CN117450416A - Hollow structure and preparation method thereof - Google Patents
Hollow structure and preparation method thereof Download PDFInfo
- Publication number
- CN117450416A CN117450416A CN202311394066.9A CN202311394066A CN117450416A CN 117450416 A CN117450416 A CN 117450416A CN 202311394066 A CN202311394066 A CN 202311394066A CN 117450416 A CN117450416 A CN 117450416A
- Authority
- CN
- China
- Prior art keywords
- hollow
- honeycomb structure
- cross
- prism
- hollow prism
- 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
Links
- 238000002360 preparation method Methods 0.000 title abstract description 11
- 238000003466 welding Methods 0.000 claims abstract description 54
- 229910000679 solder Inorganic materials 0.000 claims description 57
- 239000000956 alloy Substances 0.000 claims description 56
- 229910045601 alloy Inorganic materials 0.000 claims description 54
- 238000005096 rolling process Methods 0.000 claims description 42
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 35
- 239000011888 foil Substances 0.000 claims description 35
- 238000000034 method Methods 0.000 claims description 27
- 238000005520 cutting process Methods 0.000 claims description 16
- 238000005219 brazing Methods 0.000 claims description 15
- 238000002844 melting Methods 0.000 claims description 14
- 230000008018 melting Effects 0.000 claims description 12
- 238000010438 heat treatment Methods 0.000 claims description 11
- 239000011248 coating agent Substances 0.000 claims description 10
- 238000000576 coating method Methods 0.000 claims description 10
- 238000004519 manufacturing process Methods 0.000 claims description 10
- 239000012535 impurity Substances 0.000 claims description 8
- 239000000843 powder Substances 0.000 claims description 8
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 claims description 7
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 claims description 7
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 7
- 229910052709 silver Inorganic materials 0.000 claims description 7
- 239000004332 silver Substances 0.000 claims description 7
- 229910052726 zirconium Inorganic materials 0.000 claims description 7
- 238000001514 detection method Methods 0.000 claims description 6
- 238000003754 machining Methods 0.000 claims description 5
- 238000000465 moulding Methods 0.000 claims description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 4
- 239000000853 adhesive Substances 0.000 claims description 4
- 230000001070 adhesive effect Effects 0.000 claims description 4
- 229910052802 copper Inorganic materials 0.000 claims description 4
- 239000010949 copper Substances 0.000 claims description 4
- 238000009713 electroplating Methods 0.000 claims description 4
- 238000012216 screening Methods 0.000 claims description 3
- 230000000669 biting effect Effects 0.000 claims description 2
- 239000000463 material Substances 0.000 description 18
- 239000010936 titanium Substances 0.000 description 15
- 229910052719 titanium Inorganic materials 0.000 description 15
- 230000000694 effects Effects 0.000 description 12
- 238000009413 insulation Methods 0.000 description 11
- 239000013585 weight reducing agent Substances 0.000 description 10
- 230000008901 benefit Effects 0.000 description 9
- 230000009471 action Effects 0.000 description 6
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 230000007704 transition Effects 0.000 description 5
- 238000003723 Smelting Methods 0.000 description 4
- 238000000265 homogenisation Methods 0.000 description 4
- 238000007747 plating Methods 0.000 description 4
- 230000008439 repair process Effects 0.000 description 4
- 229910000746 Structural steel Inorganic materials 0.000 description 3
- 238000000889 atomisation Methods 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000007712 rapid solidification Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 239000000945 filler Substances 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000005304 joining Methods 0.000 description 2
- CNQCVBJFEGMYDW-UHFFFAOYSA-N lawrencium atom Chemical compound [Lr] CNQCVBJFEGMYDW-UHFFFAOYSA-N 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000005303 weighing Methods 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007373 indentation Methods 0.000 description 1
- 238000003698 laser cutting Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- ORQBXQOJMQIAOY-UHFFFAOYSA-N nobelium Chemical compound [No] ORQBXQOJMQIAOY-UHFFFAOYSA-N 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16S—CONSTRUCTIONAL ELEMENTS IN GENERAL; STRUCTURES BUILT-UP FROM SUCH ELEMENTS, IN GENERAL
- F16S1/00—Sheets, panels, or other members of similar proportions; Constructions comprising assemblies of such members
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B1/00—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations
- B21B1/08—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations for rolling structural sections, i.e. work of special cross-section, e.g. angle steel
-
- 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
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/10—Bulkheads
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16S—CONSTRUCTIONAL ELEMENTS IN GENERAL; STRUCTURES BUILT-UP FROM SUCH ELEMENTS, IN GENERAL
- F16S1/00—Sheets, panels, or other members of similar proportions; Constructions comprising assemblies of such members
- F16S1/10—Composite members, e.g. with ribs or flanges attached
Abstract
The invention discloses a hollow structure and a preparation method thereof, relating to the technical field of welding, wherein the hollow structure comprises: the hollow structure body at least comprises a first honeycomb structure unit and a second honeycomb structure unit, the first honeycomb structure unit comprises a plurality of first hollow prisms, each first hollow prism is spliced to form the first honeycomb structure unit, the second honeycomb structure unit comprises a plurality of second hollow prisms, each second hollow prism is spliced to form the second honeycomb structure unit, and the cross section area of the first hollow prism is larger than that of the second hollow prism, so that the first honeycomb structure unit and the second honeycomb structure unit are spliced to form a honeycomb structure which is in gradient arrangement. According to the hollow structure provided by the invention, the honeycomb structure which is arranged in a gradient manner is formed by arranging at least two different honeycomb structure units, so that the diversity and the versatility of the interior of the hollow structure are improved, and the comprehensive performance requirement of a bearing structural member is met.
