CN110625210B - Welding deformation control tool and method for wing rudder with lightweight structure - Google Patents
Welding deformation control tool and method for wing rudder with lightweight structure Download PDFInfo
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- CN110625210B CN110625210B CN201910822615.5A CN201910822615A CN110625210B CN 110625210 B CN110625210 B CN 110625210B CN 201910822615 A CN201910822615 A CN 201910822615A CN 110625210 B CN110625210 B CN 110625210B
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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
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
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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
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/008—Soldering within a furnace
-
- 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
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/20—Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating
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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
- B23K3/00—Tools, devices, or special appurtenances for soldering, e.g. brazing, or unsoldering, not specially adapted for particular methods
- B23K3/08—Auxiliary devices therefor
- B23K3/087—Soldering or brazing jigs, fixtures or clamping means
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Abstract
The invention provides a welding deformation control tool for a wing rudder with a lightweight structure, wherein the number of the welding deformation control tool is the same as that of parts of the wing rudder according to profile parting, a lower support plate is used for supporting a lower skin, a frame and a honeycomb core of the wing rudder structure, the upper surface of an upper pressure plate is a flat plate, and the part of the lower surface, which is attached to the upper skin, is in a copying design; a gravity pressing block is arranged on the upper surface of the upper pressing plate, and pressure is uniformly applied to the upper skin through the upper pressing plate; the positioning baffle plates are arranged around the upper pressing plate and the lower supporting plate, so that the skins, the honeycomb cores and the frame are prevented from sliding and dislocating in the assembling or welding process, the effectiveness and uniformity of pressurization of all parts are ensured, and gaps caused by local profile deviation are eliminated. The welding deformation control tool provided by the invention can effectively solve the problem of deformation control of the wing rudder type component with the lightweight structure in the welding process, has the advantages of simple structure, low manufacturing cost and good precision control effect, and has been successfully applied to flight tests of aircrafts.
Description
Technical Field
The invention belongs to the technical field of welding deformation control, and particularly relates to a vacuum brazing welding deformation control tool and method for a wing rudder with a lightweight structure in an ultrahigh-speed aircraft.
Background
In recent years, with the increasing speed of the aircraft, the aircraft is often in a high-temperature environment (such as a high temperature of more than 800 ℃) due to the aerodynamic heat generated by surface friction during the operation process of the aircraft, and the thermal protection system of the aircraft bears severe environmental tests in the aspects of heat insulation and mechanical load bearing capacity. At present, the environmental temperature for the research on the wing rudder metal protection in China is mainly concentrated between 400 ℃ and 600 ℃, and most of metal heat-proof materials are titanium alloy or aluminum alloy, are limited by the physical properties of the materials and are difficult to bear higher temperature.
The wing rudder with the lightweight structure is formed by combining, assembling and brazing three structures, namely a thin-wall special-shaped curved surface metal skin, a high-temperature alloy honeycomb core and a frame, the integral structure is a main bearing part which is highly lightweight and has good rigidity, the weight of the bearing structure is obviously reduced while the performance of a component is improved, the lightweight metal honeycomb structure is applied to the main bearing part, the high-temperature resistance and weight reduction requirements of an aircraft can be met, the wing rudder is an important component part of a hypersonic aircraft structure system, has great advantages in weight reduction, heat insulation and bearing compared with the traditional form of the frame skin, can be used for a long time below 900 ℃, and the highest working temperature can reach 1000 ℃.
Disclosure of Invention
Technical problem to be solved
The invention provides a welding deformation control tool and method for a wing rudder with a lightweight structure, and aims to solve the technical problem of how to control the welding deformation of the wing rudder with the lightweight structure.
