CN107419088A - A kind of laser peening shaping methods of Integral Wing Panel part milling unstability - Google Patents
A kind of laser peening shaping methods of Integral Wing Panel part milling unstability Download PDFInfo
- Publication number
- CN107419088A CN107419088A CN201710439754.0A CN201710439754A CN107419088A CN 107419088 A CN107419088 A CN 107419088A CN 201710439754 A CN201710439754 A CN 201710439754A CN 107419088 A CN107419088 A CN 107419088A
- Authority
- CN
- China
- Prior art keywords
- unstability
- laser peening
- wing panel
- milling
- integral wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
- C21D10/005—Modifying the physical properties by methods other than heat treatment or deformation by laser shock processing
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
Abstract
The invention discloses a kind of laser peening shaping methods of Integral Wing Panel part milling unstability, Analysis of Structural Characteristics is carried out first to the milling unstability of the local weak rigid region of wallboard, measurement unstability pattern, analytical structure rigidity and calculate critical load；Then using numerical optimisation algorithms design laser peening load path, using least amount of deformation as object function, using buckling critical stress as constraints, optimized with the theoretical nonlinear path for carrying out laser peening shaping of minimal deformation work(；Last unstability region carries out laser peening Shape correction, by load amplitude, the zone of action and the spot size and its pattern that control laser peening, accurate processing is realized to the deformation of different zones iso-curvature, equivalent high accuracy " hammering cold-working shaping " is realized, eliminates Integral Wing Panel part milling unstability.Residual stress of superficial layer 1~2mm of depth caused by laser peening processing, the milling unstability of weak rigid region can be repaired, additionally it is possible to 3~5 times of the fatigue life in lift structure service phase.
Description
Technical field
The present invention relates to Field of Aviation Manufacturing, the laser peening shaping of Integral Wing Panel parts locally milling unstability is refered in particular to
Method.
Background of invention
Integral Wing Panel is the widely used new integrated member of modern civil aircraft, with preferable rigidity, by force
Degree, fatigue behaviour and aeroperformance, greatly reduce number of parts and reduce assembly period, its digital control processing forming technique is to work as
One of core content in this life circle aviation.Integral Wing Panel structure gathered Varying Thickness Plates, stringer, lightening core,
The features such as horizontal ribs, are generally milled into from aluminum alloy pretensioning plate, and material removing rate is up to 92%, in remnants
Under the influence of the factors such as stress, milling load, processing difficulties that dimension overproof is commonly encountered when being weak rigid aluminium alloy wallboard.
Milling Process be with high temperature, high pressure, the METHOD FOR LARGE DEFORMATION ELASTOPLASTIC process of high strain-rate, milling load, thermal stress and
Forming residual stress can be produced in machined surface under the comprehensive function of the factors such as phase transformation, while the removal of material causes blank residual
The release and redistribution of residue stress, the deformation of these factors effect lower thin sheet structure is inevitable, especially wing integral wall
Average wall thickness at the wingtip of plate, lightening core is between 3~5mm, and under the influence of generalized load, inside configuration stress is much smaller than
During Materials Yield Limit stress, produce lose bearing capacity perpendicular to the displacement of loading direction suddenly, disturbed in small load
Fluctuation is presented in dynamic lower displacement structure, and this phenomenon is referred to as unstability.Unstability is closely related with the rigidity of structure, the office of Integral Wing Panel
Milling unstability main cause in portion's is exactly that regional area rigidity is weak, and generalized load disturbance produces unstability.
