CN111122346B - Test load processing method for main structure of airfoil - Google Patents

Test load processing method for main structure of airfoil Download PDF

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CN111122346B
CN111122346B CN201911346781.9A CN201911346781A CN111122346B CN 111122346 B CN111122346 B CN 111122346B CN 201911346781 A CN201911346781 A CN 201911346781A CN 111122346 B CN111122346 B CN 111122346B
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任善
杜凯
张丽
程文杰
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AVIC First Aircraft Institute
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    • 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
    • G01N3/20—Investigating strength properties of solid materials by application of mechanical stress by applying steady bending forces
    • 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
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    • B64F5/60—Testing or inspecting aircraft components or systems
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    • 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
    • G01N3/24—Investigating strength properties of solid materials by application of mechanical stress by applying steady shearing 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
    • G01N2203/02—Details not specific for a particular testing method
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Abstract

The invention discloses a test load processing method for a main structure of an airfoil, provides a set of test load processing method and flow, provides an evaluation method, can objectively evaluate the feasibility of test loading load, ensures the loading accuracy and improves the load processing efficiency.

Description

Test load processing method for main structure of airfoil
Technical Field
The invention belongs to the technical field of aviation strength, and particularly relates to a load processing method for an airfoil main structure test.
Background
When the ground static test is carried out on the airplane structure, the theoretical load is often processed to obtain the test load convenient to implement in consideration of the enforceability of the test loading scheme, but the difference between the test load and the theoretical load brings different stress of the airplane body structure, and in order to guarantee the accuracy of force transmission and the safety of the structure, the structural stress distribution under the test load state needs to be checked, and the safety of the local structure of a loading point needs to be checked.
The above process is often a repeated iteration process, and a reasonable scheme can be found between the theoretical precision and the test implementability only by adjusting the test load for multiple times, which is time-consuming and labor-consuming, and the determination of the reasonable scheme has no uniform standard and lacks objectivity.
Disclosure of Invention
The purpose of the invention is as follows: the method comprises the steps of processing theoretical load into test load through an iteration method under the condition of limiting single-point test load for the main structure of the airfoil, checking a load bending-shearing torsion curve, displacement and stress strain to determine whether the test load is feasible, and adjusting the test load if the test load is not feasible until all requirements are met.
The technical scheme of the invention is as follows:
a test load processing method for an airfoil main structure comprises the following steps:
step 1: calculating the test load P of each test loading pointj；
Step 2: checking the test load P of each test load pointjWhether or not the allowable load P is exceededj]If the test load P of the test load point isjExceeding allowable load [ P ]j]I.e. Pj≥[Pj]The excess load amount Δ PjProcessing until the allowable loading load is not exceeded Pj]At the test load point of (a);
and step 3: repeating the step 2 until the test load P on each test loading pointjAll do not exceed allowable load [ Pj]I.e. Pj≤[Pj]；
And 4, step 4: calculating the difference delta F on each rib station profile of the bending shear in the theoretical state and the experimental statek、ΔMk、ΔJk；
And 5: calculating the difference delta u of the deflection of the front beam and the rear beam of the wing box on each rib station sectionf,kAnd Δ ur,kAnd the difference in stress Δ σ at the primary force-transmitting locationp；