Description
Technical Field
The invention relates to the technical field of welding construction, in particular to a hollow structure and a preparation method thereof.
Background
The hollow structure has the performance advantage of light weight, adopts a metal material with high temperature resistance and good plasticity, and adopts a reliable connecting method to prepare a hollow structural member which is used as a wallboard or an internal support piece of an aircraft, thereby meeting the comprehensive performance requirements of the aerospace field on light weight, high temperature resistance or heat insulation and other aspects. The hollow structure forms are diversified, such as corrugated sandwich structures, reinforced sandwich structures, plate-fin or plate-fin structures, honeycomb structures and the like, the hollow structures are all formed by taking a supporting framework as a middle part, taking a panel with a certain width as an upper skin and a lower skin, and the adopted preparation method comprises 3D printing, casting, gluing, welding and other processes, and the welding can be used for brazing, diffusion welding or superplastic forming diffusion connection and the like. The connecting joint formed by the brazing method belongs to a metallurgical bonding connecting joint, has higher high temperature resistance and strength, and the brazing technology is suitable for complex internal cavity structures.
In the prior art, the hollow structure is generally in a uniform unit form, so that the hollow characteristics inside the hollow structure are uniform and uniform in any dimension, which is not beneficial to the various requirements of product performance, and greatly limits the flexibility of structural design, such as a honeycomb structure with high rigidity but a weight reduction effect obviously lower than that of a honeycomb structure with a large-size core lattice; on the contrary, the honeycomb structure with the large-size core lattice has good heat insulation and weight reduction effects, but has obvious defects in the aspect of rigidity. With the further improvement of the comprehensive requirements of the aeronautical field on the structural members for the fuselage and the internal bearing, the requirements of diversification of the internal forms of the structure and the structural versatility are urgent.
In addition, the phase transition temperature of the pure titanium material is lower than that of the traditional titanium alloy, and when the conventional brazing filler metal is adopted, the phase transition of the pure titanium material is caused or the grain structure of the pure titanium foil strip material is seriously coarsened due to the higher brazing temperature, so that the problem of brittle fracture caused by insufficient strength of a welding structural member is solved.
Therefore, how to improve the diversity and versatility of the hollow structure and meet the comprehensive performance requirement of the bearing structural member becomes a technical problem to be solved by those skilled in the art.
Disclosure of Invention
Therefore, the present invention is directed to a hollow structure, which can improve the diversity and versatility of the hollow structure and meet the overall performance requirements of the bearing structural member.
Another object of the present invention is to provide a method for preparing the hollow structure described above.
In order to achieve the above purpose, the present invention provides the following technical solutions:
a hollow structure comprising:
the hollow structure body at least comprises a first honeycomb structure unit and a second honeycomb structure unit, wherein the first honeycomb structure unit comprises a plurality of first hollow prisms, each first hollow prism is spliced to form the first honeycomb structure unit, the second honeycomb structure unit comprises a plurality of second hollow prisms, each second hollow prism is spliced to form the second honeycomb structure unit, and the cross section area of the first hollow prism is larger than that of the second hollow prism, so that the first honeycomb structure unit and the second honeycomb structure unit are spliced to form a honeycomb structure which is arranged in a gradient mode.
