CN114112352A - Fatigue test method for tail-rising buffer strut joint - Google Patents

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

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CN114112352A
CN114112352A CN202111382157.1A CN202111382157A CN114112352A CN 114112352 A CN114112352 A CN 114112352A CN 202111382157 A CN202111382157 A CN 202111382157A CN 114112352 A CN114112352 A CN 114112352A
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test
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CN114112352B (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
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Abstract

The application provides a fatigue test method for a tail-start buffer strut joint, which comprises the following steps: obtaining a first test primary load F of the cushion strut joint body according to the S-N curve of the cushion strut joint body material1(ii) a Acquiring a second test primary load F of the joint-fuselage connection structure according to the S-N curve and the failure mode of the joint-fuselage connection structure material2(ii) a According to the first test primary load F1And a second test primary load F2Calculating the primary load of the comprehensive test; establishing a finite element model of a test piece; setting boundary constraint conditions of the finite element model; according to the finite element model, acquiring the constraint counter force of the connection area of the test piece and the clamp by utilizing the primary load of the comprehensive test, calculating the strength of the connection area according to the constraint counter force of the connection area of the test piece and the clamp,determining the thickness of a connecting area of the test piece and the clamp; and determining the final state of the test piece according to the thickness of the connection area of the test piece and the clamp so as to carry out fatigue test on the test piece.

