CN114112352B - Fatigue test method for tail-lift buffer strut joint - Google Patents

Fatigue test method for tail-lift buffer strut joint Download PDF

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CN114112352B
CN114112352B CN202111382157.1A CN202111382157A CN114112352B CN 114112352 B CN114112352 B CN 114112352B CN 202111382157 A CN202111382157 A CN 202111382157A CN 114112352 B CN114112352 B CN 114112352B
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primary load
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CN114112352A (en
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杨婵
田中强
王召勇
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China Helicopter Research and Development 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
    • G01M13/00—Testing of machine parts
    • 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
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/0001—Type of application of the stress
    • G01N2203/0005—Repeated or cyclic
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/0058—Kind of property studied
    • G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
    • G01N2203/0073—Fatigue
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/02—Details not specific for a particular testing method
    • G01N2203/0202—Control of the test
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    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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Abstract

The application provides a fatigue test method for a tail-up buffer strut joint, which comprises the following steps: according to the S-N curve of the buffer post joint body material, a first test primary load F of the buffer post joint body is obtained 1 The method comprises the steps of carrying out a first treatment on the surface of the Obtaining a second test primary load F of the joint and body connection structure according to the S-N curve and the failure mode of the joint and body connection structure material 2 The method comprises the steps of carrying out a first treatment on the surface of the According to the first test primary load F 1 And a second test primary load F 2 Calculating the primary load of the comprehensive test; establishing a finite element model of the test piece; setting boundary constraint conditions of the finite element model; obtaining constraint counter force of the connecting area of the test piece and the clamp by utilizing the comprehensive test primary load according to the finite element model, calculating the strength of the connecting area according to the constraint counter force of the connecting area of the test piece and the clamp, and determining the thickness of the connecting area of the test piece and the clamp; and determining the final state of the test piece according to the thickness of the connecting area of the test piece and the clamp so as to perform fatigue test on the test piece.

