CN103572188A - Electromagnetic reinforcement method for surface of 7475-T761 aluminium alloy sheet - Google Patents
Electromagnetic reinforcement method for surface of 7475-T761 aluminium alloy sheet Download PDFInfo
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- CN103572188A CN103572188A CN201310552486.5A CN201310552486A CN103572188A CN 103572188 A CN103572188 A CN 103572188A CN 201310552486 A CN201310552486 A CN 201310552486A CN 103572188 A CN103572188 A CN 103572188A
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Abstract
The invention discloses an electromagnetic reinforcement method for a surface of a 7475-T761 aluminium alloy sheet. The method is characterized in that the 7475 aluminium alloy sheet is impacted by a rivet die by using action of an electromagnetic field pulse on the surface of a spare part; macroscopic residual compressive stress is generated at the surface layer of the sheet, so that the microstructure changes. Thus, the fatigue lift of the alloy is greatly improved. The method comprises the following reinforcement steps: mounting and fixing the sheet, and electromagnetic reinforcement. By adopting the electromagnetic reinforcement process parameters proposed by the invention, the fatigue lift of the 7475 aluminium alloy sheet can be significantly improved.
Description
Technical field
The present invention is a kind of 7475-T761 Aluminium Alloy Plate surface electrical magnetic enhancement method, belongs to aluminum alloy surface strengthening technology.
Background technology
7475-T761 Aluminium Alloy Plate not only intensity is high, also has good fracture toughness property, anti-stress corrosion performance and anti-fatigue performance, is applicable to the structural part of the primary load bearings such as covering processed, long purlin, has wide application potential.Along with further developing of technology, to having proposed requirements at the higher level the work-ing life of Aircraft Main load bearing structure of new generation, the main stress peening process that adopts is strengthened structural part, but existing reinforcing process has destruction to a certain degree to material surface integrity, and anti-fatigue performance has certain damage.
Summary of the invention
The present invention designs a kind of 7475-T761 Aluminium Alloy Plate surface electrical magnetic enhancement method is provided for above-mentioned the deficiencies in the prior art just, its objective is and make 7475-T761 Aluminium Alloy Plate component after electromagnetism strengthening, increase substantially its fatigue property, to meet the requirement of aircraft industry.
The object of the invention is to realize by following technical measures:
This kind of 7475-T761 Aluminium Alloy Plate surface electrical magnetic enhancement method, is characterized in that: the step of the method is:
(1) thin plate is installed
By thickness be 7475-T761 Aluminium Alloy Plate (1) below 6mm treat that strengthening surface is downwards towards dolly set (3), rubber pad (2) with thickness 2mm between Aluminium Alloy Plate (1) and dolly set (3) is isolated, the solenoid of electromagnetism intensifying device (5) is placed on the upper surface of Aluminium Alloy Plate (1), and by bolt (4), solenoid (5), Aluminium Alloy Plate (1), rubber pad (2), dolly set (3) is fixed together;
(2) electromagnetism strengthening
By electromagnetism intensifying device, Aluminium Alloy Plate (1) is applied to emp and carry out intensive treatment.
Electric capacity in electromagnetism intensifying device is 2400 μ f, and voltage is 1～2KV.
Technical scheme of the present invention is based on electromagnetic pulse forming and shot-peening principle, electromagnetic pulse forming principle and shot peening strengthening principle are combined, for 7475-T761 aluminum alloy outer cover class part service requirements, carry out the electromagnetism Research on Strengthen Techniques of this latten, utilize electromagnetic field pulse to act on component surface, make 7475 Aluminium Alloy Plates impact dolly set, upper layer at thin plate produces macroscopical residual compressive stress, heterogeneous microstructure is changed, thereby increased substantially the fatigue lifetime of alloy, made to meet its work-ing life the design requirements of aircraft.Laying a good foundation with material of airliner in ，Hai Jiangwei China development simultaneously, therefore has significant Social benefit and economic benefit to the research of this 7475 sheet products electromagnetism reinforcing process.