Description

Fatigue test method for tail-rising buffer strut joint
Technical Field
The invention belongs to the field of fatigue test design of an important joint of a helicopter, and relates to a fatigue test method for a tail-lift buffer strut joint.
Background
When developing the fatigue characteristic test of the important joint on the helicopter, the traditional design idea is as follows: the machine body structure connected with the important connector on the machine is not used as an examination piece, and the important connector on the machine is directly and independently used as a test piece and fixed on a test bed through a connecting bolt. And the structural rigidity of the machine body connected with the important connector on the machine can directly influence the distribution condition of the connector load, 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 application provides a fatigue test method for a tail-start buffer support joint, which can ensure the accuracy and reliability of test results.
The application provides a fatigue test method for a tail-start buffer strut joint, which comprises the following steps:
obtaining a first test primary load F of the cushion strut joint body according to the S-N curve and the failure mode of the cushion strut joint body material1；
Acquiring a second test primary load F of the joint-fuselage connection structure according to the S-N curve and the failure mode of the joint-fuselage connection structure material2；
According to the first test primary load F1And a second test primary load F2Calculating the primary load of the comprehensive test;
establishing a finite element model of a test piece;
setting boundary constraint conditions of the finite element model;
according to the finite element model, acquiring the load of a connecting area between a test piece and a clamp and the strength of the connecting area by utilizing the comprehensive test primary load;
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 connection area of the test piece and the clamp so as to carry out fatigue test on the test piece.
Specifically, a first test of the cushion post joint body is obtained from the S-N curve of the cushion post joint body materialPrimary load F1The method specifically comprises the following steps:
acquiring a fatigue working condition load F, and acquiring a corresponding stress value sigma of the joint body according to a strength analysis result;
determining an equivalent stress value according to preset cycle times by utilizing an S-N curve of a buffering strut joint body material;
according to the equivalent stress value, utilizing an equivalent stress calculation formula to calculate and obtain the static stress sigmasAnd dynamic stress σd；
Obtaining the maximum stress sigma according to the sum of the static stress and the dynamic stressmax；
According to the fatigue working condition load F and the maximum stress sigmamaxThe stress value sigma of the joint body by using the formula
Figure BDA0003364091450000021
Calculating to obtain a first test primary load F of the buffer strut joint body1。
Specifically, a second test primary load F of the joint-fuselage connection structure is obtained according to an S-N curve and a failure mode of the joint-fuselage connection structure material2The 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 connecting bolt hole failure mode is an ablation mode, and an equivalent stress value is determined according to preset cycle times by utilizing an S-N curve of a connecting structure material of the joint and the machine body;
calculating to obtain static stress and dynamic stress by using an equivalent stress calculation formula according to the equivalent stress value;
obtaining the maximum stress sigma of the connection structure of the joint and the machine body according to the sum of the static stress and the dynamic stressmax；
According to the fatigue working condition load F and the maximum stress sigmamaxBolt hole edge stress sigma, using the formula
Figure BDA0003364091450000022
Is calculated to obtainSecond test primary load F of joint-to-fuselage connection2。
Specifically, the preset cycle number is 100 ten thousand.
In particular, according to a first test primary load F1And a second test primary load F2And calculating the primary load of the comprehensive test, which specifically comprises the following steps:
according to the first test primary load F1And a second test primary load F2And calculating the comprehensive test primary load, comprising the following steps: if F1>F2According to a first test primary load F1And a second test primary load F2Using the formula
Figure BDA0003364091450000031
And calculating the primary load of the comprehensive test.
Specifically, establishing a finite element model of the test piece specifically includes:
simulating a joint and a middle frame beam of a machine body connecting structure by using a body unit;
simulating composite material skin and connecting angle bars by using a shell unit;
multi-point constrained MPC (Multi-pointendo constraints) and beam unit mock bolted connections were created.
Specifically, setting the boundary constraint conditions of the finite element model includes:
acquiring a real stress state and a load transfer path of a joint and machine body connecting structure;
and setting a boundary constraint condition of the finite element model according to the real stress state and the load transmission path of the machine body connecting structure.
Specifically, an S-N curve, also called a stress-life curve, of a material of the joint body of the buffer strut is a curve representing a relationship between fatigue strength and fatigue life of a standard test piece under a certain cycle characteristic with fatigue strength of the material standard test piece as a ordinate and a logarithmic value lg N of the fatigue life as an abscissa.
An S-N curve, also called a stress-life curve, of a material of a joint and body connection structure is a curve which takes the fatigue strength of a material standard test piece as a vertical coordinate and takes a logarithmic value lg N of the fatigue life as a horizontal coordinate and expresses the relationship between the fatigue strength and the fatigue life of the standard test piece under certain cycle characteristics.
In summary, the application provides a fatigue test method for an important connector on a machine, 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 the rationality of the fatigue test result are ensured; and acquiring the safety fatigue limit, the average fatigue limit and the 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 diagram of a tail-start buffer strut joint provided in the present application.
Detailed Description
This application is for can accurate simulation tail play buffering pillar joint true stress state, load transfer and diffusion in actual installation, and the organism structure that will connect develops fatigue characteristic test as accompanying the test piece. And taking the production period of the test piece, the cost and the joint load diffusion area into consideration, and cutting out part of the body structure connected with the joint to be used as a test piece. And designing the rigidity of the test piece and determining the installation scheme of the test piece by taking the stress distribution level of the connection area of the buffer strut joint and the machine body structure as a target.
The application provides a fatigue test method for a tail-start buffer strut joint, which comprises the following steps of:
step 101: obtaining a first test primary load F of the cushion strut joint body according to the S-N curve of the cushion strut joint body material1；
Specifically, a first test primary load F of the cushion strut joint body is obtained according to the S-N curve and the failure mode of the cushion strut joint body material1The method comprises the following steps:
step 1011: acquiring a fatigue working condition load F, and acquiring a corresponding stress value sigma of the joint body according to a strength analysis result;
