CN109050970B - A kind of ground experiment method under simulation aircraft components dangerous position is loaded in the sky - Google Patents
A kind of ground experiment method under simulation aircraft components dangerous position is loaded in the sky Download PDFInfo
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- CN109050970B CN109050970B CN201810632551.8A CN201810632551A CN109050970B CN 109050970 B CN109050970 B CN 109050970B CN 201810632551 A CN201810632551 A CN 201810632551A CN 109050970 B CN109050970 B CN 109050970B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/24—Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures
-
- 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
-
- 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
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- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a kind of ground experiment method of simulation aircraft components dangerous position under loaded in the sky, it is related to aircraft components ground simulation test field, steps of the method are: (1) foil gauge and strain rosette are pasted in the position to be tested of component aboard；(2) each flight of record aircraft is risen and fallen the strain spectrum of each foil gauge and strain rosette；(3) according to the actual loading situation of aircraft components, Test-bed is built；(4) component is established in the finite element model of Test-bed using Finite Element Simulation Software, find out the size for reaching actual measurement strain value loading force；(5) component is loaded using the loaded value found out, and measures the strain value for flying upper same area；(6) measured value on the strain value and aircraft that comparative test measures, can be tested if error is less than 5%, and otherwise return step (3) re-starts force analysis.The actual loading situation of this method energy preferably simulation aircraft components key position.
Description
Technical field
Application field of the present invention is to belong to aircraft components ground simulation test technical field, more particularly to refer in particular to a kind of simulation
Ground experiment method under aircraft components dangerous position is loaded in the sky.
Background technique
Aircraft is in the economic field of country, field of traffic, military field in occupation of critical role.It is lost by aircraft structure fatigue
Structural break caused by effect, static strength are destroyed, causes serious accident to occur, and fatigue rupture and static strength are destroyed and often sent out
The raw key position concentrated in components stress, it is therefore desirable to which fatigue and test of static strength are carried out to aircaft configuration.But it carries out whole
The time cost and economic cost of machine fatigue test and test of static strength are all very huge, therefore are closed for airplane component
The ground simulation test technology that key position invents has important practical meaning in engineering.
Current ground plane test of static strength and Stromeyer test are carried out on whole machine experiment platform, are needed to whole
Machine is loaded, and is constructed as many as length and equipment of time spent by complete machine test stand, is all limited aircraft floor simulation test
The raising of efficiency, and complete machine simulation test is very low for the specific aim of aircraft critical component, proposes a kind of simulation aircraft portion
Ground experiment method under part dangerous position is loaded in the sky can high efficiency, low cost, targetedly carry out aircraft floor
Simulation test.
Summary of the invention
Present invention aims to meet the needs of aircraft components ground simulation test, a kind of simulation aircraft components are proposed
Ground experiment method under dangerous position is loaded in the sky, this method are also applied for carrying out the component of other aircraft mechanical structures
Off-line simulation test.
The technical solution adopted by the present invention is a kind of aircraft components dangerous position ground simulation loaded test method in the air, real
Existing this method the steps include:
Step 1): foil gauge and strain rosette are pasted in the stress raiser of aircraft component to be tested, in stress concentration portion position
Main Impact direction at least pastes a foil gauge in neighbouring 10mm, and the strain of three directions is pasted around around this foil gauge
Flower guarantees main Impact direction, has foil gauge in 45 °, 90 °, 135 ° of direction with main Impact direction；
Step 2): each foil gauge of the record each flight course of aircraft and the strain spectrum of strain rosette, if carried out quiet strong
Maximum strain is then extracted in degree test, is filtered if carrying out Stromeyer test to strain spectrum, is filtered out and do not generate damage
Side crops industry；
Step 3): according to the stress condition of aircraft component to be tested, the main stress position of this aircraft component to be tested is found
It sets and Impact direction, builds ground simulation test platform using vibration excitor, pass through ground simulation test platform and simulate aircraft portion to be tested
The main stress of part；
Step 4): using the finite element model of Finite Element Simulation Software creation aircraft component to be tested, and in finite element mould
Apply boundary condition identical with the ground simulation test platform built in quasi- software, extracts and survey position with aircraft component to be tested
The strain of same position is as target value, using the size of loading force in boundary condition as variable and the value model of given variable
It encloses, by the Optimization Solution of finite element analysis software, obtains the load surveyed with aircraft strain under close strain value as
The load value of face simulation test；
Step 5): pasting foil gauge on the aircraft component to be tested that ground simulation test platform carries out simulation test, guarantees
Foil gauge is identical as foil gauge position on aircraft, is loaded using the load value for acquiring ground simulation test in step 4), and
Record the strain value that each foil gauge measures；
Step 6): comparison step 5) in measured value in the strain value that measures and step 2) on aircraft, if error is less than
5% is tested, otherwise return step 3) re-start force analysis.
