CN104120230A - Airplane wallboard part vibration aging straightening method and vibration aging straightening device - Google Patents
Airplane wallboard part vibration aging straightening method and vibration aging straightening device Download PDFInfo
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- CN104120230A CN104120230A CN201410299300.4A CN201410299300A CN104120230A CN 104120230 A CN104120230 A CN 104120230A CN 201410299300 A CN201410299300 A CN 201410299300A CN 104120230 A CN104120230 A CN 104120230A
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- school
- shape platform
- target ship
- school shape
- aircraft target
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Abstract
The invention relates to an airplane wallboard part vibration aging straightening method and vibration aging straightening device. The method comprises the following steps: fixing the airplane wallboard part subjected to digital control processing to a vibration aging straightening platform in a dot-matrix tightening mode, rigidly fixing a vibration exciter with the vibration aging straightening platform, and starting the vibration exciter with a control system to simultaneously vibrate the vibration aging straightening platform and the airplane wallboard fixed to the platform, thereby eliminating and homogenizing the internal stress of the airplane wallboard part, and achieving the goal of straightening.
Description
Technical field
The application relates to the manufacturing technology field of aircraft target ship part, and treatment process and the device thereof of oscillating aging carried out in the distortion particularly producing in the course of processing for correction aircraft target ship part.
Background technology
Along with improving constantly that present generation aircraft high speed, high maneuverability can require, aeroplane structure design constantly changes, and first a large amount of novel materials, new texture and new technology are applied at aviation.In order to improve maneuvering ability and the long-distance flight ability of aircraft, increase and carry load, technician is always in the new technology of constantly exploring loss of weight and raising structural strength.Some large complicated parts, especially main force support structure part, as the crossbeam of aircraft, bulkhead and wallboard, generally adopted integrated structure design.
The comprehensive action of the factor such as release, cutter and clamping of material residual stress because self structure is complex-shaped, geometry is asymmetric, thin-walled position is many, in the low and course of processing of self rigidity, it is very serious that aviation integral structure component adds post-construction deformation problem.Under existing technical qualification, only, by improving Workpiece structure, improve processing and loading clamp layout, the means such as optimization processing technology parameter are difficult to avoid completely the generation of machining deformation.Adopt high speed machining can make the machining deformation of integral structure component be effectively controlled, but for the part of some complex structure, poor rigidity, if aircraft target ship is because it has large size, plate-shaped curved-surface structure, make its machining deformation still very large.Aviation integral structure component machining deformation problem has become one of present generation aircraft manufacturing technology bottleneck.
In order to ensure the manufacturing accuracy of aviation integral structure component, except taking measures distortion preventing, also need the structural part to producing distortion to proofread and correct.
Summary of the invention
The object of this invention is to provide a kind of aircraft target ship part oscillating aging straightening method and oscillating aging corrector, in manufacturing processed, be out of shape the band stress assembly problem in excessive and assembling process to solve aircraft target ship part, improve anti-stress corrosion performance and the anti-fatigue performance of aircraft target ship part in aircraft utilization process.
A kind of aircraft target ship part oscillating aging straightening method, is characterized in that containing following conditioned disjunction step: 1) there is the aircraft target ship part of machine-shaping, and the theoretical profile of known this part, 2) there is an oscillating aging corrector, this device contains school shape platform, dot matrix Flexible Fixturing unit, supporting seat and vibrator, described school shape platform is supported on elastic supporting seat, the upper surface of school shape platform has the school shape face identical with the theoretical profile of the lower surface of aircraft target ship part, the both sides of the upper surface of school shape platform are provided with the connective slot (platform) of tie point configuration Flexible Fixturing unit, described dot matrix Flexible Fixturing unit is fixed on the crossbeam on the shape platform connective slot of school by multiple two ends and multiple clamping screws of being located on crossbeam form, described vibrator is fixed on the shape platform of school, 3) the aircraft target ship part of machine-shaping is placed on the school shape face of school shape platform, by the clamping screw compression aircraft target ship of dot matrix Flexible Fixturing unit, 4) start vibrator by Controlling System oscillating aging school shape platform and the dot matrix Flexible Fixturing structure being fixedly connected with it and aircraft target ship part are vibrated simultaneously, to eliminate and the internal stress of homogenizing aircraft target ship part.
