CN110625335A - Welding deformation control method for high-aspect-ratio framework skin wing type component - Google Patents
Welding deformation control method for high-aspect-ratio framework skin wing type component Download PDFInfo
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- CN110625335A CN110625335A CN201910822627.8A CN201910822627A CN110625335A CN 110625335 A CN110625335 A CN 110625335A CN 201910822627 A CN201910822627 A CN 201910822627A CN 110625335 A CN110625335 A CN 110625335A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K31/00—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups
- B23K31/003—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups relating to controlling of welding distortion
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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Abstract
The invention belongs to the technical field of welding deformation control, and particularly relates to a welding deformation control method for a large-aspect-ratio framework skin wing component. The welding deformation control method comprises the steps of respectively welding the front section and the rear section of the missile wing, and then integrally welding the front section and the rear section of the missile wing which are welded in a segmented mode on a tool. The segmented welding comprises skin forming, framework forming, repair before welding, positioning welding of the skin and the periphery of the framework, positioning welding of the skin and the framework ribs, formal welding of the skin and the framework ribs and formal welding of the skin and the periphery of the framework. The invention adopts a proper welding principle in the welding process, so that the deviation between the overall dimension and the theoretical profile after the integral welding is finished is less than 1.5mm, the precision control effect is good, and the invention has been successfully applied to aircraft tests.
Description
Technical Field
The invention belongs to the technical field of welding deformation control, and particularly relates to a welding deformation control method for a large-aspect-ratio framework skin wing component.
Background
In recent years, along with the continuous improvement of the speed of an aircraft, the appearance precision of wing type components for controlling flight postures is required to be higher and higher, for the missile wing components with the length dimension of 2700mm and the width dimension of 370mm, the theoretical appearance deviation is smaller than 1.0mm, and in order to adapt to supersonic flight, the wing type components are mostly framework skin structures with large aspect ratio, the welding is adopted to complete, meanwhile, the weight is lightened and the weight is reduced, the skins are mostly thin-wall rib lattice structures, the rigidity is poor, the frameworks are narrow-rib long and narrow structures, and the deformation control of the skin and the framework assembly welding is a technical difficulty.
Disclosure of Invention
Technical problem to be solved
The invention provides a welding deformation control method for a high-aspect-ratio framework skin wing member, and aims to solve the technical problem of how to control the welding deformation of the high-aspect-ratio wing member.
(II) technical scheme
In order to solve the technical problem, the invention provides a welding deformation control method of a high-aspect-ratio framework skin wing type component, which comprises the following steps:
firstly, respectively executing the steps S1-S5 on the front and rear sections of the missile wing to carry out segmented welding:
s1, skin forming: carrying out thermal leveling on the mechanically-machined skin;
s2, skeleton molding: carrying out rough machining and finish machining on the framework;
s3, repair before welding: presetting process repair allowance on the periphery of the skin, and repairing the skin into a lower limit structure of the periphery of the framework through clamp repair;
s4, tack welding: the positioning welding is carried out in two steps, including:
s4.1, positioning and welding the skin and the frame periphery: the skin is intermittently positioned with the circumference of the framework in a flattened state, so that the skin is ensured to be flat; the positioning welding follows the principle of symmetrical welding, namely after positioning welding is carried out on a certain part on one side of the airfoil, the airfoil is turned over, and positioning welding is carried out on the symmetrical part according to the same parameters;
s4.2, positioning and welding the skin and the framework ribs: according to the principle of jump discontinuous double-sided symmetrical welding and the principle of welding from a rib thin area to a rib thick area, penetrating welding and positioning are carried out on the skin and ribs in the framework, so that the skin is ensured to be flatly fixed on the framework;
s5, formal welding: the formal welding is carried out in two steps, including:
s5.1, formally welding the skin and the framework ribs: welding the skin and the ribs inside the framework in a penetrating manner according to the principle of jump symmetrical welding and welding from a thin area to a thick area, wherein in the welding process, after one rib is welded, the wing surface is turned over, the rib opposite to the wing surface is welded, meanwhile, when the next rib is welded, the rib far away from the previous rib is selected for welding, and the deformation can be effectively controlled by adopting the jump welding sequence;
s5.2, formally welding the skin and the frame periphery: fully welding the skin and the periphery of the framework according to the intermittent segmented symmetrical welding principle;
step two, welding the integral airfoil:
and S6, integrally welding the front and rear sections of the missile wings which are welded in the segmented mode on a tool.
Further, in step S1, the skin which is formed by the addition of the TA15 plate machine is subjected to heat leveling by adopting vacuum thermal shape correction parameters of 750 ℃ and heat preservation for 3h-4h, and the flatness of the skin before welding is controlled within 0.3.
Further, in step S2, the skeleton circumference chord plane size is controlled to be within 0.5.
Further, in step S3, a process trimming margin of 0.3mm is preset on the periphery of the skin, and the skin is trimmed to the lower limit structure of the periphery of the framework by clinching, wherein the welding gap is required to be less than 0.1mm, and the step difference is required to be less than 0.1 mm.