Optionally, in the hollow structure, the cross-sectional shape of the first hollow prism and the cross-sectional shape of the second hollow prism are regular hexagons, the cross-section of the first hollow prism is a first cross-section, and the cross-section of the second hollow prism is a second cross-section; the distance between the opposite sides of the first cross section is D 1 The distance between the opposite sides of the second cross section is D 2 And D is 1 ＞D 2 。
Optionally, in the hollow structure, the first hollow prism and the second hollow prism are formed by splicing corrugated strips, and the corrugated strips are preset with low-melting-point solder alloy; the low-melting-point solder alloy comprises 30-45% of zirconium element, 10-15% of titanium element, 10-25% of tin element and the balance of silver element, wherein the phase line temperature of the low-melting-point solder alloy is lower than 820 ℃.
Optionally, in the hollow structure, the corrugated strip is formed by rolling a pure titanium foil strip through a rolling die, the height of the pure titanium foil strip is 3 mm-50 mm, and the thickness of the pure titanium foil strip is 0.02 mm-0.5 mm.
Optionally, in the hollow structure, the low-melting-point solder alloy is fixed on the surface of the corrugated strip by means of resistance spot welding; or alternatively, the first and second heat exchangers may be,
the low-melting-point solder alloy is in a powder shape and is uniformly distributed on the surface of the corrugated strip through a mixed adhesive; or alternatively, the first and second heat exchangers may be,
the low-melting-point solder alloy is arranged on the surface of the corrugated strip in an electroplating manner to form a solder coating, and the thickness of the solder coating is 20-25 mu m.
A method of producing a hollow structure as claimed in any one of the preceding claims, comprising the steps of:
splitting, namely machining a pure titanium foil belt into foil strips with preset widths through splitting, and removing impurities of the foil strips, wherein the impurities comprise burrs and oxides;
forming corrugated strips, namely rolling the foil strips through a rolling die to form corrugated strips for splicing the first hollow prism body and the second hollow prism body;
presetting a low-melting-point solder alloy, and fixing the low-melting-point solder alloy on the surface of the corrugated strip;
cutting the corrugated strip, namely cutting the corrugated strip through a cutting tool, and removing burrs at the cutting part of the corrugated strip to form a strip;
Splicing and assembling, namely splicing the strips through a positioning tool to form the first hollow prism and the second hollow prism respectively, and splicing the first hollow prism and the second hollow prism in sequence to form the hollow structure body in gradient arrangement;
and (3) brazing, namely placing the hollow structure body into a vacuum heat treatment furnace, and brazing and connecting the splicing position of the honeycomb structure through the melted low-melting-point solder alloy to form the hollow structure body.
Optionally, in the method for preparing a hollow structure, the method further includes the steps of:
welding detection, namely detecting the continuity of the welding position of the hollow structure body, screening out qualified hollow structure bodies, and ensuring that the size of the non-continuous welding part of the qualified hollow structure bodies is not more than 0.2mm.
Optionally, in the method for manufacturing a hollow structure, in the step of splicing and assembling, the corrugated strips form the first hollow prism and the second hollow prism respectively by means of resistance spot welding; the first hollow prism body and the second hollow prism body are connected through spot welding so as to form the honeycomb structure with weak connection.
Optionally, in the above method for manufacturing a hollow structure, in the step of forming the corrugated strip, the rolling die includes two rolling wheels, and the rolling wheels include a roller body and teeth disposed outside the roller body, so that the two rolling wheels roll the foil strip into the corrugated strip through a snapping action, the teeth include at least a first tooth and a second tooth, and the height of the first tooth is H 1 The height of the second tooth is H 2 The cross-sectional shape of the first hollow prism and the cross-sectional shape of the second hollow prism are regular hexagons, the cross-section of the first hollow prism is a first cross-section, the cross-section of the second hollow prism is a second cross-section, and the distance between opposite sides of the first cross-section is equal to the distance between the opposite sides of the second cross-sectionLeave as D 1 The distance between the opposite sides of the second cross section is D 2 And H is 1 ＝D 1 /2，H 2 ＝D 2 /2。
Optionally, in the method for manufacturing a hollow structure, in the step of splicing and assembling, the positioning tool is made of pure copper, and the positioning tool is provided with concave grooves which are identical to the teeth of the rolling die in shape and consistent in arrangement sequence.
According to the hollow structure provided by the invention, at least two different honeycomb structure units are arranged and are respectively a first honeycomb structure unit and a second honeycomb structure unit, the first honeycomb structure unit is formed by splicing a plurality of first hollow prisms, the second honeycomb structure unit is formed by splicing a plurality of second hollow prisms, and meanwhile, the cross section area of the first hollow prism is larger than that of the second hollow prism, so that the first honeycomb structure unit and the second honeycomb structure unit are spliced to form a honeycomb structure in a gradient arrangement. The first hollow prism can be a hollow prism with larger cross-sectional area, so that the first honeycomb structure unit has good weight reduction and heat insulation effects, can be used on the outer side of an aircraft to resist the high Wen Wenti caused by airflow impact, and the second hollow prism can be a hollow prism with smaller cross-sectional area, so that the second honeycomb structure unit has higher rigidity and strength, and can be used on the inner side of the aircraft to provide enough strength and resistance to structural deformation.