The current local buckling's shaping for being directed to Integral Wing Panel, conventional method have hammering cold-working method, mechanic shot peening method
With ultrasonic wave shot-peening method.Hammering cold-working method is the convex side surface that pincers worker taps unstability region using pane hammer, by new plastic deformation
Instability status are repaired, this method shaping efficiency is low, quality conformance is difficult to ensure that, when relying on operation experience, and hammering
It is also easy to produce top layer microscopic damage and stress concentration.Mechanic shot peening method is to utilize default shot-peening density model striking work surface,
Unstability is repaired with plastic deformation and residual compressive stress, but mechanic shot peening is to carry out spraying striking work table using entity bullet
Face, the shortcomings that shot peening coverage is difficult to accurate control, surface roughness difference be present with a large amount of pellet injections.Ultrasonic wave shot-peening method is profit
Strong high-frequency percussion ripple acts on material surface by medium caused by ultra sonic machinery acts on, and reaches strengthening surface and improvement
The purpose of stress distribution, typical media are striker and bullet, are substantially that physical impact produces local plastic deformation, pass through accumulation
Plastic deformation realizes overall shaping purpose, and due to the high frequency random motion of entity striker/bullet, this method is carried out at unstability shaping
The shortcomings that load is difficult to accurately control during reason be present.In summary, the shaping of Integral Wing Panel part milling unstability needs one
The kind zone of action and load character controllable precise, the new method for possessing flexibility.
The content of the invention
It is an object of the invention to overcome the shortcomings of current shaping technique in above-mentioned background technology discussion, there is provided one kind effect
Region and load character controllable precise, the new method for possessing flexibility, i.e. laser peening shaping technique.The technology is excellent using laser
Controllability and stable repeatability, the design load accurately calculated is applied to unstability region, is repairing the same of unstability form
When lifting region fatigue life, realize high-performance shaping.
The technical scheme is that：
A kind of laser peening shaping methods of Integral Wing Panel part milling unstability, are comprised the steps of：
1) to the local weak rigid region of Integral Wing Panel, i.e., thickness is between portions such as the wingtips of 3~5mm scopes, lightening cores
The milling unstability of position carries out Analysis of Structural Characteristics：Unstability pattern is determined first, and unstability shape is carried out using optics in-situ measurement system
Looks measure, and obtain the spatial distribution of iso-curvature envelope；Secondly the rigidity of structure is calculated, is counted based on the distribution of iso-curvature envelope
Calculate the rigidity under unstability region large deformation state；Ultimate analysis critical load, buckling structure point is carried out using numerical simulation software
Analysis and plate shell stable calculation, determine the limit stress of structural instability.
2) using numerical optimisation algorithms design laser peening load path, optimized algorithm is using least amount of deformation as target letter
Number, using buckling critical stress as constraints, the nonlinear path using the theoretical progress laser peening shaping of minimal deformation work(is excellent
Change.
3) laser peening Shape correction is carried out to unstability region according to path optimizing, by the load width for controlling laser peening
Value, the zone of action and spot size and its pattern, accurate processing is realized to the deformation of different zones iso-curvature, realizes equivalent high accuracy
" hammering cold-working shaping ", eliminates Integral Wing Panel part milling unstability.
The laser peening shaping methods of Integral Wing Panel part milling unstability of the present invention, the Integral Wing Panel material of processing
Expect for aluminium alloy 7055-T7751,70 °~110 ° of laser peening angle change scope.
1~10ns of laser pulse width is adjustable used by laser peening shaping methods proposed by the present invention, pulse energy 1
~10J is adjustable, and 1~5mm of spot diameter is adjustable, and light spot shape is adjustable for circular and square focus spot.In nanosecond short pulse strong laser
In the presence of, the ablator of workpiece surface coating absorbs laser energy and plasma cloud is produced in restraint layer, in 10-100ns
Interior rapid expanding, produce the shock wave of 1-10GPa magnitudes, when surge pressure exceedes aluminium alloy dynamic yield stress intensity, material
Expect that top layer produces strain hardening, remain the residual compressive stress of 1-2mm depth so that workpiece surface produces plastic deformation.The present invention
By adjusting laser pulse width and pulse energy control induction shock wave amplitude, i.e., accurate control load size；Pass through adjustment
Laser facula size and the accurate control action region of light spot shape；By accurate control load and the zone of action, equivalent hammer is realized
Cold-working shaping is hit, while produces the residual compressive stress of 1-2mm depth, can be 3~5 times with fatigue life in lift structure service phase.