Step 6: simultaneous determination of Δ Fk、ΔMkAnd Δ JkWhether or not smaller than the error allowable value epsilon respectivelyF,k、εM,k、εJ,k；Δuf,kAnd Δ ur,kWhether or not less than the error allowable value epsilonu,f,kAnd εu,r,k；ΔσpWhether or not less than the error allowable value epsilonσ,pIf not, locally adjusting the load by observing the distribution characteristics of the difference;
and 7: and (5) repeating the steps 4 to 7 until all error requirements are met, and obtaining the final test loading load.
Step 1, calculating the test load P of each test loading pointjThe method specifically comprises the following steps: for a givenLoad case, loading nodal point on airfoil FiProcessing the load to a test loading point according to an energy method, and calculating to obtain a test load Pj。
The method is characterized in that: test load PjThe calculation formula is as follows:
Figure GDA0002403891550000021
wherein: m is the number of theoretical nodes, Pi,jThe load distributed to the jth test loading point for the ith theoretical node load is calculated according to the following formula:
Figure GDA0002403891550000022
wherein: j is the number of test load points, coefficient lambdai、λi,xAnd λi,zObtained by solving the following system of equations:
Figure GDA0002403891550000031
wherein:
Figure GDA0002403891550000032
xjand yjIs the coordinate value of the jth test load point, xiAnd yiAnd the coordinate value of the ith theoretical load point.
Excess load Δ P in step 2j＝Pj-[Pj]。
The excess load amount delta P in step 2jProcessing until the allowable loading load is not exceeded Pj]The treatment method used at the test load point of (1) is an energy method.
Step 4, difference delta F on each rib station section of the bending shear torsion curves in the theoretical state and the test statek、ΔMk、ΔJkThe calculation formula is as follows:
Figure GDA0002403891550000033
Figure GDA0002403891550000034
Figure GDA0002403891550000035
wherein m iskThe number of theoretical nodes outside the k section, nkNumber of test load points outside the k section, dk,iIs the distance from the ith theoretical node to the profile k, dk,jDistance from jth test load point to section k, diDistance from the ith theoretical node to the rigid axis of the airfoil, djThe distance from the jth test loading point to the airfoil rigid axis.
Step 5, the difference delta u of the deflection of the front beam and the deflection of the rear beam of the wing box on the section of each rib stationf,kAnd Δ ur,kAnd the difference in stress Δ σ at the primary force-transmitting locationp，Δuf,kAnd Δ ur,kAnd Δ σpCalculated as follows: respectively applying theoretical node load and test loading load by establishing a finite element model of the airfoil structure to obtain the displacement and stress analysis results of two states, wherein
Figure GDA0002403891550000041
And
Figure GDA0002403891550000042
is the deflection of the front and rear beams at the section k of the theoretical statef,kAnd ur,kThe deflection of the front beam and the back beam at the section k under the test state,
Figure GDA0002403891550000043
and σpStress at the theoretical state and the test state, respectively, at the site p
Test condition of wing box front beam at section kThe difference in deflection from the theoretical state is
Figure GDA0002403891550000044
The difference of the deflection of the wing box back beam at the section k between the test state and the theoretical state is
Figure GDA0002403891550000045
The stress difference between the test state and the theoretical state at any main force transmission part p is
Figure GDA0002403891550000046
k is 1, …, s, s is the number of sections, p is 1, …, t, t is the number of main force transfer parts.
And 5, the main force transmission part is a wall plate.
And 5, the main force transmission part is a wing beam.
The invention has the beneficial effects that: compared with the prior art: the invention provides a set of test load processing method and flow and an evaluation method, which can objectively evaluate the feasibility of test loading load, ensure the loading accuracy and improve the load processing efficiency.
Drawings
FIG. 1 is a flow chart of the method of the present invention.
Detailed Description
The invention is further described with reference to the accompanying drawings, and the test load processing method of the airfoil main structure comprises the following steps:
step 1: calculating the test load P of each test loading pointjThe method specifically comprises the following steps: for a given load case, loading the nodal point on the airfoil FiProcessing the load to a test loading point according to an energy method, and calculating to obtain a test load PjTest load PjThe calculation formula is as follows:
Figure GDA0002403891550000051
wherein: m is the number of theoretical nodes, Pi,jThe load distributed to the jth test loading point for the ith theoretical node load is calculated according to the following formula:
Figure GDA0002403891550000052
wherein: j is the number of test load points, coefficient lambdai、λi,xAnd λi,zObtained by solving the following system of equations:
Figure GDA0002403891550000053
wherein:
Figure GDA0002403891550000054
xjand yjIs the coordinate value of the jth test load point, xiAnd yiAnd the coordinate value of the ith theoretical load point.
Step 2: checking the test load P of each test load pointjWhether or not the allowable load P is exceededj]If the test load P of the test load point isjExceeding allowable load [ P ]j]I.e. Pj≥[Pj]Then the excess load Δ P is measured by an energy methodjProcessing until the allowable loading load is not exceeded Pj]At the test load point of (1), the excess load amount Δ Pj＝Pj-[Pj]。
And step 3: repeating the step 2 until the test load P on each test loading pointjAll do not exceed allowable load [ Pj]I.e. Pj≤[Pj]；
And 4, step 4: calculating the difference delta F on each rib station profile of the bending shear in the theoretical state and the experimental statek、ΔMk、ΔJk；
The calculation formula is as follows:
Figure GDA0002403891550000061
Figure GDA0002403891550000062
Figure GDA0002403891550000063
wherein m iskThe number of theoretical nodes outside the k section, nkNumber of test load points outside the k section, dk,iIs the distance from the ith theoretical node to the profile k, dk,jDistance from jth test load point to section k, diDistance from the ith theoretical node to the rigid axis of the airfoil, djThe distance from the jth test loading point to the airfoil rigid axis.
And 5: calculating the difference delta u of the deflection of the front beam and the rear beam of the wing box on each rib station sectionf,kAnd Δ ur,kAnd the difference in stress Δ σ at the primary force-transmitting locationp；
Δσp，Δuf,kAnd Δ ur,kAnd Δ σpCalculated as follows:
respectively applying theoretical node load and test loading load by establishing a finite element model of the airfoil structure to obtain the displacement and stress analysis results of two states, wherein
Figure GDA0002403891550000064
And
Figure GDA0002403891550000065
is the deflection of the front and rear beams at the section k of the theoretical statef,kAnd ur,kThe deflection of the front beam and the back beam at the section k under the test state,
Figure GDA0002403891550000066
and σpAt the theoretical and experimental states, respectively, at the site pStress of
The difference of the deflection of the wing box front beam at the section k between the test state and the theoretical state is
Figure GDA0002403891550000067
The difference of the deflection of the wing box back beam at the section k between the test state and the theoretical state is
Figure GDA0002403891550000068
The stress difference between the test state and the theoretical state at any main force transmission part p is
Figure GDA0002403891550000069
k is 1, …, s, s is the number of sections, p is 1, …, t, t is the number of main force transfer parts.
The main force transmission part is a wall plate and a wing beam.
Step 6: simultaneous determination of Δ Fk、ΔMkAnd Δ JkWhether or not smaller than the error allowable value epsilon respectivelyF,k、εM,k、εJ,k；Δuf,kAnd Δ ur,kWhether or not less than the error allowable value epsilonu,f,kAnd εu,r,k；ΔσpWhether or not less than the error allowable value epsilonσ,pIf not, locally adjusting the load by observing the distribution characteristics of the difference;
and 7: and (5) repeating the steps 4 to 7 until all error requirements are met, and obtaining the final test loading load. The invention provides a set of test load processing method and flow and an evaluation method, which can objectively evaluate the feasibility of test loading load, ensure the loading accuracy and improve the load processing efficiency.