The invention has the beneficial effects as follows: 1) utilize dot matrix Flexible Fixturing structure that strained aircraft target ship part is fixed on the shape platform of oscillating aging school, forcing to implement oscillating aging under the condition flattening, efficiently solving aircraft target ship part because variation in thickness is large, the defect of poor rigidity; 2) this apparatus structure is simple, and easy handling has solved the realistic problem that aircraft target ship part cannot oscillating aging school shape.
Below in conjunction with embodiment, the application is described in further detail.
Brief description of the drawings
Fig. 1 is Aircraft Sheet Metal Parts vibratory stress reliefing principle schematic.
Fig. 2 is aircraft target ship part.
Number in the figure explanation: 1 vibrator, 2 school shape platforms, 3 elastic supporting seats, 4 crossbeams, 5 aircraft target ship parts, 6 clamping screws, 7T type bolt and nut, 8 connective slots.
Embodiment
Referring to accompanying drawing, in embodiment, aircraft target ship part 5 is according to the aircraft wing wallboard of the theoretical sharp processing moulding of its design, its one side is plane in theory, another side is uneven, minimum wall thickness (MINI W.) is 3mm, and minimum wall thickness (MINI W.) is 15mm, and length is 6000mm, material is aluminium alloy 2324, shapes with numerically-controlled machine.For the inherent strain after its processing of homogenizing correcting deformed, the application has proposed it to carry out oscillating aging straightening method and oscillating aging corrector.In Fig. 1, aircraft target ship part vibration ageing device, contain school shape platform 2, dot matrix Flexible Fixturing unit, elastic supporting seat 3 and vibrator 1, school shape platform 2 is supported on elastic supporting seat 3, the upper surface of school shape platform 2 has the school shape face identical with the theoretical profile of the lower surface of aircraft target ship part, the both sides of the upper surface of school shape platform are provided with the connective slot 8 of tie point configuration Flexible Fixturing unit, described dot matrix Flexible Fixturing unit is fixed on the crossbeam 4 on the shape platform connective slot of school by multiple two ends and multiple clamping screws 6 of being located on crossbeam form
Each crossbeam 4 forms a dot matrix Flexible Fixturing unit with the clamping screw 6 being fixed on crossbeam, and multiple dot matrix Flexible Fixturing unit, along oscillating aging school shape platform longitudinal arrangement, forms whole dot matrix Flexible Fixturing structure.The T shape structure of the connective slot of dot matrix Flexible Fixturing structure on crossbeam 4 two ends places and oscillating aging school shape platform 2 is rigidly connected by T-shaped bolt and nut 7, is rigidly fixed in the upper of oscillating aging school shape platform 2 for generation of the vibrator 1 use clamp of vibrational energy.Four elastic supporting seats 3 of oscillating aging school shape platform 2 use support, and its effect is that vibration damping is so that protection work ground.While implementing oscillating aging, first unload the crossbeam of dot matrix Flexible Fixturing unit from school shape platform, the aircraft target ship part 5 of machine-shaping is placed on the school shape face of school shape platform 2, be fixed on one by one again the both sides of school shape platform with the crossbeam of dot matrix Flexible Fixturing unit, compress aircraft target ship with clamping screw; Vibrator 1 is electrically connected with Controlling System, open the Controlling System of vibrator 1, oscillating aging school shape platform 2 and the dot matrix Flexible Fixturing structure being fixedly connected with it and aircraft target ship part 5 are vibrated simultaneously, to eliminate and the internal stress of homogenizing aircraft target ship part.In order to obtain accurately the feedback signal of oscillating aging, preferably vibro-pickup (not shown) is sticked on aircraft target ship part, complete after oscillating aging, unload aircraft target ship part.