Description

Fatigue test method for tail-lift buffer strut joint
Technical Field
The invention belongs to the field of fatigue test design of important joints of helicopters, and relates to a fatigue test method for a tail-lift buffer strut joint.
Background
When carrying out the fatigue characteristic test of important joints on a helicopter, the traditional design thought is as follows: the machine body structure connected with the on-machine important joint is not used as an examination piece, and the on-machine important joint is directly used as a test piece and is fixed on a test bed through a connecting bolt. The structural rigidity of the machine body connected with the important joint on the machine can directly influence the load distribution condition of the joint, the rigidity is not designed, the precision of the whole fatigue characteristic test can be directly influenced, and the accuracy and the reliability of the test result can not be ensured.
Disclosure of Invention
The fatigue test method for the tail-lift buffer strut joint can ensure the accuracy and reliability of test results.
The application provides a fatigue test method for a tail-up buffer strut joint, which comprises the following steps:
acquiring a first test primary load F of the buffer post joint body according to the S-N curve and the failure mode of the buffer post joint body material 1 ；
Obtaining a second test primary load F of the joint and body connection structure according to the S-N curve and the failure mode of the joint and body connection structure material 2 ；
According to the first test primary load F 1 And a second test primary load F 2 Calculating the primary load of the comprehensive test;
establishing a finite element model of the test piece;
setting boundary constraint conditions of the finite element model;
according to the finite element model, the primary load of the comprehensive test is utilized to obtain the load of the connecting area of the test piece and the clamp and the strength of the connecting area;
calculating the strength of a connecting area according to the load of the connecting area of the test piece and the clamp, and determining the thickness of the connecting area of the test piece and the clamp;
and determining the final state of the test piece according to the thickness of the connecting area of the test piece and the clamp so as to perform fatigue test on the test piece.
Specifically, according to the S-N curve of the buffer post joint body material, a first test primary load F of the buffer post joint body is obtained 1 The method specifically comprises the following steps:
acquiring a fatigue working condition load F, and acquiring a corresponding joint body stress value sigma according to a strength analysis result;
the joint body damage mode is a non-wiping mode, and an equivalent stress value is determined according to preset cycle times by utilizing an S-N curve of a buffer post joint body material;
according to the equivalent stress value, calculating to obtain static stress sigma by using an equivalent stress calculation formula s And dynamic stress sigma d ；
Obtaining the maximum stress sigma according to the sum of static stress and dynamic stress max ；
According to the fatigue condition load F and the maximum stress sigma max The stress value sigma of the joint body is calculated by using the formula
Figure BDA0003364091450000021
Calculating to obtain the first buffer post joint bodyA test primary load F 1 。
Specifically, according to the S-N curve and the failure mode of the joint and body connection structure material, a second test primary load F of the joint and body connection structure is obtained 2 The method specifically comprises the following steps:
acquiring a fatigue working condition load F, and acquiring a corresponding bolt hole edge stress sigma according to a strength analysis result;
the connection bolt hole damage mode is an etching mode, and an equivalent stress value is determined according to preset cycle times by utilizing an S-N curve of a joint and a machine body connection structure material;
according to the equivalent stress value, calculating to obtain static stress and dynamic stress by using an equivalent stress calculation formula;
obtaining the maximum stress sigma of the joint and the machine body connecting structure according to the sum of the static stress and the dynamic stress max ；
According to the fatigue condition load F and the maximum stress sigma max Bolt hole edge stress sigma, using the formula
Figure BDA0003364091450000022
Calculating a second test primary load F of the joint and fuselage connection structure 2 。
Specifically, the preset cycle number is 100 ten thousand times.
Specifically, according to the first test primary load F 1 And a second test primary load F 2 The method for calculating the comprehensive test primary load specifically comprises the following steps:
according to the first test primary load F 1 And a second test primary load F 2 Calculating a combined test primary load comprising: if F 1 >F 2 According to the first test primary load F 1 And a second test primary load F 2 Using the formula
Figure BDA0003364091450000031
The combined test primary load is calculated.
Specifically, establishing a finite element model of a test piece, which specifically comprises the following steps:
simulating a joint by using a body unit and connecting a middle frame beam of a structure by using a machine body;
simulating a composite skin and a connection angle by using the shell unit;
multi-point constrained MPCs (Multi-point constraints) and beam unit simulation bolting were created.
Specifically, setting the boundary constraint condition of the finite element model includes:
acquiring a real stress state and a load transmission path of a joint and a machine body connecting structure;
and setting boundary constraint conditions of the finite element model according to the real stress state of the engine body connecting structure and the load transmission path.
Specifically, the S-N curve of the material of the buffer post joint body, which is also called a stress-life curve, is a curve which uses the fatigue strength of a standard test piece of the material as an ordinate and uses the logarithmic value lg N of the fatigue life as an abscissa, and represents the relationship between the fatigue strength and the fatigue life of the standard test piece under a certain cycle characteristic.
The S-N curve of the material of the joint and the machine body connecting structure, which is also called a stress-life curve, is a curve which takes the fatigue strength of a standard test piece of the material as an ordinate and takes the logarithmic value lg N of the fatigue life as an abscissa, and represents the relation between the fatigue strength and the fatigue life of the standard test piece under a certain cycle characteristic.
In summary, the application provides an on-board important joint fatigue test method, which ensures that the influence of the rigidity of a machine body structure on the fatigue test precision is within an acceptable range, and the reliability and rationality of the fatigue test result; and acquiring safety fatigue limit, average fatigue limit and service life curve of the structure of the important joint on the machine according to the fatigue test data.
Drawings
Fig. 1 is a schematic structural view of a tail-up buffer strut joint provided in the present application.
Detailed Description
The fatigue characteristic test device can accurately simulate the real stress state, load transmission and diffusion of the tail-starting buffer strut joint in an actual installation machine, and takes a connected machine body structure as a test piece to develop the fatigue characteristic test. Taking the production period, cost and joint load diffusion area of the test piece into consideration, the machine body structure of the joint connection of the cut-out part is taken as a test piece. And (3) aiming at the stress distribution level of the connection area of the buffer support joint and the machine body structure, designing the rigidity of the test piece and determining the installation scheme of the test piece.
The application provides a fatigue test method for a tail-up buffer strut joint, as shown in fig. 1, the method comprises the following steps:
step 101: according to the S-N curve of the buffer post joint body material, a first test primary load F of the buffer post joint body is obtained 1 ；