it should be noted that the fatigue condition load F is a load condition with the largest static stress in multiple fatigue conditions.
Step 1012: if the joint body failure mode is the non-fretting mode, determining an equivalent stress value by utilizing an S-N curve of the joint body material of the buffer strut according to the preset cycle number;
wherein the preset cycle number is 100 ten thousand.
The S-N curve of the material of the buffer strut joint body, also called a stress-life curve, is a curve which takes the fatigue strength of a material standard test piece as a vertical coordinate and takes the logarithmic value lg N of the fatigue life as a horizontal coordinate and expresses the relation between the fatigue strength and the fatigue life of the standard test piece under certain cycle characteristics.
Step 1013: calculating to obtain static stress and dynamic stress by using an equivalent stress calculation formula according to the equivalent stress value;
wherein the equivalent stress is calculated by the formula
Figure BDA0003364091450000041
Step 1014: obtaining the maximum stress sigma according to the sum of the static stress and the dynamic stressmax；
Step 1015: according to the fatigue working condition load F and the maximum stress sigmamaxThe stress value sigma of the joint body by using the formula
Figure BDA0003364091450000042
Calculating to obtain a first test primary load F of the buffer strut joint body1。
It is necessary to supplement that the material of the buffer strut joint body is high-strength steel, the joint body failure mode is non-fretting corrosion (A-), and according to the average S-N curve of the joint material, when the cycle number is 100 ten thousand, the equivalent stress value is obtained. For high strength steels, the equivalent stress calculation formula is known and the static stress σ is consideredsAnd dynamic stress sigmadEquality, calculating to obtain static stress (or dynamic stress), maximum stress sigmamaxEqual to the sum of the static stress and the dynamic stress, i.e. 2 times the static stress (or dynamic stress). From the results of the fatigue strength analysis, it is found that: the fatigue working condition load F with the maximum static stress and the corresponding stress value sigma of the joint body are calculated according to the equation:
Figure BDA0003364091450000051
can acquire experimental primary load F of joint body1。
TABLE 1 fatigue load schematic of strut joint at certain tail start
Figure BDA0003364091450000052
Step 102: acquiring a second test primary load F of the joint-fuselage connection structure according to the S-N curve and the failure mode of the joint-fuselage connection structure material2；
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;
it should be noted that the fatigue condition load F is a load condition with the largest static stress in multiple fatigue conditions.
Step 1022: if the connecting bolt hole failure mode is the mode with the ablation, determining an equivalent stress value according to the preset cycle times by utilizing an S-N curve of a connecting structure material of the joint and the machine body;
wherein the preset cycle number is 100 ten thousand.
The S-N curve of the material of the connecting structure of the joint and the machine body, which is also called a stress-life curve, is a curve which takes the fatigue strength of a material standard test piece as a vertical coordinate and takes a logarithmic value lg N of the fatigue life as a horizontal coordinate and expresses the relation between the fatigue strength and the fatigue life of the standard test piece under certain cycle characteristics.
Step 1023: calculating to obtain static stress and dynamic stress by using an equivalent stress calculation formula according to the equivalent stress value;
wherein the equivalent stress is calculated by the formula
Figure BDA0003364091450000061
Step 1024: obtaining the maximum stress sigma of the connection structure of the joint and the machine body according to the sum of the static stress and the dynamic stressmax；
Step 1025: according to the fatigue working condition load F and the maximum stress sigmamaxBolt hole edge stress sigma, using the formula
Figure BDA0003364091450000062
Calculating to obtain a second test primary load F of the joint and fuselage connection structure2。
It is added that the material of the connecting structure of the joint and the machine body is 7050-T7451, the failure mode of the connecting bolt hole is the friction (D +), and the equivalent stress value is obtained when the cycle number is 100 ten thousand according to the average S-N curve of the material of the joint. For aluminum alloys, the equation for equivalent stress calculation is known and the static stress σ is consideredsAnd dynamic stress sigmadEquality, calculating to obtain static stress (or dynamic stress), maximum stress sigmamaxEqual to the sum of the static stress and the dynamic stress, i.e. 2 times the static stress (or dynamic stress). Knowing a certain fatigue working condition load F, calculating the bolt hole edge stress sigma by applying an engineering method, and according to the equation:
Figure BDA0003364091450000063
can acquire experimental primary load F that connects with organism2。
Step 103: according to the first test primary load F1And a second test primary load F2Calculating the primary load of the comprehensive test;
in particular, according to a first test primary load F1And a second test primary load F2And calculating the comprehensive test primary load, comprising the following steps: if F1>F2According to a first test primary load F1And a second test primary load F2Using the formula
Figure BDA0003364091450000064
And calculating the primary load of the comprehensive test.
The cushion strut joint tabs always receive in-plane axial compressive loads and have no side load components, so the tabs do not have the fatigue failure problem.
Step 104: establishing a finite element model of a test piece;
specifically, a body unit is utilized to simulate a joint and a middle frame beam of a machine body connecting structure; simulating composite material skin and connecting angle bars by using a shell unit; multi-point constrained MPC (Multi-pointendo constraints) and beam unit mock bolted connections were created.
Considering the load diffusion area of the buffer strut joint, a part of the body connecting structure is cut out to be used as an analysis object together with the joint, and the composite material skin is connected with the test fixture through a connecting angle.
Step 105: setting boundary constraint conditions of the finite element model;
in practical application, the setting of the boundary constraint condition of the finite element model comprises the following steps:
acquiring a real stress state and a load transfer path of a joint and machine body connecting structure; and setting a boundary constraint condition of the finite element model according to the real stress state and the load transmission path of the machine body connecting structure.
Step 106: according to the finite element model, acquiring the load of a connecting area between a test piece and a clamp and the strength of the connecting area by utilizing the comprehensive test primary load;
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 connection area of the test piece and the clamp so as to carry out fatigue test on the test piece.
The test piece is fixed on the test bed through a connecting bolt, and test load is applied through the tail buffer strut dummy piece.
In summary, the application provides a fatigue test method for an important connector on a machine, 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 the rationality of the fatigue test result are ensured; and acquiring the safety fatigue limit, the average fatigue limit and the service life curve of the structure of the important joint on the machine according to the fatigue test data.