(II) technical scheme
In order to solve the technical problem, the invention provides a welding deformation control tool for a wing rudder with a lightweight structure, which comprises a lower support plate, an upper pressure plate, a positioning baffle, a positioning pin and a hexagon bolt; the number of the lower supporting plates and the number of the upper pressing plates are the same as the number of parts of the wing rudder according to profile parting; the lower supporting plate is fixed on the lower platform through positioning pins and is used for supporting a lower skin, a frame and a honeycomb core of the wing rudder structure, the upper pressing plates are fixed through hexagonal bolts, and each upper pressing plate can independently pressurize the upper skin of each wing rudder; the upper surface of the upper pressure plate is a flat plate, and the part of the lower surface, which is jointed with the upper skin, is of a copying design; a gravity pressing block is arranged on the upper surface of the upper pressing plate, and pressure is uniformly applied to the upper skin through the upper pressing plate; the positioning baffle plates are arranged around the upper pressing plate and the lower supporting plate, so that the skins, the honeycomb cores and the frame are prevented from sliding and dislocating in the assembling or welding process, the effectiveness and uniformity of pressurization of all parts are ensured, and gaps caused by local profile deviation are eliminated.
Furthermore, the lower supporting plate, the upper pressing plate and the positioning baffle are processed by graphite.
The invention also provides a welding deformation control method of the light-weight structure wing rudder, wherein the light-weight structure wing rudder consists of an upper skin, a honeycomb core, a frame and a lower skin, and is divided into a plurality of parts; the welding deformation control method comprises the following steps:
s1, cleaning: removing oil stains and organic matters on the surface of each part to be welded in the wing rudder;
s2, assembling: assembling each to-be-welded part processed in place according to a model diagram, and checking the quality of an assembly gap of a welding part;
s3, adding brazing filler metal: foil belt brazing filler metal is preset on the inner side of the skin, and the foil belt brazing filler metal is positioned by an energy storage spot welding machine after being laid, so that falling off is avoided;
s4, loading into a vacuum brazing tool: transferring the assembled parts into the welding deformation control tool, applying pressure to the upper skin through a gravity pressing block arranged on the upper pressing plate, and eliminating a gap between the tool and the parts through gravity pressing;
s5, furnace charging and welding: pushing the tool assembly onto a support of a vacuum brazing furnace;
s6, setting welding process parameters;
s7, detection: and detecting the external dimension of the welded part and evaluating the welding effect.
Further, in step S2, the fitting clearance is less than or equal to 0.15 mm.
Further, in step S3, the gap between the layers of the brazing filler metal is controlled to be less than or equal to 0.1mm when the foil brazing filler metal is added; the thickness of each layer of the foil brazing filler metal is 0.0025mm, and 2-3 layers are used.
Further, in step S6, the welding process parameters are: controlling the temperature rise speed within 10 ℃/min, raising the temperature slowly, controlling the brazing temperature to be 1170-1180 ℃, keeping the temperature for 25-30 min, and controlling the vacuum degree to be not less than 3 multiplied by 10-2MPa。
(III) advantageous effects
The welding deformation control tool for the wing rudder with the lightweight structure is the same as the wing rudder in number of parts according to profile parting, the lower support plate is used for supporting the lower skin, the frame and the honeycomb core of the wing rudder structure, the upper surface of the upper pressure plate is a flat plate, and the part of the lower surface, which is attached to the upper skin, is in a copying design; a gravity pressing block is arranged on the upper surface of the upper pressing plate, and pressure is uniformly applied to the upper skin through the upper pressing plate; the positioning baffle plates are arranged around the upper pressing plate and the lower supporting plate, so that the skins, the honeycomb cores and the frame are prevented from sliding and dislocating in the assembling or welding process, the effectiveness and uniformity of pressurization of all parts are ensured, and gaps caused by local profile deviation are eliminated.
The welding deformation control tool provided by the invention can effectively solve the deformation control of the wing rudder type component with the lightweight structure in the welding process, can be used repeatedly at 1200 ℃, has a simple structure and low manufacturing cost, can effectively solve the key technical problem of welding deformation, has the advantages that the deviation between the overall dimension and the theoretical dimension is less than 0.5mm after the integral welding is finished, has a good precision control effect, and has been successfully applied to the flight test of an aircraft.