Compared with the prior art, the hollow structure provided by the invention has the advantages that the at least two different honeycomb structure units are arranged, so that the first honeycomb structure unit and the second honeycomb structure unit are spliced to form the honeycomb structure which is arranged in a gradient manner, and the diversity and the versatility of the inside of the hollow structure are improved by combining the advantages and the characteristics of the different honeycomb structure units, and the comprehensive performance requirement of a bearing structural member is met. Meanwhile, the hollow structure is flexible, and the first hollow prism and the second hollow prism can be flexibly combined and matched according to actual demands, so that the problem of single product performance caused by absolute homogenization of the internal units of the traditional hollow structure is solved.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are only embodiments of the present application, and other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a hollow structure according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a rolling die according to an embodiment of the present invention;
fig. 3 is a schematic working diagram of a rolling die according to an embodiment of the present invention;
FIG. 4 is a flowchart I of a method for fabricating a hollow structure according to an embodiment of the present invention;
fig. 5 is a second flowchart of a method for manufacturing a hollow structure according to an embodiment of the present invention.
Wherein 100 is a hollow structural body, 101 is a first honeycomb structural unit, 1011 is a first hollow prismatic body, 102 is a second honeycomb structural unit, 1021 is a second hollow prismatic body, 103 is a third honeycomb structural unit, and 1031 is a third hollow prismatic body;
200 is a roller, 201 is a roller body, 202 is a tooth, 2021 is a first tooth, 2022 is a second tooth, and 2023 is a third tooth.
Detailed Description
The core of the invention is to provide a hollow structure so as to improve the diversification and the versatility of the interior of the hollow structure and meet the comprehensive performance requirements of the bearing structural member.
Another core of the present invention is to provide a method for preparing the hollow structure.
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
As shown in fig. 1, an embodiment of the present invention discloses a hollow structure including a hollow structure body 100. It should be noted that, in the prior art, the hollow structure is generally in a uniform unit form, so that the hollow characteristics inside the hollow structure are uniform and uniform in any dimension, which is not beneficial to various requirements of product performance, and greatly limits the flexibility of structural design, such as a dense honeycomb structure with higher rigidity but a weight reduction effect obviously lower than that of a honeycomb structure with a large-size core lattice; on the contrary, the honeycomb structure with the large-size core lattice has good heat insulation and weight reduction effects, but has obvious defects in the aspect of rigidity. With the further improvement of the comprehensive requirements of the aeronautical field on the structural members for the fuselage and the internal bearing, the requirements of diversification of the internal forms of the structure and the structural versatility are urgent. In addition, the phase transition temperature of the pure titanium material is lower than that of the traditional titanium alloy, and when the conventional brazing filler metal is adopted, the phase transition of the pure titanium material is caused or the grain structure of the pure titanium foil strip material is seriously coarsened due to the higher brazing temperature, so that the problem of brittle fracture caused by insufficient strength of a welding structural member is solved. According to the hollow structure disclosed by the invention, at least two different honeycomb structure units are arranged, so that the first honeycomb structure unit 101 and the second honeycomb structure unit 102 are spliced to form the honeycomb structure which is arranged in a gradient manner, and the diversity and the versatility of the inside of the hollow structure are improved by combining the advantages and the characteristics of the different honeycomb structure units, and the comprehensive performance requirement of a bearing structural member is met. Meanwhile, the hollow structure is flexible, and the first hollow prism 1011 and the second hollow prism 1021 can be flexibly combined and matched according to actual requirements, so that the problem of single product performance caused by absolute homogenization of the internal units of the traditional hollow structure is solved. In addition, the low-melting-point solder alloy is adopted and is preset on the surface of the corrugated strip in a coating mode, and the lower interface of the low-melting-point solder alloy component does not form a brittle compound phase, so that the welding structure has higher bonding strength, and the problem of brittle fracture caused by insufficient strength of a welding structural member is solved.
