CN114739615A - Method for measuring vibration fatigue damage of metal material structure in airplane test - Google Patents

Method for measuring vibration fatigue damage of metal material structure in airplane test Download PDF

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CN114739615A
CN114739615A CN202210661484.9A CN202210661484A CN114739615A CN 114739615 A CN114739615 A CN 114739615A CN 202210661484 A CN202210661484 A CN 202210661484A CN 114739615 A CN114739615 A CN 114739615A
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elastic wave
metal material
calculating
vibration fatigue
fatigue damage
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黄文超
马君峰
李凯翔
代承霖
王纯
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AVIC Aircraft Strength Research Institute
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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
    • G01M7/00—Vibration-testing of structures; Shock-testing of structures
    • G01M7/02—Vibration-testing by means of a shake table
    • 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
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
    • G01M5/0066—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by exciting or detecting vibration or acceleration
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M7/00—Vibration-testing of structures; Shock-testing of structures
    • G01M7/02—Vibration-testing by means of a shake table
    • G01M7/025—Measuring arrangements
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/04—Analysing solids
    • G01N29/07—Analysing solids by measuring propagation velocity or propagation time of acoustic waves

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Abstract

The invention relates to the technical field of airplane testing, and particularly discloses a method for measuring vibration fatigue damage of a metal material structure in airplane testing, which comprises the following steps: s1, setting an elastic wave excitation point and an elastic wave receiving point on the surface of the detection component; applying elastic waves to the elastic wave excitation points by adopting an elastic wave applying device; s2, receiving the elastic waves transmitted from the interior of the material of the component to be tested at an elastic wave receiving point by adopting a receiving device; s3, calculating the propagation velocity of the elastic wave, and calculating the propagation velocity of the elastic wave according to the measured distance and the detected time; s4, calculating the rigidity parameter of the metal material of the detection part under the corresponding timeE(ii) a S5 stiffness parameter from S4ECalculating thermodynamic internal variablesInjury of the skinD(ii) a The method solves the problem of measuring the thermodynamic internal variable damage in the vibration fatigue damage test of the metal material structure, and can ensure accurate vibration fatigue damage evaluation on the metal material.

