CN109178340A - A kind of wing body docking siding and its test method for fatigue test - Google Patents
A kind of wing body docking siding and its test method for fatigue test Download PDFInfo
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- CN109178340A CN109178340A CN201810972919.5A CN201810972919A CN109178340A CN 109178340 A CN109178340 A CN 109178340A CN 201810972919 A CN201810972919 A CN 201810972919A CN 109178340 A CN109178340 A CN 109178340A
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- docking
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- siding
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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
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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
This application involves aeroplane structure designs and verification experimental verification technical field, siding and its test method are docked more particularly to a kind of wing body for fatigue test, the wing body docking siding for fatigue test includes: clamping plate, docking band plate (3) and is used for connecting cleat and docks the covering (4) and stringer (5) of band plate (3).Clamping plate includes first clamping plate and second clamping plate, and first clamping plate and second clamping plate include upper clamp plate and lower clamp plate, and lower clamp plate is bolted with upper clamp plate；Docking band plate includes upper docking band plate and lower docking band plate, and lower docking band plate is connect with upper jointing strip crab bolt；First clamping plate and second clamping plate are symmetricly set on the both ends of docking band plate by covering and stringer.Present application addresses aircraft wing body full size structures to test the problem that loading environment is complicated, at high cost, the period is long and risk is big, improves the reliability of wing body docking structure, reduces cost, has great social and economic benefit.
Description
Technical field
The application belongs to aeroplane structure design and verification experimental verification technical field, in particular to a kind of wing for fatigue test
Body docks siding and its test method.
Background technique
Wing body docking structure is the key that power transmission channel in aircaft configuration, type of attachment and loaded complexity, must pass through conjunction
The means such as the topology layout and selection of reason, the detailed design of exquisiteness and suitable manufacturing process, reliable corrosion protection design guarantee
The important bonding pad of wing body docking structure has both the characteristics of high reliability and tired long-life, does not occur as far as possible within the period of being on active service
Fatigue rupture.Currently, the domestic design verification to the class formation is mostly to test by full size structure in conjunction with emulation technology to grind
Study carefully details power transmission feature, assesses its fatigue life and reliability.But full size structure test process is complicated, higher cost is tested
It is longer to demonstrate,prove the period；Simulation analysis is although at low cost, speed is fast, but precision is difficult to meet the requirements.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
There is provided a kind of wing bodies for fatigue test to dock siding and its test method for the purpose of the application, to solve
At least one problem of the existing technology.
The technical solution of the application is:
A kind of wing body docking siding for fatigue test, comprising:
Clamping plate, the clamping plate include first clamping plate and second clamping plate, and the first clamping plate and the second clamping plate include
Upper clamp plate and lower clamp plate, the lower clamp plate are bolted with the upper clamp plate；
Dock band plate, the docking band plate includes upper docking band plate and lower docking band plate, the lower docking band plate with it is described
Upper jointing strip crab bolt connection；
The first clamping plate and the second clamping plate are symmetricly set on the two of the docking band plate by covering and stringer
End.
Optionally, the covering includes two, and the upper clamp plate of the first clamping plate is arranged in one end of a covering
Between lower clamp plate, the upper docking band plate that the docking band plate is arranged in the other end docks between band plate under, described in another
One end of covering is arranged between the upper clamp plate and lower clamp plate of the second clamping plate, and the upper of the docking band plate is arranged in the other end
Docking band plate docks between band plate under；
The stringer include it is multiple, it is T-shaped, the upper clamp plate and it is described it is upper docking band plate corresponding end offer phase
The gap matched, the stringer side are posted and fixed with the covering, and the other side is prominent from each gap.
Optionally, the bolt is high locked bolts.
Optionally, the clamping plate is 30CrMnSiA material, and the upper docking band plate is titanium alloy product, the lower docking
Band plate, the covering and the stringer are articles made of aluminium alloy.
Optionally, the length of the wing body docking siding for fatigue test is 1800mm, width 510mm, maximum
With a thickness of 52.5mm.
Optionally, the one end of the first clamping plate and the second clamping plate far from the docking band plate is trapezoidal.
