 mm; main rib plate and square tube: 400 mm x 900 mm x 12 mm x 12 mm; and (4) auxiliary rib plates: 400 mm x 400 mm x 8 mm.
Further, in step S2-2, the specific content of defining the boundary condition of the lifting wind tunnel system is:
the tool joint in the lifting wind tunnel system is equivalent to a fixed structure formed by square pipes when the lifting wind tunnel system is in a lifting stage;
simplifying the correlation between the base and the foundation soil, and processing the boundary condition according to full constraint.
Further, in step S3, the tenth order natural frequency of the lifting wind tunnel system is as follows:
first-order natural frequency: 0.18076 Hz, second order natural frequency: 1.0318 Hz, third order natural frequency: 1.6661 Hz, fourth order natural frequency: 2.825 Hz, fifth order natural frequency: 5.594 Hz, sixth order natural frequency: 7.5019 Hz, seventh order natural frequency: 7.7613 Hz, eighth order natural frequency: 8.4213 Hz, ninth order natural frequency: 9.8241 Hz, tenth order natural frequency: 10.1 Hz.
Further, in step S4, the excitation frequency of the fan module corresponding to each airflow wind speed is as follows:
airflow speed: 5 m/s, excitation frequency: 4.3 Hz; airflow speed: 8 m/s, excitation frequency: 6.8 Hz; airflow wind speed: 10 m/s, excitation frequency: 8.5 Hz; airflow speed: 12 m/s, excitation frequency: 10.2 Hz; airflow wind speed: 15 m/s, excitation frequency: 12.8 Hz; airflow wind speed: 18 m/s, excitation frequency: 15.3 Hz.
Further, in step S5:
when the fan module normally operates in the test of the blowing of the airplane, the air flow speed v capable of inducing the resonance of the lifting wind tunnel system1The range of (A) is as follows: 0 m/s < v1 ＜ 8 m/s；
When the fan module normally operates in the test of the blowing of the airplane, the air flow speed v causing the resonance risk of the lifting wind tunnel system exists2The range of (A) is as follows: v is not more than 8 m/s2 ＜ 12 m/s；
When the fan module normally operates in the test of the air blowing of the airplane, the air flow speed v capable of avoiding the resonance of the lifting wind tunnel system can be avoided3The range of (A) is as follows: v. of3 ≥ 12 m/s。
Furthermore, the lifting wind tunnel system used by the invention has the height lifting adjustment range of 2 m-8 m from the center to the ground, and the highest wind speed in the horizontal direction at the position 4 m away from the wind tunnel wind port is 55 m/s; it can be seen that the lifting wind tunnel system greatly increases the available area of the wind tunnel test section by means of the lifting function.
Compared with the prior wind tunnel fan anti-resonance method, the invention has the beneficial effects that:
(1) the invention designs a wind tunnel system resonance boundary determining method for airplane blowing test, which mainly determines the resonance boundary of a lifting wind tunnel system in a mode of simulation calculation and test, so as to solve the resonance problem of the lifting wind tunnel system caused by high complexity and provide a safe wind speed index for the safe and efficient operation of the test system of the airplane blowing test; before the invention, no report for determining the resonance boundary of a liftable wind tunnel fan exists;
(2) in the design scheme of the invention, the traditional rotation disturbance motion theory is reasonably corrected, a dynamic equation suitable for a lifting wind tunnel system with high complexity is established, and theoretical support is provided for the whole scheme.
Drawings
FIG. 1 is a flow chart of a method of determining a resonant boundary of a lifting wind tunnel system according to the present invention;
FIG. 2 is a schematic structural view of a lifting wind tunnel system according to the present invention;
FIG. 3 is a finite element model diagram of a lifting wind tunnel system according to the present invention;
FIG. 4 is a first order natural frequency cloud plot of the elevating wind tunnel system of the present invention;
FIG. 5 is a second order natural frequency cloud plot of the elevating wind tunnel system of the present invention;
FIG. 6 is a third order natural frequency cloud of the elevating wind tunnel system of the present invention;
FIG. 7 is a fourth order natural frequency cloud of the elevating wind tunnel system of the present invention;
FIG. 8 is a fifth order natural frequency cloud of the elevating wind tunnel system of the present invention.
In FIG. 2: 1: fan module, 1-1: a hole body, 2: liftable support, 2-1: base, 2-2: and (5) a tooling section.