Description

Method for measuring vibration fatigue damage of metal material structure in airplane test
Technical Field
The invention relates to the technical field of airplane testing, in particular to a method for measuring vibration fatigue damage of a metal material structure in airplane testing.
Background
In the field of airplane testing, structural vibration fatigue damage testing is performed on metal materials applied to airplane structures, and is an extremely important task, and fatigue damage measurement is a key for evaluating the fatigue life of mechanical structures. The traditional fatigue damage is based on the stress-life curve of the measured material or component, i.e. the S-N curve; defining damage as a ratio of the number of cycles at a certain stress level to the lifetime at that stress level; the damage at different stress levels is simply summed and when the total damage reaches 1, the material or structure is considered to be failed.
This method of the prior art does not relate to the mechanism of damage of the material during vibration fatigue, and therefore the assessment of damage does not represent the degree of damage of the actual material; the damage defined based on continuous damage mechanics is a thermodynamic internal variable, and the physical meaning is the reduction of the effective bearing area of the material infinitesimal; the definition reflects the microscopic mechanism of material damage to a certain extent and can better evaluate the damage degree of the material; however, because the damage defined by the method is a thermodynamic internal variable, no one in the airplane test of the prior art researches the thermodynamic internal variable of the metal material in the vibration fatigue damage test of the metal material structure, and no one in the vibration fatigue test tests performs experimental measurement on the thermodynamic internal variable damage of the metal material.
Therefore, in order to ensure accurate vibration fatigue damage assessment of metal material structures in aircraft testing, a new method for vibration fatigue damage assessment based on the microscopic mechanism of material damage is needed.
Disclosure of Invention
Aiming at the technical problems, the invention provides a method for measuring the vibration fatigue damage of the metal material structure in the airplane test, which solves the measurement problem of the internal variable damage of thermodynamics in the vibration fatigue damage test of the metal material structure and can ensure that the metal material is accurately evaluated by the vibration fatigue damage.
The technical scheme of the invention is as follows: the method for measuring the vibration fatigue damage of the metal material structure in the airplane test comprises the following steps:
s1, applying elastic wave
Setting an elastic wave excitation point and an elastic wave receiving point on the surface of the detection component; applying elastic waves to the elastic wave excitation points by adopting an elastic wave applying device;
s2 collecting elastic waves
Receiving elastic waves transmitted from the interior of the material of the component to be tested at an elastic wave receiving point by using a receiving device;
s3, calculating the propagation velocity of the elastic wave
Measuring the distance between the elastic wave excitation point and the elastic wave receiving point; detecting the time from an elastic wave excitation point to an elastic wave receiving point; calculating the propagation speed of the elastic wave according to the measured distance and the detected time;
s4, calculating the rigidity parameter at the corresponding wave velocity
Calculating the rigidity parameter of the metal material of the detection component at the corresponding time according to the propagation speed of the elastic wave at a certain moment and the material parameter of the metal material of the detection componentE；
S5, calculating the damage of the thermodynamic internal variableD
According to the rigidity parameter of the detection part under the condition that the metal material is not damagedE 0 And the stiffness parameter obtained in step S4ECalculating to obtain the thermodynamic internal variable damage of the metal material at the corresponding timeD。
Further, repeating the steps S1-S5 in the vibration fatigue damage test process, and recording the vibration cycle times to obtain the thermodynamic internal variable damage in the metal material of the detection partDVariation curve of vibration cycle number and internal rigidity parameter of metal materialEA variation curve with the number of vibration cycles; can solve the problem of thermodynamic internal variable damageDThe method can provide damage data based on tests for the vibration fatigue life evaluation of the mechanical structure in the aircraft test.
Go toThe material parameter in step S4 is densityρAnd poisson ratioν(ii) a Calculating rigidity parameters at different wave speeds through density and Poisson ratio of metal materialERealize the pair of stiffness parametersEDynamic measurement of (2).
Further, the step S3 calculates the propagation velocity of the elastic wave as the longitudinal wave velocity of the elastic wave
Figure DEST_PATH_IMAGE002
；
Step S4 calculating the corresponding longitudinal wave velocity
Figure 252850DEST_PATH_IMAGE002
Stiffness parameter ofE L Comprises the following steps:
Figure DEST_PATH_IMAGE004
。
further, the step S3 calculates the propagation velocity of the elastic wave as the transverse wave velocity of the elastic wave
Figure DEST_PATH_IMAGE006
；
Step S4 calculating corresponding shear wave velocity
Figure 966728DEST_PATH_IMAGE006
Lower stiffness parameterE T Comprises the following steps:
Figure DEST_PATH_IMAGE008
。
further, step S5 calculates the thermodynamic internal variable damageDThe formula of (1) is:
Figure DEST_PATH_IMAGE010
。
further, the elastic wave applying device is an ultrasonic wave emitting device.
Further, the receiving device is an acoustic wave monitoring device.
The elastic waves can be accurately measured by the ultrasonic wave transmitting device and the sound wave monitoring device.
Furthermore, the metal material of the detection part is any one of aluminum alloy, steel, copper and titanium alloy.
The invention has the beneficial effects that: compared with the prior art, the method for measuring the vibration fatigue damage of the metal material structure in the airplane test solves the problem of measuring the internal thermodynamic variable damage in the vibration fatigue damage test of the metal material structure of the airplane, and can ensure that the metal material of the airplane is accurately evaluated in the vibration fatigue damage; according to the method, the rigidity parameter of the metal material of the airplane under the vibration fatigue damage test is obtained through the propagation rate of the elastic wave, and further the thermodynamic internal variable loss D can be obtained through the rigidity parameter; the method can obtain the change rule of the internal rigidity parameter of the metal material of the airplane along with the damage D of the internal thermodynamic variable; damage data based on a vibration fatigue damage test can be provided for mechanical structure vibration fatigue life evaluation in an airplane test; therefore, the accurate vibration fatigue damage assessment of the metal material of the airplane is realized.