Claims (8)

1. A test load processing method for an airfoil main structure is characterized by comprising the following steps: the method comprises the following steps:
step 1: calculating the test load P of each test loading pointj；
Step 2: checking the test load P of each test load pointjWhether or not the allowable load P is exceededj]If the test load P of the test load point isjExceeding allowable load [ P ]j]I.e. Pj≥[Pj]The excess load amount Δ PjProcessing until the allowable loading load is not exceeded Pj]At the test load point of (a);
and step 3: repeating the step 2 until the test load P on each test loading pointjAll do not exceed allowable load [ Pj]I.e. Pj≤[Pj]；
And 4, step 4: calculating the difference delta F on each rib station profile of the bending shear in the theoretical state and the experimental statek、ΔMk、ΔJk；
And 5: calculating the difference delta u of the deflection of the front beam and the rear beam of the wing box on each rib station sectionf,kAnd Δ ur,kAnd the difference in stress Δ σ at the primary force-transmitting locationp(ii) a Calculated as follows:
respectively applying theoretical node load and test loading load by establishing a finite element model of the airfoil structure to obtain the displacement and stress analysis results of two states, wherein
Figure FDA0003517157830000011
And
Figure FDA0003517157830000012
is the deflection of the front and rear beams at the section k of the theoretical statef,kAnd ur,kThe deflection of the front beam and the back beam at the section k under the test state,
Figure FDA0003517157830000013
and σpStress at the theoretical state and the test state, respectively, at the site p
The difference of the deflection of the wing box front beam at the section k between the test state and the theoretical state is
Figure FDA0003517157830000014
The difference of the deflection of the wing box back beam at the section k between the test state and the theoretical state is
Figure FDA0003517157830000015
The stress difference between the test state and the theoretical state at any main force transmission part p is
Figure FDA0003517157830000016
k is 1, …, s, s is the number of sections, p is 1, …, t, t is the number of main force transmission parts;
step 6: simultaneous determination of Δ Fk、ΔMkAnd Δ JkWhether or not smaller than the error allowable value epsilon respectivelyF,k、εM,k、εJ,k；Δuf,kAnd Δ ur,kWhether or not less than the error allowable value epsilonu,f,kAnd εu,r,k；ΔσpWhether or not less than the error allowable value epsilonσ,pIf not, locally adjusting the load by observing the distribution characteristics of the difference;
and 7: and (5) repeating the steps 4 to 6 until all error requirements are met, and obtaining the final test loading load.
2. The test load handling method for the main structure of the airfoil according to claim 1, wherein: step 1, calculating the test load P of each test loading pointjThe method specifically comprises the following steps: for a given load case, loading the nodal point on the airfoil FiProcessing the load to a test loading point according to an energy method, and calculating to obtain a test load Pj。
3. The test load handling method for the main structure of the airfoil according to claim 2, wherein: test load PjThe calculation formula is as follows:
Figure FDA0003517157830000021
wherein: m is the number of theoretical nodes, Pi,jThe load distributed to the jth test loading point for the ith theoretical node load is calculated according to the following formula:
Figure FDA0003517157830000022
wherein: j is the number of test load points, coefficient lambdai、λi,xAnd λi,zObtained by solving the following system of equations:
Figure FDA0003517157830000023
wherein:
Figure FDA0003517157830000024
xjand yjIs the coordinate value of the jth test load point, xiAnd yiAnd the coordinate value of the ith theoretical load point.
4. The test load handling method for the main structure of the airfoil according to claim 1, wherein: excess load Δ P in step 2j＝Pj-[Pj]。
5. The test load handling method for the main structure of the airfoil according to claim 1, wherein: the excess load amount delta P in step 2jProcessing until the allowable loading load is not exceeded Pj]The treatment method used at the test load point of (1) is an energy method.
6. The test load handling method for the main structure of the airfoil according to claim 1, wherein: step 4, the difference delta F of the sections of the theoretical state and the experimental state of the bending shear on the station positions of each ribk、ΔMk、ΔJkThe calculation formula is as follows:
Figure FDA0003517157830000031
Figure FDA0003517157830000032
Figure FDA0003517157830000033
wherein m iskThe number of theoretical nodes outside the k section, nkNumber of test load points outside the k section, dk,iIs the distance from the ith theoretical node to the profile k, dk,jDistance from jth test load point to section k, diDistance from the ith theoretical node to the rigid axis of the airfoil, djDistance from jth test load point to airfoil rigid axis, FiIs the nodal load on the airfoil.
7. The test load handling method for the main structure of the airfoil according to claim 1, wherein: and 5, the main force transmission part is a wall plate.
8. The test load handling method for the main structure of the airfoil according to claim 1, wherein: and 5, the main force transmission part is a wing beam.
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