Further, in step S4.1, the skin and the frame periphery are tack welded by manual argon arc welding or laser welding.
Further, in step S6, welding is performed in a state that the difference between chord plane sizes of the two sections of airfoils is less than 0.5, positioning welding is performed first, positioning welding is performed sequentially from the thin area of the outer edge of the airfoil to the thick area of the root of the airfoil, after one side is welded, the other side of the airfoil is turned over, after the to-be-welded seam is cooled to room temperature, a butt-joint welding seam is formally welded in a direction from the thick area to the thin area, after the to-be-welded seam is cooled to room temperature, the airfoil is turned over, and another side of the to-be-welded seam is formally welded in a direction from the thick area to the thin; and disassembling the tool after the airfoil surface is cooled to room temperature.
(III) advantageous effects
The invention provides a welding deformation control method of a large-aspect-ratio framework skin wing component. The segmented welding comprises skin forming, framework forming, repair before welding, positioning welding of the skin and the periphery of the framework, positioning welding of the skin and the framework ribs, formal welding of the skin and the framework ribs and formal welding of the skin and the periphery of the framework. The invention adopts a proper welding principle in the welding process, so that the deviation between the overall dimension and the theoretical profile after the integral welding is finished is less than 1.5mm, the precision control effect is good, and the invention has been successfully applied to aircraft tests.
Detailed Description
In order to make the objects, contents and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be given in conjunction with examples.
The embodiment provides a welding deformation control method for a high-aspect-ratio framework skin wing component, and the high-aspect-ratio framework skin wing component is formed by assembling and welding two structures, namely a titanium alloy thin-wall rib double-layer metal skin and a cast titanium alloy framework. The welding of covering and skeleton, the butt joint position of the front and back sections of the missile wing all adopt laser welding, and there is a bending line in the covering of the back section of the missile wing.
The welding deformation control method of the embodiment specifically includes the following steps:
firstly, respectively executing the steps S1-S5 on the front and rear sections of the missile wing to carry out segmented welding:
s1, skin forming: in order to improve the flatness of the weak rigid skin before welding, the skin which is additionally formed by the TA15 plate machine is subjected to thermal leveling by adopting the technological parameters of thermal insulation for 3-4 h at 750 ℃, and the flatness of the skin before welding is controlled within 0.3.
S2, skeleton molding: and (5) performing rough and finish machining on the framework, and controlling the plane size of the circumferential chord of the framework within 0.5.
S3, repair before welding: the skin periphery is preset with the process repair allowance of 0.3mm, the skin is repaired to the lower limit structure of the framework periphery through clamp repair, the welding gap is required to be smaller than 0.1mm, and the step difference is required to be smaller than 0.1 mm.
S4, tack welding: the positioning welding is carried out in two steps, including:
s4.1, positioning and welding the skin and the frame periphery: and the skin is intermittently positioned with the circumference of the framework in a flattened state by manual argon arc welding or laser welding, so that the flatness of the skin is ensured. The length of the positioning point is executed according to the reference of the distance of 50mm and the length of 20mm, and the positioning point can be adaptively adjusted according to the actual step difference condition. The positioning welding is carried out according to the principle of symmetrical welding, namely, after a certain part on one side of the airfoil surface is positioned and welded, the airfoil surface is turned over, and the positioning welding is carried out on the symmetrical part according to the same parameters.
S4.2, positioning and welding the skin and the framework ribs: according to the principle of jump discontinuous double-sided symmetrical welding and the principle of welding from a rib thin area to a rib thick area, the skin and ribs in the framework are penetrated, welded and positioned, and the skin is ensured to be flatly fixed on the framework.
S5, formal welding: the formal welding is carried out in two steps, including:
s5.1, formally welding the skin and the framework ribs: and (4) carrying out penetration welding on the skin and ribs inside the framework according to the principle of jump symmetrical welding and welding from a thin area to a thick area. During welding, after one rib is welded, the wing surface is turned over, the rib on the opposite side is welded, meanwhile, when the next rib is welded, the rib far away from the previous rib is selected for welding, and deformation can be effectively controlled by adopting a skip welding sequence.
S5.2, formally welding the skin and the frame periphery: and performing full welding on the skin and the periphery of the framework according to the intermittent segmented symmetrical welding principle.
Step two, welding the integral airfoil:
s6, integrally welding the front and rear sections of the missile wing after the section welding on the tool, wherein:
welding is carried out under the condition that the size difference of chord planes of two sections of airfoils is less than 0.5, positioning welding is firstly carried out, positioning welding is carried out from the position of a thin area at the outer edge of the airfoil to a thick area at the root of the airfoil in sequence, the positioning welding can be carried out according to the size of 20mm of the length and 30mm of the positioning welding, after one side is welded, the other side of the airfoil is welded in a turnover mode, after a to-be-welded seam is cooled to room temperature, a butt-joint welding seam is formally welded in the direction from the thick area to the thin area, the airfoil is turned over after the to-be-welded seam is cooled to room temperature, and another side of. And after the airfoil is cooled to room temperature, the tool is disassembled, so that the deformation can be effectively controlled after the cooling time is long enough.