Drawings
FIG. 1 is a flow chart of a vibration fatigue damage measurement method of the present invention;
FIG. 2 is a schematic diagram of the arrangement of an elastic wave excitation point and an elastic wave receiving point in the vibration fatigue damage measurement of the present invention;
FIG. 3 shows the thermodynamic internal variable damage in example 1 of the present inventionDA variation curve with the number of vibration cycles;
FIG. 4 shows stiffness parameters of example 2 of the present inventionE T A variation curve with the number of vibration cycles;
wherein, the device comprises a 1-elastic wave excitation point, a 2-elastic wave receiving point, a 3-elastic wave applying device and a 4-receiving device.
Detailed Description
Example 1
The method for measuring the vibration fatigue damage of the metal material structure in the airplane test as shown in the figures 1 and 2 comprises the following steps:
s1, applying elastic wave
Setting an elastic wave excitation point 1 and an elastic wave receiving point 2 on the surface of a detection component; applying elastic waves to the elastic wave excitation point 1 by using an elastic wave applying device 3;
the metal material of the detection part is aluminum alloy;
the elastic wave applying device 3 is an ultrasonic wave emitting device;
s2 collecting elastic waves
Receiving elastic waves transmitted from the interior of the material of the component to be detected at an elastic wave receiving point 2 by using a receiving device 4;
the receiving device 4 is a sound wave monitoring device;
s3, calculating the propagation velocity of the elastic wave
Measuring the distance between an elastic wave excitation point 1 and an elastic wave receiving point 2; detecting the time from an elastic wave excitation point 1 to an elastic wave receiving point 2; calculating the propagation speed of the elastic wave according to the measured distance and the detected time;
calculating to obtain the longitudinal wave velocity of the elastic wave with the propagation velocity of the elastic wave
Figure 41738DEST_PATH_IMAGE002
；
S4, calculating the rigidity parameter at the corresponding wave velocity
Calculating the rigidity parameter of the metal material of the detection component under the corresponding time according to the propagation speed of the elastic wave and the material parameter of the metal material of the detection component at a certain momentE；
The material parameter being densityρAnd poisson ratioν；
Calculating the wave velocity of corresponding longitudinal wave
Figure 702526DEST_PATH_IMAGE002
Lower stiffness parameterE L Comprises the following steps:
Figure 516899DEST_PATH_IMAGE004
s5, calculating the damage of the thermodynamic internal variableD
According to the detection of metal material of the componentStiffness parameter under damageE 0 And the stiffness parameter obtained in step S4E L Calculating to obtain the thermodynamic internal variable damage of the metal material at the corresponding timeD；
Calculating thermodynamic internal variable damageDThe formula of (1) is:
Figure DEST_PATH_IMAGE012
as shown in fig. 3, repeating the steps S1-S5 in the vibration fatigue damage test process, and recording the vibration cycle number to obtain the internal thermodynamic internal variable damage of the metal material of the detection componentDA variation curve with the number of vibration cycles; and different thermodynamic internal variable damages are obtained by adjusting the stress S of the damaged partDA variation curve with the number of vibration cycles.
Example 2
The method for measuring the vibration fatigue damage of the metal material structure in the airplane test as shown in the figures 1 and 2 comprises the following steps:
s1, applying elastic wave
Setting an elastic wave excitation point 1 and an elastic wave receiving point 2 on the surface of a detection component; applying elastic waves to the elastic wave excitation point 1 by using an elastic wave applying device 3;
the metal material of the detection part is titanium alloy;
the elastic wave applying device 3 is an ultrasonic wave emitting device;
s2 collecting elastic waves
Receiving elastic waves transmitted from the interior of the material of the component to be detected at an elastic wave receiving point 2 by using a receiving device 4;
the receiving device 4 is a sound wave monitoring device;
s3, calculating the propagation velocity of the elastic wave
Measuring the distance between an elastic wave excitation point 1 and an elastic wave receiving point 2; detecting the time from an elastic wave excitation point 1 to an elastic wave receiving point 2; calculating the propagation speed of the elastic wave according to the measured distance and the detected time;
calculating the propagation velocity of the elastic wave as the elastic waveTransverse wave velocity of
Figure 870520DEST_PATH_IMAGE006
；
S4, calculating the rigidity parameter at the corresponding wave velocity
Calculating the rigidity parameter of the metal material of the detection component at the corresponding time according to the propagation speed of the elastic wave at a certain moment and the material parameter of the metal material of the detection componentE；
The material parameter being densityρAnd poisson's ratioν；
Corresponding to the wave velocity of the transverse wave
Figure 403132DEST_PATH_IMAGE006
Lower stiffness parameterE T Comprises the following steps:
Figure 867611DEST_PATH_IMAGE008
s5, calculating the damage of the thermodynamic internal variableD
According to the rigidity parameter of the detection part under the condition that the metal material is not damagedE 0 And the stiffness parameter obtained in step S4E T Calculating to obtain the thermodynamic internal variable damage of the metal material at the corresponding timeD；
Calculating thermodynamic internal variable damageDThe formula of (1) is:
Figure DEST_PATH_IMAGE014
as shown in fig. 4, repeating the steps S1-S5 in the vibration fatigue damage test process, and recording the vibration cycle number to obtain the internal stiffness parameter of the metal materialE T Obtaining different rigidity parameters by adjusting the stress S of the damaged part according to the change curve of the vibration cycle timesE T A variation curve with the number of vibration cycles.
Example 3
The difference from the embodiment 1 is that: the metal material of the detection part is steel.
Example 4
The difference from the embodiment 1 is that: the metal material of the detection part is copper.