Claims (8)

1. A tail-start buffer strut joint fatigue test method, characterized in that the method comprises:
obtaining a first test primary load F of the cushion strut joint body according to the S-N curve of the cushion strut joint body material1；
Acquiring a second test primary load F of the joint-fuselage connection structure according to the S-N curve and the failure mode of the joint-fuselage connection structure material2；
According to the first test primary load F1And a second test primary load F2Calculating the primary load of the comprehensive test;
establishing a finite element model of a test piece;
setting boundary constraint conditions of the finite element model;
according to the finite element model, acquiring the load of a connecting area of a test piece and a clamp by utilizing the primary load of the comprehensive test, and calculating 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 connection area of the test piece and the clamp so as to carry out fatigue test on the test piece.
2. The method of claim 1, wherein the first test primary load F of the cushion strut joint body is obtained from an S-N curve of the cushion strut joint body material1The method specifically comprises the following steps:
acquiring a fatigue working condition load F, and acquiring a corresponding stress value sigma of the joint body according to a strength analysis result;
determining an equivalent stress value according to preset cycle times by utilizing an S-N curve of a buffering strut joint body material;
calculating to obtain static stress and dynamic stress by using an equivalent stress calculation formula according to the equivalent stress value;
obtaining the maximum stress sigma according to the sum of the static stress and the dynamic stressmax；
According to the fatigue working condition load F,Maximum stress sigmamaxThe stress value sigma of the joint body by using the formula
Figure FDA0003364091440000011
Calculating to obtain a first test primary load F of the buffer strut joint body1。
3. Method according to claim 1, characterized in that the second test primary load F of the joint-to-fuselage connection is obtained from the S-N curve and the failure mode of the material of the joint-to-fuselage connection2The 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 connecting bolt hole failure mode is an ablation mode, and an equivalent stress value is determined according to preset cycle times by utilizing an S-N curve of a connecting structure material of the joint and the machine body;
calculating to obtain static stress and dynamic stress by using an equivalent stress calculation formula according to the equivalent stress value;
obtaining the maximum stress sigma of the connection structure of the joint and the machine body according to the sum of the static stress and the dynamic stressmax；
According to the fatigue working condition load F and the maximum stress sigmamaxBolt hole edge stress sigma, using the formula
Figure FDA0003364091440000021
Calculating to obtain a second test primary load F of the joint and fuselage connection structure2。
4. The method of claim 1, wherein the predetermined number of cycles is 100 ten thousand.
5. Method according to claim 1, characterized in that the primary load F is determined according to a first test1And a second test primary load F2And calculating the primary load of the comprehensive test, which specifically comprises the following steps:
according to the first experimental elementary stageLoad F1And a second test primary load F2And calculating the comprehensive test primary load, comprising the following steps: if F1>F2According to a first test primary load F1And a second test primary load F2Using the formula
Figure FDA0003364091440000022
And calculating the primary load of the comprehensive test.
6. The method of claim 1, wherein establishing a finite element model of the test piece comprises:
simulating a joint and a middle frame beam of a machine body connecting structure by using a body unit;
simulating composite material skin and connecting angle bars by using a shell unit;
multi-point constrained MPC (Multi-pointendo constraints) and beam unit mock bolted connections were created.
7. The method of claim 1, wherein setting boundary constraints for the finite element model comprises:
acquiring a real stress state and a load transfer path of a joint and machine body connecting structure;
and setting a boundary constraint condition of the finite element model according to the real stress state and the load transmission path of the machine body connecting structure.
8. The method of claim 1,
and the S-N curve represents a curve of the relation between the fatigue strength and the fatigue life of the standard test piece under a certain cycle characteristic by taking the fatigue strength of the material standard test piece as a vertical coordinate and taking a logarithmic value lgN of the fatigue life as a horizontal coordinate.
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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20110061732A (en) * 2009-12-02 2011-06-10 대경테크 주식회사 Total test system for power steering device of dust cover
CN106768921A (en) * 2016-11-29 2017-05-31 中国直升机设计研究所 A kind of tail undercarriage rocking arm erection joint fatigue experimental device
CN110688708A (en) * 2019-09-26 2020-01-14 中国航空工业集团公司西安飞机设计研究所 Ground load spectrum compiling method based on multi-support undercarriage
CN111079329A (en) * 2019-12-04 2020-04-28 中国直升机设计研究所 Fatigue life assessment method based on similar structure test
CN112182756A (en) * 2020-09-25 2021-01-05 中国直升机设计研究所 Fatigue test design method for main landing gear buffer strut joint
CN112733267A (en) * 2020-12-30 2021-04-30 中国特种飞行器研究所 Design method and device for advanced reinforced structural component-level test piece
CN113420366A (en) * 2021-04-20 2021-09-21 中国直升机设计研究所 Method for verifying bonding strength of blade anti-icing and deicing heating assembly
CN113515810A (en) * 2021-05-17 2021-10-19 中车长春轨道客车股份有限公司 Motor train unit bogie design and development method based on reliability and safety analysis