Detailed Description
To further illustrate the manner in which the present invention is made and the effects achieved, the following description of the present invention will be made in detail and completely with reference to the accompanying drawings.
Examples
The present example is intended to illustrate the application effect of the method for determining the resonance boundary of a lifting wind tunnel system according to the present invention through a specific embodiment.
1. The study subjects were: lifting wind tunnel system
Referring to fig. 2, the application object of the method for determining the resonance boundary of the wind tunnel system for the blowing test of the airplane is a lifting wind tunnel system, and the lifting wind tunnel system is composed of two vertically combined fan modules 1 and a lifting support 2 positioned below the fan modules 1;
the fan module 1 comprises a hole body 1-1, a structural support formed by a main rib plate and an auxiliary rib plate is arranged on the inner cavity wall of the hole body 1-1, a motor with an output shaft axis consistent with the axis position of the hole body 1-1 is arranged on the structural support, the output shaft of the motor is connected with a fan arranged on one side of the hole body 1-1, and the other side, far away from the fan, of the hole body 1-1 is connected with a fairing; the lifting support 2 comprises a base 2-1 formed by square pipes and a tool joint 2-2 used for connecting the fan module 1 and the base 2-1.
In addition, the lifting adjusting range of the height of the center of the lifting wind tunnel system from the ground is 2 m-8 m, the highest wind speed in the horizontal direction at the position 4 m away from the wind tunnel air port is 55 m/s, and the available area of the wind tunnel test section can be greatly increased.
2. Method for determining resonance boundary of lifting wind tunnel system
Referring to fig. 1, the resonance boundary determining method based on the lifting wind tunnel system includes the steps of constructing a system vertical dynamic equation, constructing a system finite element model, calculating a system natural frequency, determining a system excitation frequency and determining a system resonance boundary, and details of each step are as follows:
s1, according to the traditional rotation disturbance motion theory, after reasonable correction, the invention establishes a dynamic equation suitable for a lifting wind tunnel system:
M * [X] + (Sc+ Sg- Se) * [X] = F(t)
in the formula: m is a mass matrix, ScIs a matrix of elastic stiffness, SgIs a gravity stress stiffness matrix; seIs a centrifugal stiffness matrix, [ X ]]And F (t) is the vector of the excitation force of each point of the lifting wind tunnel system.
S2, constructing a finite element model of the lifting wind tunnel system
S2-1, constructing numerical model of lifting wind tunnel system
And establishing a fan module digital analog through the CATIA based on a lifting wind tunnel system, measuring module parameters and determining material parameters.
The fan module digifax comprises a hole digifax, a main rib plate digifax, an auxiliary rib plate digifax, a fan digifax, a fairing digifax, a motor digifax and a liftable support digifax.
The module parameters include: fan module quality, fan module barycentric coordinate and fan module moment of inertia.
Determining material parameters: the model material is 304 type steel, and the density is as follows: 7930 kg/m3The modulus of elasticity: 2e11 Pa, Poisson ratio: 0.3, base temperature: 20 ℃, thermal expansion system: 1 e-5/. degree.C.
The above material parameters were applied in and set for the following structures: a hole body: the thickness is 6 mm; main rib plate and square tube: 400 mm x 900 mm x 12 mm x 12 mm; and (4) auxiliary rib plates: 400 mm x 400 mm x 8 mm.
S2-2, constructing finite element model and meshing
Defining boundary conditions of the lifting wind tunnel system based on the displacement and load of the lifting wind tunnel system at the lifting moment to obtain a finite element model of the lifting wind tunnel system (see figure 3); and selecting a mesh division mode of a finite element model fitting the actual structure of the lifting wind tunnel system.
And (3) enabling the tooling joint 2-2 in the lifting wind tunnel system to be equivalent to a fixed structure formed by square pipes when the lifting wind tunnel system is in a lifting stage.
Simplifying the correlation between the base 2-1 and the foundation soil, and processing the boundary conditions according to full constraint.
S3, calculating the natural frequency of the lifting wind tunnel system
The ten-order natural frequency of the lifting wind tunnel system is analyzed and calculated through the limited state natural frequency, software Patran/Nastran is selected for calculation and solving, the calculation frequency range is set to be 0-100 Hz, and specific results are shown in table 1. (first order natural frequency cloud picture to fifth order natural frequency cloud picture of lifting wind tunnel system see figures 4 to 8)
S4, determining the excitation frequency of the lifting wind tunnel system
The relationship between the airflow speed and the excitation frequency of the fan module 1 is established by connecting the fan module 1 of the lifting wind tunnel system with a frequency converter, which is shown in table 2.