Claims (8)

1. The method for measuring the vibration fatigue damage of the metal material structure in the airplane test is characterized by comprising the following steps of:
s1, applying elastic wave
Setting an elastic wave excitation point (1) and an elastic wave receiving point (2) on the surface of a detection component; applying elastic waves to an elastic wave excitation point (1) by adopting an elastic wave applying device (3);
s2 collecting elastic waves
Receiving elastic waves transmitted from the interior of the material of the component to be detected at an elastic wave receiving point (2) by using a receiving device (4);
s3, calculating the propagation velocity of the elastic wave
Measuring the distance between the elastic wave excitation point (1) and the elastic wave receiving point (2); detecting the time from an elastic wave excitation point (1) to an elastic wave receiving point (2); calculating the propagation velocity of the elastic wave according to the measured distance and the detected time;
s4, calculating the rigidity parameter at the corresponding wave velocity
Calculating the rigidity parameter of the metal material of the detection component at the corresponding time according to the propagation speed of the elastic wave at a certain moment and the material parameter of the metal material of the detection componentE；
S5, calculating the damage of the thermodynamic internal variableD
According to the rigidity parameter of the detection part under the condition that the metal material is not damagedE 0 And calculating the rigidity parameter E obtained in the step S4 to obtain the thermodynamic internal variable damage of the metal material at the corresponding timeD。
2. The method for measuring the vibration fatigue damage of the metal material structure in the aircraft test as claimed in claim 1, wherein the material parameter in the step S4 is the densityρAnd poisson's ratioν。
3. The method for measuring the vibration fatigue damage of the metal material structure in the aircraft test as claimed in claim 2, wherein the step S3 is implemented by calculating the propagation velocity of the elastic wave as the longitudinal wave velocity of the elastic wave
Figure DEST_PATH_IMAGE001
；
Step S4 calculating the corresponding longitudinal wave velocity
Figure 574025DEST_PATH_IMAGE001
Lower stiffness parameterE L Comprises the following steps:
Figure 44934DEST_PATH_IMAGE002
。
4. the method for measuring the vibration fatigue damage of the metal material structure in the aircraft test as claimed in claim 1, wherein the step S3 is implemented by calculating the propagation velocity of the elastic wave as the transverse wave velocity of the elastic wave
Figure DEST_PATH_IMAGE003
；
Step S4 calculating corresponding shear wave velocity
Figure 859306DEST_PATH_IMAGE003
Lower stiffness parameterE T Comprises the following steps:
Figure 212927DEST_PATH_IMAGE004
。
5. the method for measuring vibration fatigue damage of metal material structure in airplane test as claimed in claim 1, wherein the step S5 is to calculate the damage of thermodynamic internal variablesDThe formula of (1) is:
Figure DEST_PATH_IMAGE005
。
6. the method for measuring the vibration fatigue damage of the metal material structure in the aircraft test according to claim 1, wherein the elastic wave applying device (3) is an ultrasonic wave emitting device.
7. The method for measuring the vibration fatigue damage of the metal material structure in the aircraft test according to claim 1, wherein the receiving device (4) is a sound wave monitoring device.
8. The method for measuring the vibration fatigue damage of the metal material structure in the aircraft test according to claim 1, wherein the metal material of the detection part is any one of aluminum alloy, steel, copper and titanium alloy.
CN202210661484.9A 2022-06-13 2022-06-13 Method for measuring vibration fatigue damage of metal material structure in airplane test Pending CN114739615A (en)

