CN111531334A - Three-layer lattice structural part and processing method thereof - Google Patents

Three-layer lattice structural part and processing method thereof Download PDF

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Publication number
CN111531334A
CN111531334A CN202010445066.7A CN202010445066A CN111531334A CN 111531334 A CN111531334 A CN 111531334A CN 202010445066 A CN202010445066 A CN 202010445066A CN 111531334 A CN111531334 A CN 111531334A
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CN
China
Prior art keywords
layer lattice
skin
layer
lattice structure
fixing
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.)
Pending
Application number
CN202010445066.7A
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Chinese (zh)
Inventor
雷鹍
谢秀民
李波
井超
吕昕宇
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Beijing Puhui Sanhang Technology Co ltd
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Beijing Puhui Sanhang Technology Co ltd
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Publication date
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Priority to CN202010445066.7A priority Critical patent/CN111531334A/en
Publication of CN111531334A publication Critical patent/CN111531334A/en
Pending legal-status Critical Current

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B21MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21DWORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/021Deforming sheet bodies
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23KSOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23KSOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K31/00Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups
    • B23K31/02Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups relating to soldering or welding
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23KSOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K9/00Arc welding or cutting
    • B23K9/16Arc welding or cutting making use of shielding gas
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces and the like
    • B64C1/06Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12Construction or attachment of skin panels
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64FGROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10Manufacturing or assembling aircraft, e.g. jigs therefor

Abstract

The invention discloses a three-layer lattice structural member and a processing method thereof, belonging to the field of space flight and aviation equipment. The invention achieves the effect of reducing the low quality on the premise of improving the structural strength, and is applied to aerospace equipment structural members.