S5, determining resonance boundary of lifting wind tunnel system
By analyzing the data in tables 1 and 2, it can be seen that: the first four-order natural frequency of the lifting wind tunnel system is lower than the excitation frequency of the fan module 1, and from the fifth order to the sixth order, the natural frequency of the lifting wind tunnel system is gradually higher than the excitation frequency of the fan module 1 when the wind speed is lower than 8 m/s.
In practical application, the wind speeds of the most frequently used lifting wind tunnel systems are 15 m/s and 18 m/s, and the excitation frequency of the fan module 1 is higher than the tenth-order natural frequency at the two wind speeds; therefore, by comparing the range of the tenth order natural frequency of the lifting wind tunnel system, the range of the excitation frequency of the fan module 1 and the range of the airflow wind speed, the airflow wind speed boundary capable of avoiding the occurrence of resonance of the lifting wind tunnel system during the blowing test of the airplane is obtained:
when the fan module 1 is in normal operation in the test of airplane blowing, the air flow speed v capable of inducing the resonance of the lifting wind tunnel system1The range of (A) is as follows: 0 m/s < v1 ＜ 8 m/s；
When the fan module 1 runs normally in the test of blowing of the airplane, the air flow speed v causing the resonance risk of the lifting wind tunnel system exists2The range of (A) is as follows: v is not more than 8 m/s2 ＜ 12 m/s；
When the fan module 1 runs normally in the blowing test of the airplane, the air flow speed v capable of avoiding resonance of the lifting wind tunnel system3The range of (A) is as follows: v. of3 ≥ 12 m/s。
Namely, when the fan module 1 is normally operated in the test of the air blowing of the airplane, and the wind speed is kept to be higher than 12 m/s, the possibility of resonance of the lifting wind tunnel system is extremely low, and the safety range can be regarded. The result can be used as a test system for a subsequent airplane blowing test to provide a safe wind speed index, and can also provide a theoretical basis for the structural optimization of the axial flow fan of the system.
Claims (9)
1. A wind tunnel system resonance boundary determining method for an airplane blowing test is characterized by comprising the following steps:
the wind tunnel system is a lifting wind tunnel system;
the method comprises the following steps:
s1, establishing a dynamic equation of the lifting wind tunnel system
In the formula: m is a mass matrix, ScIs a matrix of elastic stiffness, SgIs a gravity stress stiffness matrix; seIs a centrifugal stiffness matrix, [ X ]]F (t) is a displacement response vector of each point of the lifting wind tunnel system, and F (t) is an excitation force vector of each point of the lifting wind tunnel system;
s2, constructing a finite element model of the lifting wind tunnel system
S2-1, constructing a numerical model of the lifting wind tunnel system
Establishing a fan module digital model based on the lifting wind tunnel system, measuring module parameters and determining material parameters;
s2-2, constructing finite element model and meshing
Defining boundary conditions of the lifting wind tunnel system based on the displacement and the load of the lifting wind tunnel system at the lifting moment to obtain a finite element model of the lifting wind tunnel system; selecting a mesh division mode of a finite element model fitting the actual structure of the lifting wind tunnel system;
s3, calculating the natural frequency of the lifting wind tunnel system
Calculating the tenth-order natural frequency of the lifting wind tunnel system through limited state natural frequency analysis;
s4, determining the excitation frequency of the lifting wind tunnel system
Connecting a fan module (1) of the lifting wind tunnel system with a frequency converter, and establishing a relation between the airflow speed and the excitation frequency of the fan module (1);
s5, determining the resonance boundary of the lifting wind tunnel system
By comparing the range of the ten-order natural frequency of the lifting wind tunnel system, the range of the excitation frequency of the fan module (1) and the range of the airflow wind speed, the airflow wind speed boundary capable of preventing the lifting wind tunnel system from resonating when the airplane is blown to test is obtained.