A kind of test method of the wing body docking siding for fatigue test, based on as described above for fatigue test
Wing body docks siding, comprising:
Step 1: the first clamping plate of the wing body for being used for fatigue test docking siding is mounted on to the upper hydraulic chuck of testing machine
On, second clamping plate is mounted on the lower hydraulic chuck of testing machine, guarantees the verticality and centering degree of wing body docking siding；
Step 2: the loading spectrum of the pre-applied of wing body docking siding is handled, format input control system as required
System；
Step 3: by the upper hydraulic chuck and lower hydraulic chuck of control system Control experiment machine, siding is docked to wing body
Carry out verification experimental verification；
Step 4: strain data is acquired and stored by data collection system, and the strain data is analyzed.
Optionally, the specification of the testing machine is 100t.
Optionally, loading spectrum described in step 2 is random spectrum, maximum load 800kN.
Optionally, strain data described in step 4 includes the load applied and the displacement that wing body docking siding generates.
At least there are following advantageous effects in invention:
The wing body for fatigue test of the application docks siding, and design is optimized to aircraft practical structures, passes through
Clamp region ensure that it, without designing other fixture tools, not only reduces design cost, but also greatly reduce test in test
It installs, workload needed for disassembly and inspection, reduce human cost, wing body docking siding form is simple, solves aircraft machine
Wing fuselage full size structure tests the problem that loading environment is complicated, at high cost, the period is long and risk is big, improves wing body to binding
The reliability of structure.
Detailed description of the invention
Fig. 1 is front view of the application for the wing body docking siding of fatigue test；
Fig. 2 is rearview of the application for the wing body docking siding of fatigue test；
Fig. 3 is upper clamp plate schematic diagram of the application for the wing body docking siding of fatigue test；
Fig. 4 is lower clamp plate schematic diagram of the application for the wing body docking siding of fatigue test；
Fig. 5 is upper docking band plate schematic diagram of the application for the wing body docking siding of fatigue test；
Fig. 6 is lower docking band plate schematic diagram of the application for the wing body docking siding of fatigue test；
Fig. 7 is covering front view of the application for the wing body docking siding of fatigue test；
Fig. 8 is covering side view of the application for the wing body docking siding of fatigue test；
Fig. 9 is the application for stringer schematic diagram in one embodiment of the wing body docking siding of fatigue test；
Figure 10 is the sectional view of Fig. 8；
Figure 11 is the application for stringer schematic diagram in another embodiment of the wing body docking siding of fatigue test；
Figure 12 is the application for stringer schematic diagram in another embodiment of the wing body docking siding of fatigue test；
Figure 13 is high locked bolts layout of the application for the wing body docking siding of fatigue test；
Figure 14 is front view of the application for the testing machine of the wing body docking siding of fatigue test；
Figure 15 is side view of the application for the testing machine of the wing body docking siding of fatigue test；
Wherein:
1- first clamping plate；2- second clamping plate；3- docks band plate；4- covering；5- stringer.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 to Figure 15 the application is described in further details with reference to the accompanying drawing.
This application provides a kind of wing bodies for fatigue test to dock siding, comprising: clamping plate, docking band plate 3 and use
In the covering 4 and stringer 5 of connecting cleat and docking band plate 3.
Specifically, clamping plate includes first clamping plate 1 and second clamping plate 2, first clamping plate 1 and second clamping plate 2 include upper clamp plate
And lower clamp plate, lower clamp plate are bolted with upper clamp plate；Docking band plate 3 includes upper docking band plate and lower docking band plate, lower jointing strip
Plate is connect with upper jointing strip crab bolt；First clamping plate 1 and second clamping plate 2 pass through covering 4 and stringer 5 is symmetricly set on jointing strip
The both ends of plate 3.
In the present embodiment, covering 4 includes two, and thickness is stepped variation, and one end setting of a covering 4 is first
It between the upper clamp plate and lower clamp plate of clamping plate 1 and is bolted, the upper docking band plate of docking band plate 3 is arranged in under in the other end
Docking band plate between and be bolted, one end of another covering 4 be arranged in second clamping plate 2 upper clamp plate and lower clamp plate it
Between and be bolted, the other end be arranged in docking band plate 3 upper docking band plate docked under between band plate and pass through bolt
It is fixed；Stringer 5 include it is multiple, it is T-shaped, by upper clamp plate and it is upper docking band plate corresponding end offer match slit
Mouthful, 5 side of stringer is bonded and is bolted with covering 4, and the other side is prominent from each gap.In the present embodiment, preferably
Stringer 5 is arranged 6, and 3 stringers 5 of every side setting connect each clamping plate and exist with band plate 3, the setting of stringer 5 as shown in figure 11 is docked
Stringer 5 shown in middle position, Figure 12 and Figure 13 is separately positioned on two sides up and down.