Drawings
Fig. 1 is a schematic structural view of a lightweight wing rudder in an embodiment of the present invention;
FIG. 2 is a schematic view of a welding deformation control tool in an embodiment of the invention;
fig. 3 is a result of measuring the deformation of the molded surface of the lightweight wing rudder after welding in the embodiment of the invention: (a) a lower profile detection result, and (b) an upper profile detection result.
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 made in conjunction with the accompanying drawings and examples.
The quality of the profile after welding affects the aerodynamic profile layout of the aircraft, so the control and guarantee of welding deformation are one of key core technologies for manufacturing the wing rudder with the lightweight structure.
The embodiment provides a tool and a method for controlling integral welding deformation of a honeycomb core, a frame and a skin of a metal honeycomb wing rudder with a lightweight structure.
The lightweight structure metal honeycomb wing rudder structure related to this embodiment mainly comprises upper skin 1, honeycomb core 2, frame 3 and lower skin 4, and the material that uses is nickel base wrought alloy GH4099, and wherein skin and honeycomb core are the special-shaped limit curvature, and it is higher to the requirement for appearance precision, and each face has two broken lines to form three faces and the honeycomb core laminating, and the honeycomb core is regular hexagon, and honeycomb wall thickness 0.12mm +/-0.03 mm, honeycomb inscribed circle diameter ϕ 10mm, highly by 30mm to 2mm transition. The structure is shown in fig. 1.
The welding deformation control method for the wing rudder with the lightweight structure provided by the embodiment specifically comprises the following steps:
s1, cleaning: removing oil stains, organic matters and the like on the surfaces of parts, and detecting the cleaning effect by adopting a water film method;
s2, assembling: assembling the skin, the frame and the honeycomb core parts which are processed in place according to a model diagram, and checking the quality of assembly gaps of welding parts, wherein the gap is required to be less than or equal to 0.15 mm;
s3, adding brazing filler metal: foil strip brazing filler metal is preset on the inner side of the skin, and the number of layers of the brazing filler metal and the gap between the layers of the brazing filler metal are required to be controlled when the brazing filler metal is added, so that the gap is smaller than or equal to 0.1 mm; properly adjusting the number of layers of foil brazing filler metal according to the profile of the honeycomb core to adjust the thickness of the honeycomb core, wherein the thickness of each layer of the foil brazing filler metal is 0.0025mm, 2-3 layers are generally used, and the foil brazing filler metal is positioned by an energy storage spot welding machine after being laid to avoid falling off;
s4, loading into a vacuum brazing tool: the vacuum brazing tool is key equipment for controlling welding deformation, and mainly comprises main components such as a lower supporting plate 5, an upper pressing plate 6, a positioning baffle 7, a positioning pin 8 and a hexagon bolt 9 according to the structural characteristics of the lightweight wing rudder, and the specific structure is shown in fig. 2.
The special tool is processed by adopting high-temperature resistant material fine graphite with smaller thermal expansion coefficient, three upper pressing plates 6 and three lower supporting plates 5 of the tool are independently divided according to the three-section part profiles of the wing rudder structure, and the three lower supporting plates 5 are fixed on the lower platform through positioning pins 8, so that the profiles are prevented from being influenced by the sliding of the three lower supporting plates 5. Three upper press plates 6 are fixed by hexagon bolts 9, and each molded surface can be independently pressurized through the three upper press plates 6, so that the defect that the molded surfaces are not stuck due to the fact that one plate is adopted for compression is avoided. All the upper surfaces of the three upper pressing plates 6 are flat plates, the parts of the lower surfaces, which are attached to the skin, are designed into a contour surface, and gravity pressing blocks are placed in the plane areas of the upper pressing plates 6. The three independent subarea tools are in a mode of vertically pressurizing the surfaces laid all around, adjustable multi-point acting force is vertically applied to the upper pressure plate 6 respectively, the force is uniformly applied to the skin through the upper pressure plate 6, the positioning baffle plates 7 are arranged on the peripheries of the upper pressure plate 6 and the lower support plate 5, the parts are prevented from sliding and dislocating in the assembling or welding process, the pressurizing effectiveness and uniformity of all parts are ensured, the gap caused by local surface deviation is eliminated, and the tool can be repeatedly used below 1200 ℃.