Brief description of the drawings
Present invention brief description of the drawings is as follows：
Fig. 1 is Integral Wing Panel part milling unstability schematic diagram, wherein 1 is unstability area topographies, after 2 are buckling deformation
Iso-curvature envelope.
Fig. 2 is to carry out buckling analysis acquired results to local milling unstability using CAE analysis program-ABAQUS.
Fig. 3 is unstability laser peening shaping policy schematic diagram, wherein 3 be unstability area topographies, 4 be laser peening nozzle, 5
It is laser peening angle change scope, the top view of the iso-curvature envelope after 6 buckling deformations, 7 are determined using optimized algorithm
Shot-peening path planning figure.
Embodiment
The embodiment of the laser peening shaping methods of Integral Wing Panel part milling unstability is as follows：
1) to the local weak rigid region of Integral Wing Panel, i.e., thickness is between portions such as the wingtips of 3~5mm scopes, lightening cores
The milling unstability of position carries out Analysis of Structural Characteristics：
A) unstability pattern is determined first：Unstability topography measurement is carried out using optics in-situ measurement system, by optics developer
Milling unstability region is sprayed on, optical measurement camera that two are worked simultaneously, in different angle shoots unstability region, adopts
Picture is synthesized with graphics process work station and carries out binary translation, i.e., black whitening processing, is disappeared using MATLAB filter functions
Except data noise, measurement result is translated and rotated, obtain the spatial distribution of iso-curvature envelope, as indicated by a broken line in fig. 1.
B) rigidity of structure is secondly calculated：Based on the distribution of iso-curvature envelope, the wallboard local buckling of acquisition will be measured
Topographic data inputs UG, carries out CAD 3D modeling, model is imported into CAE analysis program-ABAQUS, using static-
Structure modules calculate the rigidity under unstability region large deformation state.
C) ultimate analysis critical load：Feature extraction wallboard unstability region geometric shape, as shown in Fig. 2 example of the present invention is built
200 × 500 × 10mm sheet model has been found, flexing is carried out using the bulk analysis modules of CAE analysis program-ABAQUS
Analysis, solves each rank mode of structural instability, is illustrated in figure 24 rank mode.Enter andante shell stable calculation, determine that structure is lost
Steady limit stress, for instructing post laser shot-peening parameter.
2) by the unstability pattern obtained by step 1, the spatial distribution of iso-curvature envelope is as primary condition, by step 1 institute
The rigidity under unstability region large deformation state is obtained as boundary condition, by the limit stress of each rank mode of unstability obtained by step 1
For constraints, laser peening load path is designed using the numerical optimisation algorithms of MATLAB softwares, draw after initial path with
Least amount of deformation is object function, and nonlinear path optimized algorithm is carried out using MATLAB.The path optimizing of gained is as in Fig. 3
Shown in 7, the determination of the path optimizing based on unstability structure iso-curvature envelope, the rigidity of structure, limit stress and determine.
3) laser peening Shape correction is carried out to panel surfaces, by the load amplitude and the zone of action that control laser peening
Equivalent " hammering cold-working shaping " is realized, eliminates Integral Wing Panel part milling unstability.The wherein essence of laser peening load amplitude
Really control is to realize that the 1~10ns of laser pulse width used is adjustable, laser by adjusting laser pulse width and pulse energy
1~10J of energy is adjustable；The accurate control of the zone of action is that adjustment laser facula size and shape is realized, 1~5mm of spot diameter
Adjustable, light spot shape is circular and square adjustable.It is simultaneously guarantee processed material aluminium alloy 7055-T7751 unstability shaping
Quality, 70 °~110 ° of laser peening angle change scope, the scope at 90 ° of skew vertical incidence angle is ± 20 ° so that laser sprays
Ball load amplitude maximizes and acts on material surface, and caused top layer compression depth reaches aluminium alloy 7055- up to 1~2mm
The 70~80% of T7751 yield limits, while 3~5 times of the fatigue life in lift structure service phase.