Advantageously, in the present embodiment, the upper buttcover plate of clamp area, covering 4, stringer 5, between lower buttcover plate, posting area
Covering 4, stringer 5 and the upper docking band plate of docking area, covering 4, stringer 5, pass through between lower docking band plate
CFBL1007AP high locked bolts are fixed, diameter and length with change in location reasonable Arrangement, the wing body dock siding docking area,
Posting area and clamp area form one by the reasonable Arrangement of high locked bolts, and structure design form is novel, simplify test load
Boundary condition.
Advantageously, the material of first clamping plate 1 and second clamping plate 2 is 30CrMnSiA material, upper docking in the present embodiment
Band plate is Ti-6Al-4V titanium alloy product, and lower docking band plate is 2024-T351 articles made of aluminium alloy, and Varying-thickness covering 4 is
2024HDT-T351 articles made of aluminium alloy, stringer 5 are 2026-T351 articles made of aluminium alloy.
Advantageously, the length of the wing body docking siding for fatigue test is 1800mm, and width is in the present embodiment
510mm, maximum gauge 52.5mm, meet the open ended maximum testpieces size of 100t testing machine, and when test does not need again
Design fixture tooling reduces design cost and cost of labor.
Advantageously, the one end of first clamping plate 1 and second clamping plate 2 far from docking band plate 3 is trapezoidal in the present embodiment, on
The design form of clamping plate and lower clamp plate is conducive to test installation, disassembly and inspection convenient for the overall weight of mitigation wall panel structure.
Siding is docked based on the above-mentioned wing body for fatigue test, present invention also provides a kind of for fatigue test
The test method of wing body docking siding.
Before this test progress, the process of processing wing body docking siding testpieces includes: the reliable of consideration aircaft configuration
Sexual factor simplifies Aircraft Structural Panels in conjunction with real aircraft wing body docking structure and simulation analysis, ignores angle of sweep, guarantees structure
Posting ratio；The wing body docking siding of the application has ignored the angle of sweep of practical structures, ensure that the posting of stringer 5 Yu covering 4
Than meeting the posting feature of practical structures for 1:1.Wall panel structure reasonable material is docked according to real aircraft wing body, and is processed into
Required structure size and form.Each component is assembled using high locked bolts, forms integral panel testpieces, need to guarantee to add
Work and assembly precision guarantee reliability.
In test method of the application for the wing body docking siding of fatigue test, pilot system mainly includes hydraulic pressure system
System, 100t testing machine, computer control system and corresponding data monitoring, acquisition and transmitting device.
A kind of test method of the wing body docking siding of fatigue test of the application, specifically includes:
Step 1: the first clamping plate 1 of the wing body for being used for fatigue test docking siding is mounted on to the upper hydraulic clip of testing machine
On head, second clamping plate 2 is mounted on the lower hydraulic chuck of testing machine, guarantees the verticality and centering degree of wing body docking siding；
Step 2: the loading spectrum of the pre-applied of wing body docking siding is handled, format input control system as required
System；
Step 3: by the upper hydraulic chuck and lower hydraulic chuck of control system Control experiment machine, siding is docked to wing body
Carry out verification experimental verification；
Step 4: strain data is acquired and stored by data collection system, and the strain data is analyzed.
In the present embodiment, the specification of the testing machine is 100t, and loading spectrum is random spectrum, maximum load in step 2
800kN, strain data includes the load applied and the displacement that wing body docking siding generates in step 4.Load and displacement difference
Data monitoring and data acquisition device are passed to by transmitting device by force snesor and displacement sensor, realize load and displacement
Real-time monitoring and acquisition, DATA REASONING precision with higher.
The wing body for fatigue test of the application docks siding, and being computed its DFR value is 134MPa, compared to original structure
6% is improved, i.e. the reliability of the structure is higher than original structure, longer life expectancy.