The frock can fix a position the tight part through locating baffle 7, rationally arranges the gravity briquetting position according to the part profile in the frock top, compresses tightly through gravity and eliminates the clearance of frock and part, and the at utmost makes covering and honeycomb core seam, guarantees covering and honeycomb core's total welding deformation and welding quality.
S5, furnace charging and welding: pushing the tool assembly onto a vacuum brazing furnace support through a feeding trolley, placing a gravity pressing block on an upper pressing plate 6 of the tool, screwing down the gravity pressing block by using a tool screw, pressing and attaching tightly a gap to be welded in the component under certain pressure, and simultaneously preventing the component from being misplaced under the action of external force;
s6, setting welding process parameters: the brazing process parameters have quite important influence on the brazing process and the joint quality, and the heat preservation time of the large brazed piece is longer than that of the small brazed piece, so that the heating uniformity is ensured. Considering that the lightweight wing rudder in the embodiment is a thin-wall structure, the thermal conductivity of the wing rudder is low, and the selection of a lower temperature rise speed is beneficial to uniformity and deformation control of a brazing seam structure.
The specific welding process parameters are as follows: controlling the temperature rise speed within 10 ℃/min, raising the temperature slowly, controlling the brazing temperature to be 1170-1180 ℃, keeping the temperature for 25-30 min, and controlling the vacuum degree to be not less than 3 multiplied by 10-2MPa。
S7, detection: and detecting the external dimension of the welded part and evaluating the welding effect. The profile test result after welding of the lightweight wing rudder is shown in fig. 3.
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 (3)
1. The welding deformation control tool for the wing rudder with the lightweight structure is characterized in that the wing rudder with the lightweight structure is formed by assembling and brazing three structures, namely a thin-wall special-shaped curved surface metal skin, a high-temperature alloy honeycomb core and a frame; the welding deformation control tool comprises a lower supporting plate, an upper pressing plate, a positioning baffle, a positioning pin and a hexagon bolt; the number of the lower supporting plates and the number of the upper pressing plates are the same as the number of parts of the wing rudder according to profile parting; the lower supporting plate is fixed on the lower platform through positioning pins and is used for supporting a lower skin, a frame and a honeycomb core of the wing rudder structure, the upper pressing plates are fixed through hexagonal bolts, and each upper pressing plate can independently pressurize the upper skin of each wing rudder; the upper surface of the upper pressure plate is a flat plate, and the part of the lower surface, which is jointed with the upper skin, is of a copying design; a gravity pressing block is arranged on the upper surface of the upper pressing plate, and pressure is uniformly applied to the upper skin through the upper pressing plate; the positioning baffle plates are arranged around the upper pressing plate and the lower supporting plate, so that the skins, the honeycomb cores and the frame are prevented from sliding and dislocating in the assembling or welding process, the effectiveness and uniformity of pressurization of all parts are ensured, and gaps caused by local profile deviation are eliminated.
2. The welding deformation control tool according to claim 1, wherein the lower supporting plate, the upper pressing plate and the positioning baffle are machined from graphite.