As shown in fig. 1, the hollow structural body 100 includes at least two honeycomb structural units, which are defined as a first honeycomb structural unit 101 and a second honeycomb structural unit 102, respectively, for convenience of understanding, the first honeycomb structural unit 101 includes a plurality of first hollow prisms 1011, each of the first hollow prisms 1011 is spliced to form the first honeycomb structural unit 101, the second honeycomb structural unit 102 includes a plurality of second hollow prisms 1021, each of the second hollow prisms 1021 is spliced to form the second honeycomb structural unit 102, and the cross-sectional area of the first hollow prisms 1011 is larger than the cross-sectional area of the second hollow prisms 1021, so that the first honeycomb structural unit 101 and the second honeycomb structural unit 102 are spliced to form a honeycomb structure arranged in a gradient. The first hollow prism 1011 may be a hollow prism with a larger cross-sectional area, so that the first honeycomb structure 101 has good weight reduction and heat insulation effects, and may be used on the outside of an aircraft to resist the high Wen Wenti caused by airflow impact, and the second hollow prism 1021 may be a hollow prism with a smaller cross-sectional area, so that the second honeycomb structure 102 has higher rigidity and strength, and may be used on the inside of an aircraft to provide sufficient strength and resistance to structural deformation. By combining the advantages and characteristics of different honeycomb structural units, the diversity and the versatility of the hollow structure are improved, and the comprehensive performance requirement of the bearing structural member is met.
Further, as shown in fig. 1, in order to make the hollow structural body 100 have a better reflection effect on heat radiation, so that it has a better heat insulation performance, the cross-sectional shape of the first hollow prism 1011 and the cross-sectional shape of the second hollow prism 1021 are both regular hexagons, and the cross-section of the first hollow prism 1011 is a first cross-section, and the cross-section of the second hollow prism 1021 is a second cross-section. For ease of understanding, the distance between the opposite sides of the first cross section is defined as D 1 Distance between opposite sides of the second cross-section is definedFor D 2 And D is 1 ＞D 2 The cross section area of the first hollow prism 1011 is larger than that of the second hollow prism 1021, so that the first honeycomb structure unit 101 formed by the first hollow prism 1011 is a large-size honeycomb structure unit, the large-size honeycomb structure unit has good weight reduction and heat insulation effects, the second honeycomb structure unit 102 formed by the second hollow prism 1021 is a small-size honeycomb structure unit, the high rigidity and strength are achieved, the first honeycomb structure unit 101 and the second honeycomb structure unit 102 are spliced to form a gradient honeycomb structure, the hollow structure body 100 has good weight reduction and heat insulation effects, meanwhile, the high rigidity and strength are achieved, the diversification and the multifunction of the inside of the hollow structure are improved, and the comprehensive performance requirements of a bearing structural member are met.
Of course, the honeycomb structure units of the hollow structure body 100 are not limited to two but may be three, four, etc., as shown in fig. 1, in a specific embodiment, the honeycomb structure units of the hollow structure body 100 are four, and only three adjacent honeycomb structure units among them are explained and illustrated below, and for convenience of understanding, the three honeycomb structure units are defined as the first honeycomb structure unit 101, the second honeycomb structure unit 102, and the third honeycomb structure unit 103, respectively, and similar to the above embodiment, the third honeycomb structure unit 103 includes a plurality of third hollow prisms 1031, each of the third hollow prisms 1031 is spliced to form the third honeycomb structure unit 103, and the cross-sectional area of the second hollow prism 1021 is larger than that of the third hollow prism 1031, so that the first honeycomb structure unit 101, the second honeycomb structure unit 102, and the third honeycomb structure unit 103 are spliced to form a honeycomb structure in a gradient arrangement. Meanwhile, the cross-sectional shape of the third hollow prism 1031 may also employ a regular hexagon identical to the cross-sectional shape of the first hollow prism 1011 and the cross-sectional shape of the second hollow prism 1021, the cross-section of the third hollow prism 1031 being defined as a third cross-section, and correspondingly, the distance between opposite sides of the third cross-section being defined as D 3 And D is 1 ＞D 2 ＞D 3 So that the cross-sectional area of the first hollow prism 1011, the cross-sectional area of the second hollow prism 1021, and the cross-sectional area of the third hollow prism 1031 are sequentially reduced, thereby enabling the first honeycomb structural element 101 formed of the first hollow prism 1011 to have good weight reduction and heat insulation effects, the third honeycomb structural element 103 formed of the third hollow prism 1031 to have higher rigidity and strength, and the second honeycomb structural element 102 formed of the second hollow prism 1021 to function as an intermediate transition element, the phenomenon of stress concentration caused by the direct splicing of the first honeycomb structural element 101 with the third honeycomb structural element 103 can be avoided. When a hollow structure is used, the first honeycomb unit 101 may be disposed on the outside of the aircraft to resist the high temperature problems caused by airflow impingement, while the third honeycomb unit 103 is disposed on the inside of the aircraft to provide sufficient strength and resistance to structural deformation. Wherein D is 1 、D 2 And D 3 The values of (2) can be determined according to the mechanical property basic data of the honeycomb structures with different sizes, and the number of the honeycomb structure units and the cross-section shape of the hollow prism can be selected and flexibly combined according to the property requirements of products, such as weight, high temperature resistance, heat insulation and the like, so that the problem of single product property caused by absolute homogenization of the internal units of the traditional hollow structure is solved.