The wing body for fatigue test of the application docks siding, and smart structural design is light-weight, docking area and clamp area
Integrated design be convenient on testing machine carry out test, simplify wall panel structure verification experimental verification process, reduce wing body dock siding
Test the complexity of boundary condition simulation.Solve that aircraft wing body full size structure test loading environment is complicated, at high cost, period is long and
The big problem of risk improves the reliability of wing body docking structure, reduces cost, has great social and economic benefit.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of wing body for fatigue test docks siding characterized by comprising
Clamping plate, the clamping plate include first clamping plate (1) and second clamping plate (2), the first clamping plate (1) and the second clamping plate
It (2) include upper clamp plate and lower clamp plate, the lower clamp plate is bolted with the upper clamp plate；
It docks band plate (3), the docking band plate (3) includes upper docking band plate and lower docking band plate, the lower docking band plate and institute
State the connection of jointing strip crab bolt；
The first clamping plate (1) and the second clamping plate (2) pass through covering (4) and stringer (5) is symmetricly set on the docking
The both ends of band plate (3).
2. the wing body according to claim 1 for fatigue test docks siding, which is characterized in that covering (4) packet
Two are included, one end of a covering (4) is arranged between the upper clamp plate and lower clamp plate of the first clamping plate (1), the other end
The upper docking band plate being arranged in docking band plate (3) docks between band plate under, one end setting of another covering (4)
Between the upper clamp plate and lower clamp plate of the second clamping plate (2), upper docking band plate of the other end setting in docking band plate (3)
It is docked between band plate under；
The stringer (5) include it is multiple, it is T-shaped, the upper clamp plate and it is described it is upper docking band plate corresponding end offer phase
The gap matched, stringer (5) side are posted and fixed with the covering (4), and the other side is prominent from each gap.
3. the wing body according to claim 1 for fatigue test docks siding, which is characterized in that the bolt is high lock
Bolt.
4. the wing body according to claim 1 for fatigue test docks siding, which is characterized in that the clamping plate is
30CrMnSiA material, the upper docking band plate are titanium alloy product, the lower docking band plate, the covering (4) and the length
Purlin (5) is articles made of aluminium alloy.
5. the wing body according to claim 1 for fatigue test docks siding, which is characterized in that described for fatigue examination
The length for the wing body docking siding tested is 1800mm, width 510mm, maximum gauge 52.5mm.
6. the wing body according to claim 1 for fatigue test docks siding, which is characterized in that the first clamping plate
(1) and the one end of the second clamping plate (2) far from docking band plate (3) is trapezoidal.
7. a kind of test method of the wing body docking siding for fatigue test, is appointed based on the claims 1 to claim 5
Siding is docked for the wing body of fatigue test described in one characterized by comprising
Step 1: the first clamping plate (1) of the wing body for being used for fatigue test docking siding is mounted on to the upper hydraulic chuck of testing machine
On, second clamping plate (2) is mounted on the lower hydraulic chuck of testing machine, guarantees the verticality and centering degree of wing body docking siding；
Step 2: the loading spectrum of the pre-applied of wing body docking siding is handled, format input control system as required；
Step 3: by the upper hydraulic chuck and lower hydraulic chuck of control system Control experiment machine, wing body docking siding is carried out
Verification experimental verification；
Step 4: strain data is acquired and stored by data collection system, and the strain data is analyzed.
8. the test method of the wing body docking siding according to claim 7 for fatigue test, which is characterized in that described
The specification of testing machine is 100t.
9. the test method of the wing body docking siding according to claim 7 for fatigue test, which is characterized in that step
Loading spectrum described in two is random spectrum, maximum load 800kN.
10. the test method of the wing body docking siding according to claim 7 for fatigue test, which is characterized in that step
Strain data described in rapid four includes the load applied and the displacement that wing body docking siding generates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810972919.5A CN109178340B (en) | 2018-08-24 | 2018-08-24 | Wing body butt joint wallboard for fatigue test and test method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810972919.5A CN109178340B (en) | 2018-08-24 | 2018-08-24 | Wing body butt joint wallboard for fatigue test and test method thereof |
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| Publication Number | Publication Date |
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| CN109178340A true CN109178340A (en) | 2019-01-11 |
| CN109178340B CN109178340B (en) | 2022-03-29 |
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| CN201810972919.5A Active CN109178340B (en) | 2018-08-24 | 2018-08-24 | Wing body butt joint wallboard for fatigue test and test method thereof |
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| CN110704951A (en) * | 2019-09-29 | 2020-01-17 | 中国直升机设计研究所 | Helicopter tail section fatigue test load spectrum compilation method |
| CN114965025A (en) * | 2022-05-13 | 2022-08-30 | 哈尔滨工业大学 | Test fixture for nondestructive compression test of double-layer hollow thin plate |
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| CN109178340B (en) | 2022-03-29 |
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