Description

Three-layer lattice structural part and processing method thereof
Technical Field
The invention relates to a structural member, in particular to a three-layer lattice structural member and a processing method thereof.
Background
The invention provides a novel three-layer lattice structural component and a processing method thereof, wherein the structural strength of large complex titanium structural components on an aircraft, such as wing leading edges, slats, various force bearing wall plates, missile wings and other components, is high, and the weight of the components is light.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a three-layer lattice structural part and a processing method thereof.
In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a three-layer dot matrix structure, includes that two-layer skin, two skins that form top surface and bottom surface respectively are equipped with a plurality of support piece between, and support piece includes integrated into one piece fixed block and integrated into one piece in fixed block week side on the skin, and integrated into one piece is in a fixed plate between the adjacent fixed block that is located two skins respectively, and one side shaping of two skins is as an organic whole.
By adopting the technical scheme, the three-layer lattice structure formed by the support piece and the two skins is improved in structural strength, lighter in weight and suitable for the fields of aerospace engineering and the like with higher structural strength and quality requirements on structural members.
Preferably, the following steps: the number of the fixing plates on the same fixing block is four, the fixing blocks are in a square plate shape, and the fixing plates are integrally formed on four side walls of the fixing blocks respectively.
Preferably, the following steps: the fixed blocks on the two side plates are distributed in a staggered mode, and the fixed blocks on the same side plate are uniformly distributed in a dot matrix mode.
Preferably, the following steps: the two ends of each fixing plate are respectively and integrally formed with the two fixing blocks positioned on the two side plates.
Preferably, the following steps: the curb plate has the straight portion of fixed block, with another covering shaping thick straight portion as an organic whole and be located the transition portion that is the (shape) between thick straight portion and the straight portion, fixedly connected with reinforcing plate on the inside wall of transition portion, the other end of reinforcing plate is connected rather than adjacent fixed plate on another curb plate including the shaping.
Preferably, the following steps: and reinforcing plates are connected between the reinforcing blocks respectively positioned at the two sides of the transition part.
A method of manufacturing a three-layer lattice structure, comprising the three-layer lattice structure of any one of claims 1 to 6, further comprising the steps of:
firstly, preparing: preparing a process flow card and a titanium alloy plate;
secondly, blanking: blanking according to a blanking drawing of the three-layer lattice structural part;
thirdly, processing the blank: processing scribed lines according to a blank drawing of the three-layer lattice structural part;
fourthly, coating of a solder stop agent: coating the upper skin, the lower skin and the core layer with a solder stop agent according to the process specification requirements of the three-layer lattice structural member;
fifthly, sealing and welding: fixing the core layer on the upper skin by spot welding by using argon arc welding, sealing and welding the upper skin and the lower skin into a pocket, and welding an upper air inlet pipe;
sixthly, superplastic forming/diffusion bonding: firstly, diffusion connection is carried out, and then superplastic forming is carried out;
seventhly, processing the appearance: and processing the appearance of the part according to the processing drawing of the three-layer lattice structural part and performing surface treatment.
Preferably, the forming temperature of the superplastic forming in the sixth step is 910 +/-10 ℃, and the strain rate range is 5 × 10-4/s~5×10-3And/s, inflating the interior of the blank pocket, wherein argon is used as gas, and the maximum pressure is 1.2 MPa.
Preferably, the following steps: the forming temperature of diffusion bonding in the sixth step is 910 +/-10 ℃, and the unit pressure is as follows: 1.0MPa to 1.5MPa, vacuum degree: less than 10-2And (5) maintaining the pressure for 40-60 min under MPa.
In summary, compared with the prior art, the invention has the following beneficial effects:
1. the three-layer lattice structure formed by the support piece and the two skins improves the structural strength of the three-layer lattice structure, is lighter in weight, and is suitable for the fields of aerospace engineering and the like with higher structural strength and quality requirements on structural members;
2. the microstructure and the performance of the diffusion welding head are close to or the same as those of the base metal, the melting defect does not exist, the welding temperature is lower than that of the conventional welding process, the damage of the base metal is small, the stress is small, the high-precision characteristic is achieved, and the diffusion welding head is suitable for high-airtightness welding of the interior, multiple points and a large area.
3. The channel is filled with heat insulating materials or water cooling materials, so that heat protection and cooling effects can be achieved.
4. The space can store fuel, increases aircraft fuel reserves.
Drawings
FIG. 1 is an isometric view of a first embodiment;
fig. 2 is an enlarged view of a portion a of fig. 1 showing the structure of the support member.
FIG. 3 is a schematic view showing a mounting position of a core board in the second embodiment;
FIG. 4 is a schematic view showing the distribution of the positions of the vent holes of the cavity in the second embodiment;
FIG. 5 is a schematic view showing the shape of the air passages according to the second embodiment;
FIG. 6 is a schematic view illustrating the connection between the cavity vent and the gas path in the second embodiment;
FIG. 7 is a schematic view showing the position of an air inlet in the second embodiment;
FIG. 8 is a schematic view showing the positions of the scribed lines on the upper skin or the lower skin in the second embodiment;
FIG. 9 is a schematic view showing a position of applying the solder resist on the core board in the second embodiment.
Reference numerals: 1. covering a skin; 11. a straight portion; 12. a thick straight portion; 13. a transition section; 14. a reinforcing plate; 15. a reinforcing block; 2. a support member; 21. a fixing plate; 21. and (5) fixing blocks.