Specifically, a first test primary load F of the buffer post joint body is obtained according to the S-N curve and the failure mode of the buffer post joint body material 1 Comprising:
step 1011: acquiring a fatigue working condition load F, and acquiring a corresponding joint body stress value sigma according to a strength analysis result;
the fatigue working condition load F is one of the multiple fatigue working conditions with the largest static stress.
Step 1012: if the joint body damage mode is a scratch-free mode, determining an equivalent stress value according to the preset cycle times by utilizing an S-N curve of the buffer post joint body material;
wherein the preset cycle number is 100 ten thousand times.
The S-N curve of the buffer post joint body material, which is also called a stress-life curve, is a curve which takes the fatigue strength of a standard test piece of the material as an ordinate and takes the logarithmic value lg N of the fatigue life as an abscissa, and represents the relation between the fatigue strength and the fatigue life of the standard test piece under a certain cycle characteristic.
Step 1013: according to the equivalent stress value, calculating to obtain static stress and dynamic stress by using an equivalent stress calculation formula;
wherein the equivalent stress calculation formula is as follows
Figure BDA0003364091450000041
Step 1014: according to the sum of static stress and dynamic stressObtaining the maximum stress sigma max ；
Step 1015: according to the fatigue condition load F and the maximum stress sigma max The stress value sigma of the joint body is calculated by using the formula
Figure BDA0003364091450000042
Calculating a first test primary load F of the buffer post joint body 1 。
It is to be added that the material of the buffer post joint body is high-strength steel, the joint body is damaged in a non-wiping (A-), and according to the average S-N curve of the joint material, when the cycle number is 100 ten thousand times, the equivalent stress value is obtained. For high strength steels, the equivalent stress calculation formula is known and static stress σ is considered s And dynamic stress sigma d Equal, calculate the static stress (or dynamic stress), the maximum stress sigma max Equal to the sum of the static and dynamic stresses, i.e. 2 times the static (or dynamic) stress. From the fatigue strength analysis results, it was found that: the fatigue working condition load F with the largest static stress and the corresponding joint body stress value sigma are calculated according to the equation:
Figure BDA0003364091450000051
obtaining the test primary load F of the joint body 1 。
TABLE 1 fatigue load indication for a buffer post joint from the tail
Figure BDA0003364091450000052
Step 102: obtaining a second test primary load F of the joint and body connection structure according to the S-N curve and the failure mode of the joint and body connection structure material 2 ；
Specifically, step 102 includes:
step 1021: acquiring a fatigue working condition load F, and acquiring a corresponding bolt hole edge stress sigma according to a strength analysis result;
the fatigue working condition load F is one of the multiple fatigue working conditions with the largest static stress.
Step 1022: if the connecting bolt hole damage mode is an etching mode, determining an equivalent stress value according to the preset cycle times by utilizing an S-N curve of the joint and the machine body connecting structure material;
wherein the preset cycle number is 100 ten thousand times.
The S-N curve of the material of the joint and the machine body connecting structure, which is also called a stress-life curve, is a curve which takes the fatigue strength of a standard test piece of the material as an ordinate and takes the logarithmic value lg N of the fatigue life as an abscissa, and represents the relation between the fatigue strength and the fatigue life of the standard test piece under certain cycle characteristics.
Step 1023: according to the equivalent stress value, calculating to obtain static stress and dynamic stress by using an equivalent stress calculation formula;
wherein the equivalent stress calculation formula is as follows
Figure BDA0003364091450000061
Step 1024: obtaining the maximum stress sigma of the joint and the machine body connecting structure according to the sum of the static stress and the dynamic stress max ；
Step 1025: according to the fatigue condition load F and the maximum stress sigma max Bolt hole edge stress sigma, using the formula
Figure BDA0003364091450000062
Calculating a second test primary load F of the joint and fuselage connection structure 2 。
It is to be added that the joint and machine body connecting structure material is 7050-T7451, the connecting bolt hole damage mode is the friction corrosion (D+), and according to the average S-N curve of the joint material, when the cycle time is 100 ten thousand times, the equivalent stress value is obtained. For aluminum alloys, the equivalent stress calculation formula is known and static stress σ is considered s And dynamic stress sigma d Equal, calculate the static stress (or dynamic stress), the maximum stress sigma max Equal to the sum of the static and dynamic stresses, i.e. 2 times the static (or dynamic) stress. Knowing a certain fatigue working condition load F, calculating the edge stress sigma of the bolt hole by using an engineering method, and according to the stress sigmaAccording to the equation:
Figure BDA0003364091450000063
test primary load F for obtaining connection of joint and machine body 2 。
Step 103: according to the first test primary load F 1 And a second test primary load F 2 Calculating the primary load of the comprehensive test;
specifically, according to the first test primary load F 1 And a second test primary load F 2 Calculating a combined test primary load comprising: if F 1 >F 2 According to the first test primary load F 1 And a second test primary load F 2 Using the formula
Figure BDA0003364091450000064
The combined test primary load is calculated.
The buffer post joint tab always bears in-plane axial compression load without side load components, so the tab has no fatigue failure problem.
Step 104: establishing a finite element model of the test piece;
specifically, a body unit is utilized to simulate a joint and a frame beam in a machine body connecting structure; simulating a composite skin and a connection angle by using the shell unit; multi-point constrained MPCs (Multi-point constraints) and beam unit simulation bolting were created.
Considering the buffer post joint load diffusion area, the cut-out part organism connecting structure and the joint are taken as analysis objects together, and the composite material skin is connected with the test fixture through the connecting angle material.
Step 105: setting boundary constraint conditions of the finite element model;
in practical application, setting the boundary constraint condition of the finite element model includes:
acquiring a real stress state and a load transmission path of a joint and a machine body connecting structure; and setting boundary constraint conditions of the finite element model according to the real stress state of the engine body connecting structure and the load transmission path.
Step 106: according to the finite element model, the primary load of the comprehensive test is utilized to obtain the load of the connecting area of the test piece and the clamp and the strength of the connecting area;
step 107: calculating the strength of a connecting area according to the load of the connecting area of the test piece and the clamp, and determining the thickness of the connecting area of the test piece and the clamp;
step 108: and determining the final state of the test piece according to the thickness of the connecting area of the test piece and the clamp so as to perform fatigue test on the test piece.
The test piece is fixed to the test stand by means of a connecting bolt, and the test load is applied by means of a tail-up buffer post dummy.
In summary, the application provides an on-board important joint fatigue test method, which ensures that the influence of the rigidity of a machine body structure on the fatigue test precision is within an acceptable range, and the reliability and rationality of the fatigue test result; and acquiring safety fatigue limit, average fatigue limit and service life curve of the structure of the important joint on the machine according to the fatigue test data.