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20110061732A (en) * 2009-12-02 2011-06-10 대경테크 주식회사 Total test system for power steering device of dust cover
CN106768921A (en) * 2016-11-29 2017-05-31 中国直升机设计研究所 A kind of tail undercarriage rocking arm erection joint fatigue experimental device
CN110688708A (en) * 2019-09-26 2020-01-14 中国航空工业集团公司西安飞机设计研究所 Ground load spectrum compiling method based on multi-support undercarriage
CN111079329A (en) * 2019-12-04 2020-04-28 中国直升机设计研究所 Fatigue life assessment method based on similar structure test
CN112182756A (en) * 2020-09-25 2021-01-05 中国直升机设计研究所 Fatigue test design method for main landing gear buffer strut joint
CN112733267A (en) * 2020-12-30 2021-04-30 中国特种飞行器研究所 Design method and device for advanced reinforced structural component-level test piece
CN113420366A (en) * 2021-04-20 2021-09-21 中国直升机设计研究所 Method for verifying bonding strength of blade anti-icing and deicing heating assembly
CN113515810A (en) * 2021-05-17 2021-10-19 中车长春轨道客车股份有限公司 Motor train unit bogie design and development method based on reliability and safety analysis

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
闫宇飞 等: "柔性起落架间隙型摆振动力学分析", 《科学技术与工程》, vol. 21, no. 14, pages 6057 - 6061 *

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