Claims (3)
- A kind of 1. laser peening shaping methods of Integral Wing Panel part milling unstability, it is characterised in that this method include with Lower step：1) to the local weak rigid region of Integral Wing Panel, i.e., thickness is between the portion such as the wingtip of 3~5mm scopes and/or lightening core The milling unstability of position carries out Analysis of Structural Characteristics；2) using numerical optimisation algorithms design laser peening load path, optimized algorithm using least amount of deformation as object function, with Buckling critical stress is constraints, is optimized using the theoretical nonlinear path for carrying out laser peening shaping of minimal deformation work(；3) according to path optimizing to unstability region carry out laser peening Shape correction, by control laser peening load amplitude, The zone of action and spot size and its pattern, accurate processing is realized to the deformation of different zones iso-curvature, realizes equivalent high accuracy " hammer Hit cold-working shaping ", eliminate Integral Wing Panel part milling unstability.
- 2. a kind of laser peening shaping methods of Integral Wing Panel part milling unstability according to claim 1, it is special Sign is that the Analysis of Structural Characteristics in the step 1) specifically includes：Unstability pattern is determined first, and unstability topography measurement is carried out using optics in-situ measurement system, obtains iso-curvature envelope Spatial distribution；Secondly the rigidity of structure is calculated, is distributed as with iso-curvature envelope under basic calculation unstability region large deformation state Rigidity；Ultimate analysis critical load, buckling structure analysis and plate shell stable calculation are carried out using numerical simulation software, it is determined that knot The limit stress of structure unstability.
- 3. a kind of laser peening shaping methods of Integral Wing Panel part milling unstability according to claim 1, it is special Sign is, Integral Wing Panel is that material is aluminium alloy 7055-T7751,70 °~110 ° of laser peening angle change scope.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710439754.0A CN107419088A (en) | 2017-06-12 | 2017-06-12 | A kind of laser peening shaping methods of Integral Wing Panel part milling unstability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710439754.0A CN107419088A (en) | 2017-06-12 | 2017-06-12 | A kind of laser peening shaping methods of Integral Wing Panel part milling unstability |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107419088A true CN107419088A (en) | 2017-12-01 |
Family
ID=60429667
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710439754.0A Withdrawn CN107419088A (en) | 2017-06-12 | 2017-06-12 | A kind of laser peening shaping methods of Integral Wing Panel part milling unstability |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107419088A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110802218A (en) * | 2019-10-21 | 2020-02-18 | 苏州科技大学 | Rapid creep aging forming method for large-curvature corrugated plate |
| CN110900463A (en) * | 2018-09-17 | 2020-03-24 | 鲍臻 | Automatic shot blasting forming device and method for synchronous cambered surface forming hammer |
| CN113221394A (en) * | 2021-02-08 | 2021-08-06 | 西北工业大学 | Simulation method for laser shot-peening forming of integral wall panel of airplane |
| CN113255069A (en) * | 2021-03-08 | 2021-08-13 | 武汉理工大学 | Rapid and accurate ultrasonic shot blasting material surface morphology prediction method |
| CN116770036A (en) * | 2023-06-21 | 2023-09-19 | 安徽理工大学 | Progressive firing pin type ultrasonic shot blasting surface strengthening equipment |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101004595A (en) * | 2007-01-19 | 2007-07-25 | 中国科学院力学研究所 | Laser method for fine-tuning shaped objects of body case of airplane |
| CN101011777A (en) * | 2006-12-11 | 2007-08-08 | 江苏大学 | Method and apparatus of forming cut deal laser prestress composite shot blasting |
| CN101288888A (en) * | 2008-06-25 | 2008-10-22 | 中国科学院力学研究所 | Laser and blast compound forming method based prestress force |
| CN106216843A (en) * | 2016-08-25 | 2016-12-14 | 广东工业大学 | A kind of self adaptation laser peening corrector based on big data platform and method |