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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107014705A (en) * 2017-03-27 2017-08-04 太原理工大学 A kind of method and system based on sound characteristic information prediction magnesium alloy sample fatigue limit
CN108444920A (en) * 2018-01-22 2018-08-24 南京大学 A method of utilizing the intrinsic spectrum analysis method nondestructive evaluation fatigue of materials degree of optoacoustic
CN111189727A (en) * 2020-01-13 2020-05-22 长安大学 Test device and method for testing material damage
CN111208014A (en) * 2020-01-15 2020-05-29 中国石油大学(华东) Ultrasonic-based high polymer material damage in-situ testing device and method
CN112444563A (en) * 2020-11-25 2021-03-05 大连理工大学 Transverse isotropic material damage evaluation method based on ultrasonic back reflection
CN113325075A (en) * 2021-05-27 2021-08-31 浙江工业大学 Nonlinear wave detection method for high-cycle fatigue damage of metal sheet
CN113607814A (en) * 2021-07-30 2021-11-05 广东工业大学 Laser ultrasonic measurement method and system for elastic constant of metal additive manufacturing part
CN113899811A (en) * 2021-09-29 2022-01-07 安徽理工大学 Sound wave method test system for accumulative damage of coal mine tunnel rock mass

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107014705A (en) * 2017-03-27 2017-08-04 太原理工大学 A kind of method and system based on sound characteristic information prediction magnesium alloy sample fatigue limit
CN108444920A (en) * 2018-01-22 2018-08-24 南京大学 A method of utilizing the intrinsic spectrum analysis method nondestructive evaluation fatigue of materials degree of optoacoustic
CN111189727A (en) * 2020-01-13 2020-05-22 长安大学 Test device and method for testing material damage
CN111208014A (en) * 2020-01-15 2020-05-29 中国石油大学(华东) Ultrasonic-based high polymer material damage in-situ testing device and method
CN112444563A (en) * 2020-11-25 2021-03-05 大连理工大学 Transverse isotropic material damage evaluation method based on ultrasonic back reflection
CN113325075A (en) * 2021-05-27 2021-08-31 浙江工业大学 Nonlinear wave detection method for high-cycle fatigue damage of metal sheet
CN113607814A (en) * 2021-07-30 2021-11-05 广东工业大学 Laser ultrasonic measurement method and system for elastic constant of metal additive manufacturing part
CN113899811A (en) * 2021-09-29 2022-01-07 安徽理工大学 Sound wave method test system for accumulative damage of coal mine tunnel rock mass

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