The hollow structure disclosed by the invention is characterized in that at least two different honeycomb structure units, namely a first honeycomb structure unit 101 and a second honeycomb structure unit 102, are arranged, the first honeycomb structure unit 101 is formed by splicing a plurality of first hollow prisms 1011, the second honeycomb structure unit 102 is formed by splicing a plurality of second hollow prisms 1021, and meanwhile, the cross-sectional area of the first hollow prisms 1011 is larger than that of the second hollow prisms 1021, so that the first honeycomb structure unit 101 and the second honeycomb structure unit 102 are spliced to form a honeycomb structure in a gradient arrangement. The first hollow prism 1011 may be a hollow prism with a larger cross-sectional area, so that the first honeycomb structure 101 has good weight reduction and heat insulation effects, and may be used on the outside of an aircraft to resist the high Wen Wenti caused by airflow impact, and the second hollow prism 1021 may be a hollow prism with a smaller cross-sectional area, so that the second honeycomb structure 102 has higher rigidity and strength, and may be used on the inside of an aircraft to provide sufficient strength and resistance to structural deformation.
Compared with the prior art, the hollow structure disclosed by the invention has the advantages that at least two different honeycomb structure units are arranged, so that the first honeycomb structure unit 101 and the second honeycomb structure unit 102 are spliced to form the honeycomb structure which is arranged in a gradient manner, and the diversity and the versatility of the inside of the hollow structure are improved by combining the advantages and the characteristics of the different honeycomb structure units, and the comprehensive performance requirement of a bearing structural member is met. Meanwhile, the hollow structure is flexible, and the first hollow prism 1011 and the second hollow prism 1021 can be flexibly combined and matched according to actual requirements, so that the problem of single product performance caused by absolute homogenization of the internal units of the traditional hollow structure is solved.
Further, in one embodiment, the first hollow prism 1011 and the second hollow prism 1021 are formed by splicing corrugated strips, and the corrugated strips are pre-arranged with a low melting point solder alloy. Specifically, the low-melting-point solder alloy includes zirconium element, titanium element, tin element, and silver element. The alloy is prepared into a foil material by a rapid solidification method or a powder alloy material by an atomization powder preparation method, the phase line temperature of the low-melting-point solder alloy is lower than 820 ℃, the low-melting-point solder alloy is adopted and is preset on the surface of a corrugated strip in a coating mode, and a brittle compound phase is not formed at the lower interface of the low-melting-point solder alloy component, so that the welding structure has higher bonding strength, and the problem of brittle cracking caused by insufficient strength of a welding structural member is solved. Meanwhile, compared with the traditional method of adopting a cementing method or manually removing positioning and assembling under the welding materials, the method has the advantages that the low-melting-point welding material alloy is preset on the surface of one side of the corrugated strip in a coating mode, so that the production efficiency of the hollow structure is improved, and the product quality of the hollow structure is guaranteed. Specifically, the corrugated strips are formed by rolling pure titanium foil strips through a rolling die, the height of the pure titanium foil strips is 3-50 mm, the thickness of the pure titanium foil strips is 0.02-0.5 mm, and the corrugated strips can be determined according to the mechanical property of the hollow structure and the size of the honeycomb structure units. It should be noted that, when the honeycomb structural units of the hollow structural body 100 are three, four or more, the hollow prisms are prepared in the same manner as the above embodiments, and are not described herein again.
Further, the low melting point solder alloy may be pre-set on the surface of the corrugated strip by fixing the low melting point solder alloy in the form of a foil strip having a thickness of 20 μm to 25 μm on the surface of one side of the corrugated strip by resistance spot welding, or the low melting point solder alloy in powder form may be uniformly arranged on the surface of one side of the corrugated strip by a mixed adhesive, or of course, the low melting point solder alloy may be arranged on the surface of one side of the corrugated strip by electroplating, thereby forming a solder plating layer, and the thickness of the solder plating layer is 20 μm to 25 μm. It should be noted that, by adopting the mode of presetting the low-melting-point solder alloy, the low-melting-point solder alloy is only required to be preset on the surface of one side of the corrugated strip in a coating mode, and is not required to be arranged on two sides of the corrugated strip, so that the consumption of the solder is saved, and the preparation cost of the hollow structure is reduced.