Setting welding process parameters: and selecting high-speed and high-power welding parameters on the premise that the parameters of the butt joint part meet the penetration, wherein after the penetration welding parameters penetrate through the skin, the requirement that the fusion width of the skin and the ribs is 0.8 is met. The welding sequence is carried out according to the principle of symmetrically welding at two sides and welding from a thin area to a rear area, and the ideal deformation control effect of the airfoil surface component can be achieved.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (6)
1. A welding deformation control method for a high aspect ratio framework skin wing component is characterized by comprising the following steps:
firstly, respectively executing the steps S1-S5 on the front and rear sections of the missile wing to carry out segmented welding:
s1, skin forming: carrying out thermal leveling on the mechanically-machined skin;
s2, skeleton molding: carrying out rough machining and finish machining on the framework;
s3, repair before welding: presetting process repair allowance on the periphery of the skin, and repairing the skin into a lower limit structure of the periphery of the framework through clamp repair;
s4, tack welding: the positioning welding is carried out in two steps, including:
s4.1, positioning and welding the skin and the frame periphery: the skin is intermittently positioned with the circumference of the framework in a flattened state, so that the skin is ensured to be flat; the positioning welding follows the principle of symmetrical welding, namely after positioning welding is carried out on a certain part on one side of the airfoil, the airfoil is turned over, and positioning welding is carried out on the symmetrical part according to the same parameters;
s4.2, positioning and welding the skin and the framework ribs: according to the principle of jump discontinuous double-sided symmetrical welding and the principle of welding from a rib thin area to a rib thick area, penetrating welding and positioning are carried out on the skin and ribs in the framework, so that the skin is ensured to be flatly fixed on the framework;
s5, formal welding: the formal welding is carried out in two steps, including:
s5.1, formally welding the skin and the framework ribs: welding the skin and the ribs inside the framework in a penetrating manner according to the principle of jump symmetrical welding and welding from a thin area to a thick area, wherein in the welding process, after one rib is welded, the wing surface is turned over, the rib opposite to the wing surface is welded, meanwhile, when the next rib is welded, the rib far away from the previous rib is selected for welding, and the deformation can be effectively controlled by adopting the jump welding sequence;
s5.2, formally welding the skin and the frame periphery: fully welding the skin and the periphery of the framework according to the intermittent segmented symmetrical welding principle;
step two, welding the integral airfoil:
and S6, integrally welding the front and rear sections of the missile wings which are welded in the segmented mode on a tool.
2. The welding deformation control method of claim 1, wherein in step S1, the skin formed by the TA15 plate machine is heat leveled using vacuum thermal sizing parameters of 750 ℃ and 3h to 4h, and the flatness of the skin before welding is controlled within 0.3.
3. The welding deformation control method according to claim 1, wherein in said step S2, the skeleton circumference chord plane size is controlled to be within 0.5.
4. The welding deformation control method according to claim 1, wherein in step S3, a process trimming margin of 0.3mm is preset on the periphery of the skin, and the skin is trimmed to the lower limit structure of the periphery of the skeleton by clinching, wherein the welding gap is required to be less than 0.1mm, and the step difference is required to be less than 0.1 mm.
5. The welding deformation control method according to claim 1, wherein in step S4.1, the skin and the skeleton periphery are welded in position by manual argon arc welding or laser welding.
6. A welding deformation control method according to claim 1, wherein in step S6, welding is performed under the condition that the difference between the chord plane sizes of the two sections of airfoils is less than 0.5, tack welding is performed first, tack welding is performed sequentially from the thin region position of the outer edge of the airfoil to the thick region of the root, after one side is welded, the other side of the airfoil is welded by turning over, after the weld to be welded is cooled to room temperature, the butt weld is formally welded in the direction from the thick region to the thin region, after the weld to be welded is cooled to room temperature, the airfoil is turned over, and the other side of the weld is formally welded in the direction from the thick region to the thin region by using the same parameters, thereby completing the welding; and disassembling the tool after the airfoil surface is cooled to room temperature.
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| CN201910822627.8A CN110625335B (en) | 2019-09-02 | 2019-09-02 | Welding deformation control method for high-aspect-ratio framework skin wing type component |
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| CN110625335B CN110625335B (en) | 2020-05-26 |
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Cited By (4)
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| CN112643234A (en) * | 2020-12-08 | 2021-04-13 | 北京星航机电装备有限公司 | Lightweight wing rudder component high-energy-beam welding assembly tool and assembly method |
| CN113020792A (en) * | 2021-03-22 | 2021-06-25 | 北京新风航天装备有限公司 | Robot laser welding method for skeleton multi-skin component |
| CN113941809A (en) * | 2021-09-23 | 2022-01-18 | 北京星航机电装备有限公司 | Large thin-wall automatic pressing device and method |
| CN115139000A (en) * | 2022-05-27 | 2022-10-04 | 中国能源建设集团天津电力建设有限公司 | Jumping and centering welding method |
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