Accompanying drawing explanation
Fig. 1 is the structural representation of the strengthening and processing device of technical solution of the present invention
Embodiment
Below with reference to drawings and Examples, technical solution of the present invention is further described:
Shown in accompanying drawing 1, this kind of 7475-T761 Aluminium Alloy Plate surface electrical magnetic enhancement method, described 7475-T761 aluminium alloy forces overaging to manage aluminium alloy everywhere for artificial, its chemical composition and weight percent are Zn5.7%, Mg2.2%, Cu1.6%, Cr0.22%, surplus is Al, and the step of the method is:
(1) thin plate is installed
The 7475-T761 Aluminium Alloy Plate 1 that is 6mm by thickness treat that strengthening surface is downwards towards dolly set 3, rubber pad 2 with thickness 2mm between Aluminium Alloy Plate 1 and dolly set 3 is isolated, the solenoid of electromagnetism intensifying device 5 is placed on the upper surface of Aluminium Alloy Plate 1, and by bolt 4, solenoid 5, Aluminium Alloy Plate 1, rubber pad 2, dolly set 3 is fixed together;
Described dolly set 3 is by being assemblied in the multi-point support structure that on mold bottom, equally distributed snap head bolt forms.Snap head bolt be of a size of φ 6mm, the gap between each snap head bolt is 3mm;
(2) electromagnetism strengthening
By electromagnetism intensifying device, Aluminium Alloy Plate (1) is applied to emp and carry out intensive treatment, between pulse propulsion source 7 in electromagnetism intensifying device and solenoid 5, there is wire to be connected, on wire, there is trip switch 8, circuit control device 6 is connected with pulse propulsion source 7, for setting pulse propulsion source 7 charging voltage parameters, be shown in Table 1, in treating processes, disconnecting trip switch 8 charges by circuit control device 6 paired pulses propulsion sources 7, after charging finishes, Closed control switch 8, pulse propulsion source 7 is connected with solenoid 5, carry out discharge operation, Aluminium Alloy Plate 17 is applied to emp.
Table 1 electromagnetism strengthening fatigue property improves effect comparison
Table 1 comprises the fatigue lifetime of product under electromagnetism intensive conditions not.Test-results explanation, adopts after the related electromagnetism reinforcing process parameter strengthening of this patent, and the fatigue lifetime of 7475-T761 Aluminium Alloy Plate is the highest has improved 2.63 times.
Compared with prior art, the advantage of technical solution of the present invention is:
1, improved the fatigue property of 7475-T761 Aluminium Alloy Plate component; The 7475-T761 Aluminium Alloy Plate fatigue life ratio of processing through the present invention is not implemented the fatigue lifetime of electromagnetism intensive treatment product and has been improved 2～2.63 times.The reason that after electromagnetism strengthening, fatigue property improves is, causes very high macroscopical residual compressive stress and the variation of heterogeneous microstructure in component surface strengthening layer.With
Under upper two kinds of strengthening mechanism comprehensive actions, improve the fatigue resistance in product strengthening layer, thereby increased substantially the fatigue property of 7475-T761 Aluminium Alloy Plate component.
2, electromagnetism strengthening has improved the strengthening homogeneity of 7475-T761 Aluminium Alloy Plate component, and electromagnetic field pulse can not destroyed thin sheet surface quality, rubber pad has reduced the possibility that thin plate impacts dolly set generation impression simultaneously, make thin plate product surface integrity very good, product fatigue property is obviously improved; Operating procedure is easy simultaneously, is beneficial to production control.
Claims (2)
1. a 7475-T761 Aluminium Alloy Plate surface electrical magnetic enhancement method, is characterized in that: the step of the method is:
(1) thin plate is installed
By thickness be 7475-T761 Aluminium Alloy Plate (1) below 6mm treat that strengthening surface is downwards towards dolly set (3), rubber pad (2) with thickness 2mm between Aluminium Alloy Plate (1) and dolly set (3) is isolated, the solenoid of electromagnetism intensifying device (5) is placed on the upper surface of Aluminium Alloy Plate (1), and by bolt (4), solenoid (5), Aluminium Alloy Plate (1), rubber pad (2), dolly set (3) is fixed together;
(2) electromagnetism strengthening
By electromagnetism intensifying device, Aluminium Alloy Plate (1) is applied to emp and carry out intensive treatment.
2. 7475-T761 Aluminium Alloy Plate surface electrical magnetic enhancement method according to claim 1, is characterized in that: the electric capacity in electromagnetism intensifying device is 2400 μ f, and voltage is 1～2KV.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310552486.5A CN103572188A (en) | 2013-11-08 | 2013-11-08 | Electromagnetic reinforcement method for surface of 7475-T761 aluminium alloy sheet |
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| CN201310552486.5A CN103572188A (en) | 2013-11-08 | 2013-11-08 | Electromagnetic reinforcement method for surface of 7475-T761 aluminium alloy sheet |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107299217A (en) * | 2017-06-06 | 2017-10-27 | 武汉理工大学 | A kind of aeroengine components surface residual stress electromagnetic field regulates and controls method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107299217A (en) * | 2017-06-06 | 2017-10-27 | 武汉理工大学 | A kind of aeroengine components surface residual stress electromagnetic field regulates and controls method |
| CN107299217B (en) * | 2017-06-06 | 2019-01-25 | 武汉理工大学 | A kind of aeroengine components surface residual stress electromagnetic field regulation method |
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Application publication date: 20140212 |