2. The method for determining the resonance boundary of the wind tunnel system for the blowing test of the airplane according to claim 1, wherein the lifting wind tunnel system consists of two vertically combined fan modules (1) and a lifting support (2) positioned below the fan modules (1);
the fan module (1) comprises a hole body (1-1), a structural support formed by a main rib plate and an auxiliary rib plate is arranged on the inner cavity wall of the hole body (1-1), a motor with an output shaft axis consistent with the axis position of the hole body (1-1) is arranged on the structural support, the output shaft of the motor is connected with a fan arranged on one side of the hole body (1-1), and the other side, far away from the fan, of the hole body (1-1) is connected with a fairing;
the lifting support (2) comprises a base (2-1) formed by square pipes and a tool joint (2-2) used for connecting the fan module (1) and the base (2-1).
3. The method for determining the resonance boundary of the wind tunnel system for the airplane blowing test according to claim 2, wherein in the step S2-1, the fan module digifax comprises a hole body digifax, a main rib plate digifax, an auxiliary rib plate digifax, a fan digifax, a fairing digifax, a motor digifax and a liftable support digifax.
4. The method for determining the resonance boundary of the wind tunnel system for the wind blowing test of the aircraft according to claim 2, wherein in the step S2-1, the module parameters comprise: the mass of the fan module, the barycentric coordinate of the fan module and the inertia moment of the fan module.
5. The method for determining the resonance boundary of the wind tunnel system for the blowing test of the aircraft according to claim 2, wherein in step S2-1, the material parameters are determined as follows:
the model material is steel alloy, and the density is as follows: 7930 kg/m3The modulus of elasticity: 2e11 Pa, Poisson ratio: 0.3, base temperature: 20 ℃, thermal expansion system: 1e-5/° C;
the above material parameters were applied in and set for the following structures: a hole body: 6mm thick, main rib plate and square pipe: 400 mm x 900 mm x 12 mm x 12 mm, vice gusset: 400 mm x 400 mm x 8 mm.
6. The method for determining the resonance boundary of the wind tunnel system for the wind blowing test of the aircraft according to claim 2, wherein in the step S2-2, the specific content for defining the boundary condition of the lifting wind tunnel system is as follows:
the tool joint (2-2) in the lifting wind tunnel system is equivalent to a fixed structure formed by square pipes when the lifting wind tunnel system is in a lifting stage;
simplifying the correlation between the base (2-1) and the foundation soil, and processing the boundary conditions according to full constraint.
7. The method for determining the resonance boundary of the wind tunnel system for the wind blowing test of the aircraft according to claim 1, wherein in step S3, the tenth-order natural frequency of the elevating wind tunnel system is as follows:
first-order natural frequency: 0.18076 Hz, second order natural frequency: 1.0318 Hz, third order natural frequency: 1.6661 Hz, fourth order natural frequency: 2.825 Hz, fifth order natural frequency: 5.594 Hz, sixth order natural frequency: 7.5019 Hz, seventh order natural frequency: 7.7613 Hz, eighth order natural frequency: 8.4213 Hz, ninth order natural frequency: 9.8241 Hz, tenth order natural frequency: 10.1 Hz.
8. The method for determining the resonance boundary of the wind tunnel system for the blowing test of the aircraft according to claim 1, wherein in the step S4, the excitation frequency of the fan module (1) corresponding to the wind speed of each airflow is as follows:
airflow wind speed: 5 m/s, excitation frequency: 4.3 Hz; airflow wind speed: 8 m/s, excitation frequency: 6.8 Hz; airflow wind speed: 10 m/s, excitation frequency: 8.5 Hz; airflow wind speed: 12 m/s, excitation frequency: 10.2 Hz; airflow wind speed: 15 m/s, excitation frequency: 12.8 Hz; airflow speed: 18 m/s, excitation frequency: 15.3 Hz.
9. The method for determining the resonance boundary of the wind tunnel system for the wind blowing test of the aircraft according to claim 1, wherein in step S5:
when the fan module (1) normally operates in an airplane blowing test, the air flow speed v capable of inducing the resonance of the lifting wind tunnel system1The range of (A) is as follows: 0 m/s < v1 ＜ 8 m/s；
When a fan module (1) normally operates in an airplane blowing test, the air flow speed v causing the resonance risk of the lifting wind tunnel system exists2The range of (A) is as follows: v is more than or equal to 8 m/s2 ＜ 12 m/s；
When the fan module (1) normally operates in an airplane blowing test, the air flow speed v of the resonance of the lifting wind tunnel system can be avoided3The range of (A) is as follows: v. of3 ≥ 12 m/s。
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