The embodiment of the invention also discloses a preparation method of the hollow structure, and the hollow structure is the hollow structure disclosed in the embodiment, so that the hollow structure has all the technical effects of the hollow structure and is not repeated herein. As shown in fig. 4, the preparation method of the hollow structure includes:
S100, slitting;
the pure titanium foil strip is divided into foil strips with preset width by a dividing strip machine, and impurities of the foil strips are removed, wherein the impurities comprise burrs and oxides. Specifically, the pure titanium foil strip is processed into a foil strip with a preset width according to the requirement of a hollow structure product by using a slitting machine or other processing methods, such as laser cutting and the like, wherein the preset width is the height of the hollow prism body. At the same time, impurities of the foil strip are removed, and burrs, oxides or other impurities are avoided at the edge of the foil strip.
S101, molding corrugated strips;
the foil strip is rolled at room temperature by a rolling die to obtain a corrugated strip for splicing the first hollow prism 1011 and the second hollow prism 1021. Specifically, when the cross-sectional shape of the first hollow prism 1011 and the cross-sectional shape of the second hollow prism 1021 are both regular hexagons, and the cross-section of the first hollow prism 1011 is a first cross-section, the cross-section of the second hollow prism 1021 is a second cross-section, the distance between the opposite sides of the first cross-section is D 1 The distance between the opposite sides of the second cross section is D 2 Rolling the foil strip by a rolling die at room temperature to form teeth with heights D respectively 1 2 and D 2 2, and the teeth are arranged according to the size sequence.
As shown in fig. 3, the rolling mold includes two rolling wheels 200, where the two rolling wheels 200 are a driving wheel and a driven wheel, and the driving wheel is driven by a motor to rotate, so that the driven wheel is driven by the driving wheel to rotate, so as to form a biting force between the two rolling wheels 200. As shown in fig. 2, the roller 200 includes a roller body 201 and teeth 202 provided at the outer side of the roller body 201 so that when a foil strip is introduced between the two roller wheels 200, the two roller wheels 200 roll the foil strip into a corrugated strip by a nip action, as shown in fig. 3. As shown in fig. 2, the teeth 202 at least include first teeth 2021 and second teeth 2022, wherein the number of the first teeth 2021 is plural, each first tooth 2021 is adjacently disposed on the outer side of the roller 201, the number of the second teeth 2022 is plural, each second tooth 2022 is adjacently disposed on the outer side of the roller 201, and the height of the first teeth 2021 is H 1 The height of the second teeth 2022 is H 2 And H is 1 ＝D 1 /2，H 2 ＝D 2 And/2, thereby forming teeth with heights D respectively 1 2 and D 2 Corrugated strips of/2. Meanwhile, for convenience of understanding, the diameter of the roller 201 is defined as D, and the number of the first teeth 2021 is defined as N 1 The number of second teeth 2022 is defined as N 2 And the circumference length of the roller 200 is required to satisfy pi D and N 1 ×D 1 +N 2 ×D 2 +N 3 ×D 3 + … … where N 1 N, the number of first teeth 2021 2 N, the number of second teeth 2022 3 The number of third teeth 2023, and so on, and N 1 、N 2 、N 3 Are integers and are all greater than 0. When the tooth size changes, the height of the adjacent smaller tooth is half of the height of the adjacent larger tooth, namely D 1 ＝2D 2 Similarly, teeth with different sizes can be designed on the rolling die, so that the foil strip is rolled into a corrugated strip with regular gradual change of structural units, simultaneously teeth 202 with the same size on the outer side of the roller body 201 are continuously arranged, the teeth 202 with different sizes are sequentially arranged from large to small, and the included angles between the teeth 202 are 118-120 degrees. When three honeycomb units of the hollow structure body 100 are provided, namely, the first honeycomb unit 101, the second honeycomb unit 102 and the third honeycomb unit 103, the teeth 202 outside the roll 201 include the first teeth 2021, the second teeth 2022 and the third teeth 2023, and the third teeth 2023 have a height H 3 ＝D 3 2, wherein D 3 Is the distance between the opposite sides of the third cross-section of the third hollow prism 1031, as shown in fig. 2.