3. The welding deformation control method of the wing rudder with the lightweight structure is characterized in that the wing rudder with the lightweight structure consists of an upper skin, a honeycomb core, a frame and a lower skin, and is divided into a plurality of parts; the welding deformation control method comprises the following steps:
s1, cleaning: removing oil stains and organic matters on the surface of each part to be welded in the wing rudder;
s2, trial assembly: assembling each to-be-welded part processed in place according to a model diagram, and checking the quality of an assembly gap at a welding part, wherein the assembly gap is less than or equal to 0.15 mm;
s3, adding brazing filler metal: foil belt brazing filler metal is preset on the inner side of the skin, and the foil belt brazing filler metal is positioned by an energy storage spot welding machine after being laid, so that falling off is avoided; when the foil brazing filler metal is added, the gap between the layers of the brazing filler metal is controlled to be less than or equal to 0.1 mm; each layer of the foil brazing filler metal is 0.0025mm thick, and 2-3 layers are used;
s4, loading a vacuum brazing tool: transferring the assembled part into the welding deformation control tool according to claim 1 or 2, applying pressure to the upper skin through a gravity pressing block arranged on the upper pressing plate, and eliminating a gap between the tool and the part through gravity pressing;
s5, furnace charging and welding: pushing the tool assembly onto a support of a vacuum brazing furnace;
s6, setting welding technological parameters: controlling the temperature rise speed within 10 ℃/min, raising the temperature slowly, controlling the brazing temperature to be 1170-1180 ℃, keeping the temperature for 25-30 min, and controlling the vacuum degree to be not less than 3 multiplied by 10-2MPa；
S7, detection: and detecting the external dimension of the welded part and evaluating the welding effect.
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| CN111872508B (en) * | 2020-06-23 | 2022-07-29 | 上海航天精密机械研究所 | Diffusion brazing connection method for honeycomb structure |
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| CN113071163B (en) * | 2021-04-23 | 2022-10-18 | 北京机电工程研究所 | Bionic aircraft control surface preparation method |
| CN113414461B (en) * | 2021-08-23 | 2021-12-10 | 西安远航真空钎焊技术有限公司 | Brazing method of core body switching section assembly |
| CN115446406A (en) * | 2022-09-29 | 2022-12-09 | 中国航发动力股份有限公司 | Processing method of vacuum brazing heat shield assembly and fixture tool thereof |
| CN115922129A (en) * | 2022-12-28 | 2023-04-07 | 北京星航机电装备有限公司 | Forming process of crossed grid wing rudder |
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| JP2004042055A (en) * | 2002-07-09 | 2004-02-12 | Sumitomo Precision Prod Co Ltd | Brazing method for plate fin type heat exchanger |
| CN102489924B (en) * | 2011-12-22 | 2014-11-19 | 浙江大学 | Combined type flexible clamp for vacuum brazing of core body of plate-fin type aluminum heat exchanger |
| CN102744490A (en) * | 2012-07-27 | 2012-10-24 | 上海无线电设备研究所 | Brazing anti-deformation clamp for planar antenna and assembling method thereof |
| CN102873491A (en) * | 2012-10-19 | 2013-01-16 | 上海鹰峰电子科技有限公司 | Vacuum brazing tool for water-cooling plate |
| CN104400283B (en) * | 2014-09-25 | 2018-09-25 | 北京航星机器制造有限公司 | Titanium alloy framework stressed-skin construction part welder |
| CN105436653A (en) * | 2015-12-11 | 2016-03-30 | 中国科学院电子学研究所 | Special welding fixture for cavity of electronic vacuum device |
| CN105364257B (en) * | 2015-12-16 | 2018-06-26 | 中车大连机车研究所有限公司 | Aluminium-plate radiator brazing jig |
| CN105562862A (en) * | 2015-12-21 | 2016-05-11 | 天津大学 | Intermediate temperature self-reaction brazing method for aluminum honeycomb boards |
| CN206382720U (en) * | 2016-12-29 | 2017-08-08 | 武汉创恒世纪激光科技有限公司 | A kind of laser cutting machine tool sheet material clamps stationary fixture |
| CN108067701B (en) * | 2017-12-13 | 2020-07-17 | 北京华航无线电测量研究所 | Pressure-resistant airtight cold plate vacuum brazing universal tool |
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