Claims (2)
1. an aircraft target ship part oscillating aging straightening method, is characterized in that containing following conditioned disjunction step: 1) there is the aircraft target ship part of machine-shaping, and the theoretical profile of known this part, 2) there is an oscillating aging corrector, this device contains school shape platform, dot matrix Flexible Fixturing unit, elastic supporting seat and vibrator, described school shape platform is supported on elastic supporting seat, the upper surface of school shape platform has the school shape face identical with the theoretical profile of the lower surface of aircraft target ship part, the both sides of the upper surface of school shape platform are provided with the connective slot (platform) of tie point configuration Flexible Fixturing unit, described dot matrix Flexible Fixturing unit is fixed on the crossbeam on the shape platform connective slot of school by multiple two ends and multiple clamping screws of being located on crossbeam form, described vibrator is fixed on the shape platform of school, 3) the aircraft target ship part of machine-shaping is placed on the school shape face of school shape platform, by the clamping screw compression aircraft target ship of dot matrix Flexible Fixturing unit, 4) start vibrator by Controlling System oscillating aging school shape platform and the dot matrix Flexible Fixturing structure being fixedly connected with it and aircraft target ship part are vibrated simultaneously, to eliminate and the internal stress of homogenizing aircraft target ship part.
2. an aircraft target ship part vibration ageing device, contain school shape platform, dot matrix Flexible Fixturing unit, elastic supporting seat and vibrator, it is characterized in that described school shape platform is supported on elastic supporting seat, the upper surface of school shape platform has the school shape face identical with the theoretical profile of the lower surface of aircraft target ship part, the both sides of the upper surface of school shape platform are provided with the connective slot of tie point configuration Flexible Fixturing unit, described dot matrix Flexible Fixturing unit is fixed on the crossbeam on the shape platform connective slot of school by multiple two ends and multiple clamping screws of being located on crossbeam form, described vibrator is fixed on the shape platform of school.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410299300.4A CN104120230A (en) | 2014-06-27 | 2014-06-27 | Airplane wallboard part vibration aging straightening method and vibration aging straightening device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410299300.4A CN104120230A (en) | 2014-06-27 | 2014-06-27 | Airplane wallboard part vibration aging straightening method and vibration aging straightening device |
Publications (1)
| Publication Number | Publication Date |
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| CN104120230A true CN104120230A (en) | 2014-10-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201410299300.4A Pending CN104120230A (en) | 2014-06-27 | 2014-06-27 | Airplane wallboard part vibration aging straightening method and vibration aging straightening device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106197915A (en) * | 2016-06-24 | 2016-12-07 | 北京航空航天大学 | A kind of position the method that oscillating aging controls timeliness part fatigue life |
| CN110846494A (en) * | 2019-12-20 | 2020-02-28 | 北京理工大学 | Vibration aging clamping device |
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| US4968359A (en) * | 1989-08-14 | 1990-11-06 | Bonal Technologies, Inc. | Stress relief of metals |
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2014
- 2014-06-27 CN CN201410299300.4A patent/CN104120230A/en active Pending
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| US4001053A (en) * | 1972-04-21 | 1977-01-04 | Eim Electric Co., Ltd. | Method of removing residual stress of a work formed of metal or ceramic and a sealing apparatus |
| US4968359A (en) * | 1989-08-14 | 1990-11-06 | Bonal Technologies, Inc. | Stress relief of metals |
| CN202106321U (en) * | 2010-12-30 | 2012-01-11 | 成都飞机工业（集团）有限责任公司 | Skin riveted flexible clamp |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106197915A (en) * | 2016-06-24 | 2016-12-07 | 北京航空航天大学 | A kind of position the method that oscillating aging controls timeliness part fatigue life |
| CN110846494A (en) * | 2019-12-20 | 2020-02-28 | 北京理工大学 | Vibration aging clamping device |
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Application publication date: 20141029 |