Detailed Description
The first embodiment is as follows: a three-layer lattice structure, see fig. 1 and 2, comprises two skins 1 with one side formed together, wherein each skin 1 comprises a straight part 11 in the shape of a straight plate, a thick straight part 12 formed into a whole with the other skin 1 and a transition part 13 which is positioned between the thick straight part 12 and the straight part 11 and is in the shape of a (a) plate. Be equipped with a plurality of support piece 2 between two skins 1, support piece 2 includes integrated into one piece fixed block 22 on skin 1 and a plurality of fixed plate 21 of integrated into one piece in fixed block 22 week side, integrated into one piece has same fixed plate 21 between the adjacent fixed block 22 that is located two skins 1 respectively, fixed plate 21 on the same fixed block 22 has four, fixed block 22 is square platelike, fixed plate 21 integrated into one piece respectively is on four lateral walls of fixed block 22, fixed block 22 staggered distribution on two skins 1, fixed block 22 on the same skin 1 is dot matrix form evenly distributed, two fixed block 22 integrated into one piece on two skins 1 respectively are equallyd divide at the both ends of each fixed plate 21. Fixedly connected with piece on the inside wall of transition portion 13, fixedly connected with one end and its fixedly connected's reinforcing plate 14 on reinforcing block 15, reinforcing plate 14's the other end and another covering 1 go up rather than adjacent fixed block 22 and be connected, lie in common being connected with reinforcing plate 14 between the reinforcing block 15 of transition portion 13 both sides respectively.
Example two: a processing method of a three-layer lattice structural member comprises the following steps:
firstly, preparing: the titanium alloy grades available in this example include TC4, TA15, TC31, Ti60, Ti65, and Ti2 AlNb.
Secondly, blanking: and (3) blanking according to a blanking drawing of the three-layer lattice structural part, wherein the blanking drawing of the multi-layer structural part is the shape drawing of the upper skin, the lower skin and the core plate shown in the figures 8 and 9.
Thirdly, processing the blank: and (3) processing an air inlet and a scribed line according to a blanking graph of the three-layer lattice structural part (see fig. 8 and 9), and performing surface treatment, wherein the surface treatment in the embodiment is pickling until the surface of the blank is free from oxides and corrosion.
Fourthly, coating of a solder stop agent: coating the two layers of skins and the core plate with the anti-welding agent according to the process specification requirements of the three layers of lattice structural members, wherein the process specification requirements of the three layers of lattice structural members comprise: the upper and lower skin solder stop coating parts are shaded parts, and the coating position of the core plate is positioned in the area between two adjacent square holes on the core plate, as shown in fig. 8 and 9.
Fifthly, sealing and welding: the core plate is aligned with the upper skin, the core plate is fixed on the upper skin through argon arc welding points, the scribed lines of the upper skin and the scribed lines of the lower skin are aligned, then sealing welding is carried out, and the air pipes are connected.
Sixthly, die filling: the blank surface and the mould surface are wiped clean by alcohol, and a layer of antioxidant is uniformly coated. The blank is then placed on the lower mold with the scribed areas on the upper skin, lower skin and core plate aligned with the cavities and the mold is closed, see fig. 3.
The forming die structure is shown in fig. 4-7, the upper die and the lower die of the die are both flat plate structures, the die cavity is symmetrical in surface, two parallel and intercommunicated air passages are arranged in the die below the die cavity, the air passages are intercommunicated and are communicated with the outside for exhausting, the air passage arrangement is shown in fig. 5-7, die cavity exhaust holes communicated with the air passages are arranged in the die cavity, the die cavity exhaust holes are distributed at intervals along the length direction of the air passages (see fig. 4, 6 and 7), and the air passages have the following functions.
(a) And providing a protective atmosphere when the temperature is raised.
(c) Diffusion pressure is provided during diffusion bonding.
(c) And discharging redundant gas during superplastic forming.
Seventhly, superplastic forming/diffusion connection; diffusion bonding: the forming temperature of the diffusion bonding was 910 ℃, unit pressure: 1.0MPa, vacuum degree: less than 10-2MPa, dwell time of 40min, molding temperature of superplastic forming of 910 ℃, strain rate of 5 × 10-4And s. Superplasticity generally means that the material exhibits exceptionally high elongation under tensile conditions without necking and breaking. When the elongation is more than 100%, it is referred to as superplasticity. The diffusion bonding is to press a plurality of solid phase materials (including intermediate layer materials) together, heat them in vacuum or protective atmosphere to a temperature below the melting point of the base material, and apply pressure to them to generate micro plastic deformation at the micro concave-convex uneven part of the bonding interfaceThe close contact is achieved, and then the firm metallurgical bonding is formed through heat preservation and mutual diffusion of atoms. Diffusion bonding is generally divided into 3 stages: the first stage is plastic deformation to bring the connection interfaces into contact. After the metals are in close contact, atoms begin to diffuse and exchange electrons to form metal bond connection, and the second stage is diffusion, interface migration and hole disappearance. The grain growth or recrystallization and the grain boundary migration of the connecting interface enable the metal bond connection to become firm metallurgical connection. The final stage is the disappearance of the interface and the pores. The volume diffusion is mainly in this stage, the speed is slow, and it usually takes several tens of minutes to several tens of hours to make the crystal grains grow through the interface, and the original interface disappears completely.
Eighthly, processing the appearance: and processing the appearance of the part according to the processing drawing of the three-layer lattice structural part and performing surface treatment.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may occur to those skilled in the art without departing from the principle of the invention, and are considered to be within the scope of the invention.