Compared with prior art, the present invention has the advantages that.
The present invention has the advantages that propose a kind of simulation aircraft components dangerous position it is loaded in the sky under ground experiment
Method.This method can more actually simulate the stress condition of aircraft components key position, thus allow for aircraft components
Various ground simulation tests.More traditional complete machine ground experiment is compared, and this method has in terms of experimentation cost and time cost
Apparent advantage, and specific aim is higher, is capable of the concrete position stress condition of effective simulation aircraft.
Detailed description of the invention
The flow chart of Fig. 1 the method for the present invention realization aircraft components ground experiment.
Fig. 2 strain gauge adhesion position view of the present invention.
The testing stand schematic diagram of Fig. 3 the method for the present invention.
Strain effects schematic diagram Fig. 4 of the invention.
Fatigue test service life effect diagram Fig. 5 of the invention.
Specific embodiment
A specific embodiment of the invention is described with reference to the drawings.
The present invention is further illustrated the present invention by the fatigue test of aircraft components ground,
Loaded test method, circular are as follows in the air for a kind of aircraft components dangerous position ground simulation:
Step 1): foil gauge and strain rosette are pasted in the stress raiser of aircraft component to be tested, guarantees foil gauge measurement
Maximum direction is strained, as shown in Fig. 2, at least pasting one in main Impact direction in the 10mm near stress concentration portion position
Foil gauge pastes three direction strain rosettes around this foil gauge around, guarantees main Impact direction, is in main Impact direction
45 °, 90 °, 135 ° of direction have foil gauge；
Step 2): each foil gauge of the record each flight course of aircraft and the strain spectrum of strain rosette, this test are fatigue
Test, need to be filtered strain spectrum, filter out the side crops industry for not generating damage；
Step 3): according to the stress condition of aircraft component to be tested, the main stress position of this aircraft component to be tested is found
It sets and Impact direction, builds ground simulation test platform using vibration excitor, pass through ground simulation test platform and simulate aircraft portion to be tested
The main stress of part, as shown in figure 3, simulating the component to be tested using vibration excitor 1, vibration excitor 2 and vibration excitor 3 respectively
Stress；
Step 4): using the finite element model of Finite Element Simulation Software creation aircraft component to be tested, and in finite element mould
Apply boundary condition identical with the ground simulation test platform built in quasi- software, extracts and survey position with aircraft component to be tested
The strain of same position is as target value, using the size of loading force in boundary condition as variable and the value model of given variable
It encloses, by the Optimization Solution of finite element analysis software, obtains the load surveyed with aircraft strain under close strain value as
The load value of face simulation test；
Step 5): pasting foil gauge on the aircraft component to be tested that ground simulation test platform carries out simulation test, guarantees
Foil gauge is identical as foil gauge position on aircraft, is loaded using the load value for acquiring ground simulation test in step 4), and
Record the strain value that each foil gauge measures；
Step 6): comparison step 5) in measured value in the strain value that measures and step 2) on aircraft, if error is less than
5% is tested, otherwise return step 3) re-start force analysis.
The present invention has the advantages that proposing a kind of aircraft components dangerous position ground simulation loaded test method in the air.