-
2017
- 2017-06-12 CN CN201710439754.0A patent/CN107419088A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101011777A (en) * | 2006-12-11 | 2007-08-08 | 江苏大学 | Method and apparatus of forming cut deal laser prestress composite shot blasting |
| CN101004595A (en) * | 2007-01-19 | 2007-07-25 | 中国科学院力学研究所 | Laser method for fine-tuning shaped objects of body case of airplane |
| CN101288888A (en) * | 2008-06-25 | 2008-10-22 | 中国科学院力学研究所 | Laser and blast compound forming method based prestress force |
| CN106216843A (en) * | 2016-08-25 | 2016-12-14 | 广东工业大学 | A kind of self adaptation laser peening corrector based on big data platform and method |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110900463A (en) * | 2018-09-17 | 2020-03-24 | 鲍臻 | Automatic shot blasting forming device and method for synchronous cambered surface forming hammer |
| CN110802218A (en) * | 2019-10-21 | 2020-02-18 | 苏州科技大学 | Rapid creep aging forming method for large-curvature corrugated plate |
| CN110802218B (en) * | 2019-10-21 | 2021-02-09 | 苏州科技大学 | Rapid creep aging forming method for large-curvature corrugated plate |
| CN113221394A (en) * | 2021-02-08 | 2021-08-06 | 西北工业大学 | Simulation method for laser shot-peening forming of integral wall panel of airplane |
| CN113255069A (en) * | 2021-03-08 | 2021-08-13 | 武汉理工大学 | Rapid and accurate ultrasonic shot blasting material surface morphology prediction method |
| CN116770036A (en) * | 2023-06-21 | 2023-09-19 | 安徽理工大学 | Progressive firing pin type ultrasonic shot blasting surface strengthening equipment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107419088A (en) | A kind of laser peening shaping methods of Integral Wing Panel part milling unstability | |
| Hönnige et al. | Improvement of microstructure and mechanical properties in wire+ arc additively manufactured Ti-6Al-4V with machine hammer peening | |
| EP3229994B1 (en) | Additive manufacturing and integrated impact post-treatment | |
| CN105002349B (en) | Method for conducting variable-light-spot multilayer staggered laser shock homogeneous enhancement on blades | |
| CN104164538B (en) | Laser shock reinforcing method for obtaining large area uniform surface morphology | |
| Zhang et al. | Machining distortion minimization for the manufacturing of aeronautical structure | |
| CN111575476B (en) | Laser shock peening method for blade edge | |
| CN103146893B (en) | Method for treating curved surface through laser shock | |
| CN106270005B (en) | A kind of method and apparatus of blade laser peening school shape | |
| CN104899345B (en) | Method for determining complex-curved shape workpiece laser shot forming technological parameter | |
| CN103320579B (en) | Aircraft turbine blade laser shock method and device | |
| CN107186063B (en) | Integral panel rib die mould and bending integral forming method based on roll-in | |
| CN103862050A (en) | Metal 3D printer based on interlayer shock processing process and printing method thereof | |
| CN105397423B (en) | The manufacture method of the large thin-wall covering with interior muscle and complex-shaped surface mould | |
| Li et al. | A study of the micro-hole geometry evolution on glass by abrasive air-jet micromachining | |
| CN110527807B (en) | Numerical control progressive strengthening method for complex metal surface | |
| CN104822489B (en) | Method and device for manufacturing turbine blades | |
| CN110976869A (en) | Part additive composite manufacturing device and method | |
| CN106271419A (en) | The most superoleophobic titanium alloy and the preparation method of aluminum alloy surface | |
| CN109022756B (en) | Method for improving laser shock precision and efficiency of weak-rigidity part | |
| CN102513942A (en) | Supersonic shot-peening forming method for single or double curvature integral panels | |
| CN112663043A (en) | Ultrasonic shot blasting assisted laser additive repair device and repair method thereof | |
| CN113088678A (en) | Laser shock peening method for blades of small-size blisk | |
| CN103433854A (en) | Digital shot peen forming method for integral wallboard | |
| CN109136526B (en) | Method for strengthening curved surface structure by laser shock |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20171201 |
|
| WW01 | Invention patent application withdrawn after publication |