Claims (9)

1. A three-layer lattice structure characterized in that: including two-layer covering (1) that form top surface and bottom surface respectively, be equipped with a plurality of support piece (2) between two covering (1), support piece (2) include fixed block (22) and a plurality of fixed plate (21) of integrated into one piece in fixed block (22) week side on covering (1), integrated into one piece in a fixed plate (21) between adjacent fixed block (22) that are located respectively on two covering (1), one side shaping as an organic whole of two covering (1).
2. The triple-layer lattice structure of claim 1, wherein: the fixing plates (21) on the same fixing block (22) are provided with a plurality of fixing blocks (22) in a square plate shape, and the fixing plates (21) are respectively and integrally formed on four side walls of the fixing blocks (22).
3. The triple-layer lattice structure of claim 1, wherein: the fixing blocks (22) on the two skins (1) are distributed in a staggered mode, and the fixing blocks (22) on the same skin (1) are distributed uniformly in a dot matrix mode.
4. The triple-layer lattice structure of claim 1, wherein: the two ends of each fixing plate (21) are respectively integrally formed with the two fixing blocks (22) on the two skins (1).
5. The triple-layer lattice structure of claim 1, wherein: the skin (1) is including the shaping straight portion (11) that has fixed block (22), with another skin (1) shaping thick straight portion (12) as an organic whole and be located transition portion (13) that are the (shape between thick straight portion (12) and straight portion (11), fixedly connected with reinforcing plate (14) on the inside wall of transition portion (13), the other end and another skin (1) of reinforcing plate (14) are gone up rather than adjacent fixed block (22) and are connected.
6. The triple-layer lattice structure of claim 5, wherein: and reinforcing plates (14) are connected between the reinforcing blocks (15) respectively positioned at two sides of the transition part (13) in a common way.
7. A processing method of a three-layer lattice structural part is characterized by comprising the following steps: a three-layer lattice structure comprising a structure as claimed in any one of claims 1 to 6, further comprising the steps of:
preparing: preparing a process flow card and a titanium alloy plate;
blanking: blanking according to a blanking drawing of the three-layer lattice structural part;
processing a blank: processing scribed lines according to a blank drawing of the three-layer lattice structural part;
coating of a solder resist: coating the upper skin, the lower skin and the core layer with a solder stop agent according to the process specification requirements of the three-layer lattice structural member;
sealing and welding: fixing the core layer on the upper skin by spot welding by using argon arc welding, sealing and welding the upper skin and the lower skin into a pocket, and welding an upper air inlet pipe;
superplastic forming/diffusion bonding: firstly, diffusion connection is carried out, and then superplastic forming is carried out;
processing the appearance: and processing the appearance of the part according to the processing drawing of the three-layer lattice structural part and performing surface treatment.
8. The method of claim 7, wherein the superplastic forming in step six comprises forming at a temperature of 910 ± 10 ℃ and a strain rate in the range of 5 × 10-4/s~5×10-3And/s, inflating the interior of the blank pocket, wherein argon is used as gas, and the maximum pressure is 1.2 MPa.
9. A method of forming a three-layer lattice structure according to claim 7, wherein: the forming temperature of diffusion bonding in the sixth step is 910 +/-10 ℃, and the unit pressure is as follows: 1.0MPa to 1.5MPa, vacuum degree: less than 10-2And (5) maintaining the pressure for 40-60 min under MPa.
CN202010445066.7A 2020-05-23 2020-05-23 Three-layer lattice structural part and processing method thereof Pending CN111531334A (en)

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5269058A (en) * 1992-12-16 1993-12-14 General Electric Company Design and processing method for manufacturing hollow airfoils
US6591499B1 (en) * 1998-10-02 2003-07-15 Volvo Aero Corporation Method for manufacturing outlet nozzles for rocket engines
CN105346070A (en) * 2015-09-30 2016-02-24 北京大学 Method for preparing pyramid-shaped composite three-dimensional lattice sandwich structure
CN107234818A (en) * 2017-06-30 2017-10-10 哈尔滨工业大学 A kind of High Performance Thermoplastic Composites pyramid and X-type dot-matrix sandwich panel and preparation method thereof
CN107470436A (en) * 2017-08-07 2017-12-15 北京航星机器制造有限公司 A kind of alloy three-decker surface grooves control method
CN109203423A (en) * 2017-07-06 2019-01-15 中国航空制造技术研究院 A method of improving SPF/DB three-decker forming quality
CN110666457A (en) * 2019-10-09 2020-01-10 北京星航机电装备有限公司 Preparation method of titanium alloy thin-wall lightweight flap part

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5269058A (en) * 1992-12-16 1993-12-14 General Electric Company Design and processing method for manufacturing hollow airfoils
US6591499B1 (en) * 1998-10-02 2003-07-15 Volvo Aero Corporation Method for manufacturing outlet nozzles for rocket engines
CN105346070A (en) * 2015-09-30 2016-02-24 北京大学 Method for preparing pyramid-shaped composite three-dimensional lattice sandwich structure
CN107234818A (en) * 2017-06-30 2017-10-10 哈尔滨工业大学 A kind of High Performance Thermoplastic Composites pyramid and X-type dot-matrix sandwich panel and preparation method thereof
CN109203423A (en) * 2017-07-06 2019-01-15 中国航空制造技术研究院 A method of improving SPF/DB three-decker forming quality
CN107470436A (en) * 2017-08-07 2017-12-15 北京航星机器制造有限公司 A kind of alloy three-decker surface grooves control method
CN110666457A (en) * 2019-10-09 2020-01-10 北京星航机电装备有限公司 Preparation method of titanium alloy thin-wall lightweight flap part

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Application publication date: 20200814