The stress condition that this method can more actually simulate aircraft components key position carries out the various ground experiments of aircraft components, compared with
Traditional complete machine ground experiment is compared, and the experimentation cost of this method and time cost have an apparent advantage, and specific aim compared with
Height, is capable of the concrete position stress condition of effective simulation aircraft, and the component relatively low for certain service life can be tried individually
It tests, substantive feedback is provided faster for Optimal Structure Designing.
It, will in order to verify the effect of aircraft components dangerous position ground simulation proposed by the present invention loaded test method in the air
This method is applied on aircraft component, by simulation calculating and verification experimental verification, is found the strain value of ground simulation test and is flown
The strain value that machine component is surveyed in the sky is almost consistent, as shown in Figure 4.And the component uses the fatigue test service life of this method
It is also very close with aerial actual life, all in 2 times of factors, as shown in Figure 5.It is therefore proposed that a kind of aircraft portion
Loaded test method can accurately simulate the aerial loading conditions of aircraft components dangerous position to the ground simulation of part dangerous position in the air.
Claims (2)
1. a kind of aircraft components dangerous position ground simulation loaded test method in the air, it is characterised in that: realize the step of this method
Suddenly it is,
Step 1): foil gauge and strain rosette are pasted in the stress raiser of aircraft component to be tested, near stress concentration portion position
10mm in main Impact direction at least paste a foil gauge；
Step 2): each foil gauge of the record each flight course of aircraft and the strain spectrum of strain rosette, if carrying out static strength examination
It tests, extracts maximum strain, strain spectrum is filtered if carrying out Stromeyer test, filter out the small load for not generating damage
Lotus；
Step 3): according to the stress condition of aircraft component to be tested, find this aircraft component to be tested main forced position and
Impact direction builds ground simulation test platform using vibration excitor, simulates aircraft component to be tested by ground simulation test platform
Main stress；
Step 4): the finite element model of aircraft component to be tested is created using Finite Element Simulation Software, and soft in finite element modelling
Apply boundary condition identical with the ground simulation test platform built in part, extracts identical as aircraft component actual measurement position to be tested
The strain of position is led to as target value using the size of loading force in boundary condition as the value range of variable and given variable
The Optimization Solution for crossing finite element analysis software show that straining the load under close strain value with aircraft actual measurement is ground simulation
The load value of test；
Step 5): pasting foil gauge on the aircraft component to be tested that ground simulation test platform carries out simulation test, guarantees strain
Piece is identical as foil gauge position on aircraft, is loaded using the load value for acquiring ground simulation test in step 4), and record
The strain value that each foil gauge measures；
Step 6): comparison step 5) in measured value in the strain value that measures and step 2) on aircraft, if error is less than 5%
Simulation test is carried out, otherwise return step 3) re-start force analysis.
2. a kind of aircraft components dangerous position ground simulation according to claim 1 loaded test method in the air, feature
It is: in step 1), pastes three direction strain rosettes around around foil gauge, guarantee main Impact direction and main stress side
There is foil gauge in 45 °, 90 °, 135 ° of direction.
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| CN201810632551.8A CN109050970B (en) | 2018-06-19 | 2018-06-19 | A kind of ground experiment method under simulation aircraft components dangerous position is loaded in the sky |
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Families Citing this family (5)
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| JP6741716B2 (en) | 2018-04-09 | 2020-08-19 | 株式会社Ｓｕｂａｒｕ | Aircraft management system |
| CN109720601B (en) * | 2019-01-19 | 2020-08-28 | 北京工业大学 | Multi-axis fatigue test device for full-size structural part of airplane |
| CN109733641A (en) * | 2019-01-19 | 2019-05-10 | 北京工业大学 | A kind of aircraft full size structure part multiaxle fatigue experimental method |
| CN110282153B (en) * | 2019-05-27 | 2022-09-20 | 中国飞机强度研究所 | Ear fork-box section structure static strength test device |
| CN111539068A (en) * | 2020-04-22 | 2020-08-14 | 中国飞机强度研究所 | Method for contrastively displaying static strength test data of airplane structure |
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