Claims (7)

1. A method of fatigue testing a tail-out buffer strut joint, the method comprising:
according to the S-N curve of the buffer post joint body material, a first test primary load F of the buffer post joint body is obtained 1 ；
Obtaining a second test primary load F of the joint and body connection structure according to the S-N curve and the failure mode of the joint and body connection structure material 2 ；
According to the first test primary load F 1 And a second test primary load F 2 Calculating the primary load of the comprehensive test;
establishing a finite element model of the test piece;
setting boundary constraint conditions of the finite element model;
according to the finite element model, the primary load of the comprehensive test is utilized to obtain the load of the connecting area of the test piece and the clamp, and the strength of the connecting area is calculated;
calculating the strength of a connecting area according to the load of the connecting area of the test piece and the clamp, and determining the thickness of the connecting area of the test piece and the clamp;
determining the final state of the test piece according to the thickness of the connecting area of the test piece and the clamp so as to perform fatigue test on the test piece;
according to the S-N curve of the buffer post joint body material, a first test primary load F of the buffer post joint body is obtained 1 The method specifically comprises the following steps:
acquiring a fatigue working condition load F, and acquiring a corresponding joint body stress value sigma according to a strength analysis result;
the joint body damage mode is a non-wiping mode, and an equivalent stress value is determined according to preset cycle times by utilizing an S-N curve of a buffer post joint body material;
according to the equivalent stress value, calculating to obtain static stress and dynamic stress by using an equivalent stress calculation formula;
obtaining the maximum stress sigma according to the sum of static stress and dynamic stress max ；
According to the fatigue condition load F and the maximum stress sigma max The stress value sigma of the joint body is calculated by using the formula
Figure FDA0004225091030000021
Calculating a first test primary load F of the buffer post joint body 1 。
2. The method of claim 1, wherein the second test primary load F of the joint-to-fuselage connection is obtained from the S-N curve and failure mode of the joint-to-fuselage connection material 2 The method specifically comprises the following steps:
acquiring a fatigue working condition load F, and acquiring a corresponding bolt hole edge stress sigma according to a strength analysis result;
the connection bolt hole damage mode is an etching mode, and an equivalent stress value is determined according to preset cycle times by utilizing an S-N curve of a joint and a machine body connection structure material;
according to the equivalent stress value, calculating to obtain static stress and dynamic stress by using an equivalent stress calculation formula;
obtaining the maximum stress sigma of the joint and the machine body connecting structure according to the sum of the static stress and the dynamic stress max ；
According to the fatigue condition load F and the maximum stress sigma max Bolt hole edge stress sigma, using the formula
Figure FDA0004225091030000022
Calculating a second test primary load F of the joint and fuselage connection structure 2 。
3. The method of claim 1, wherein the predetermined number of cycles is 100 ten thousand.
4. The method according to claim 1, characterized in that the primary load F is based on a first test 1 And a second test primary load F 2 The method for calculating the comprehensive test primary load specifically comprises the following steps:
according to the first test primary load F 1 And a second test primary load F 2 Calculating a combined test primary load comprising: if F 1 >F 2 According to the first test primary load F 1 And a second test primary load F 2 Using the formula
Figure FDA0004225091030000023
The combined test primary load is calculated.
5. The method according to claim 1, characterized in that the finite element model of the test piece is built, in particular comprising:
simulating a joint by using a body unit and connecting a middle frame beam of a structure by using a machine body;
simulating a composite skin and a connection angle by using the shell unit;
a Multi-point constrained MPC (Multi-point constraints) and beam unit simulation bolting was created.
6. The method of claim 1, wherein setting boundary constraints of the finite element model comprises:
acquiring a real stress state and a load transmission path of a joint and a machine body connecting structure;
and setting boundary constraint conditions of the finite element model according to the real stress state of the engine body connecting structure and the load transmission path.
7. The method of claim 1, wherein the step of determining the position of the substrate comprises,
and the S-N curve takes the fatigue strength of the standard test piece of the material as an ordinate and takes the logarithmic value lgN of the fatigue life as an abscissa, and represents the relation between the fatigue strength and the fatigue life of the standard test piece under the cyclic characteristic.
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