S102, presetting a low-melting-point solder alloy;
a low melting point solder alloy is fixed to the surface of the corrugated strip. Specifically, the simple elements of the low-melting-point solder alloy are weighed and mixed, and a conventional smelting means is adopted to prepare an ingot. Wherein, the content of zirconium element is 30% -45%, the content of titanium element is 10% -15%, the content of tin element is 10% -25%, and the balance is silver element, and the alloy is prepared into foil strip material by a rapid solidification method or powder alloy material by an atomization powder preparation method. The low-melting-point solder alloy is adopted and is preset on the surface of the corrugated strip in a coating mode, and the brittle compound phase is not formed at the lower interface of the low-melting-point solder alloy component, so that the welding structure has higher bonding strength, and the problem of brittle fracture caused by insufficient strength of a welding structural member is solved. It should be noted that, the preset manner of the low melting point solder alloy has been explained and illustrated in the above embodiments, and is not described herein.
S103, cutting corrugated strips;
the corrugated strip is cut through a cutting tool, and burrs of the cutting part of the corrugated strip are removed. Tooth impressions with different sizes are periodically arranged on the corrugated strip, and the corrugated strip is cut according to the periodic arrangement sequence and the required length on the corrugated strip to form a strip. Specifically, according to the height of tooth indentation from large to small, the number of tooth forms contained on the rolling die is N in sequence 1 、N 2 And then the length of the cutting corrugated strip is equal to (N 1 +N 2 ) The cells correspond to integer multiples of the length. Similarly, when the number of tooth forms contained in the rolling die is N in order 1 、N 2 、N 3 And then the length of the cutting corrugated strip is equal to (N 1 +N 2 +N 3 ) Units correspond to integer multiples of the length, and so on.
S104, splicing and assembling;
the strips are spliced through the positioning tool to form a first hollow prism 1011 and a second hollow prism 1021 respectively, and the first hollow prism 1011 and the second hollow prism 1021 are spliced in sequence to form a honeycomb structure which is arranged in a gradient mode. Specifically, the positioning tool is made of pure copper with good conductivity, so that flatness and perpendicularity of the strip in the horizontal direction and the vertical direction are guaranteed, and mismatching of the hollow prism is avoided. The positioning tool is of a semi-hexagonal structure prepared from pure copper materials, and has concave grooves which are identical to the teeth 202 of the rolling die in shape and consistent in arrangement sequence. And (3) arranging the N strip and the (n+1) strip in a sequential gradient manner from large to small or from small to large by adopting a positioning tool according to adjacent honeycomb structure units, and repeating the steps once for each strip splice welding until the required first hollow prism 1011 and the second hollow prism 1021 are spliced. At this time, the first honeycomb structural unit 101 is formed by joining each of the first hollow prisms 1011 by spot welding, the second honeycomb structural unit 102 is formed by joining each of the second hollow prisms 1021 by spot welding, and the first honeycomb structural unit 101 and the second honeycomb structural unit 102 are formed into a weakly connected honeycomb structure by spot welding. When the honeycomb structural units of the hollow structural body 100 are three, that is, the first honeycomb structural unit 101, the second honeycomb structural unit 102 and the third honeycomb structural unit 103, the embodiments of the splice assembly are similar to the above-described embodiments, and the description thereof will be omitted herein. The spot welding mode may be resistance spot welding, laser spot welding or spot welding by a spot welder.
S105, brazing;
the honeycomb structure is placed in a vacuum heat treatment furnace, and the joint positions of the honeycomb structure are brazed by a molten low-melting-point solder alloy to form a hollow structure body 100. Specifically, a vacuum low-temperature heat treatment mode is adopted, the weakly connected honeycomb structure is placed into a vacuum heat treatment furnace, heat is preserved for 20-25 min in an environment of 15-30 ℃ above the phase line temperature of the low-melting-point solder alloy, so that the low-melting-point solder alloy is melted, and the splicing position of the honeycomb structure is subjected to braze welding connection through the capillary action of molten metal, so that the hollow structure body 100 with higher bonding strength is formed.
Further, as shown in fig. 5, the preparation method of the hollow structure further includes the steps of:
s106, welding detection;
detecting the continuity of the welding position of the hollow structural body 100, screening out a qualified hollow structural body 100, wherein the size of a discontinuous welding position of the qualified hollow structural body 100 is not more than 0.2mm, and when the prepared hollow structural body 100 does not meet the standard of the qualified hollow structural body 100, repair welding is required to improve the internal connection strength of the hollow structural body 100.
In one embodiment, the hollow structure is made of pure titanium TA1, and the hollow structure body 100 includes three dimensions of hollow prisms with regular hexagonal cross-sectional shapes according to product performance requirements. The opposite side distances of the regular hexagon are 24mm, 12mm and 6mm respectively, the heights of the hollow prisms are 20mm, namely the heights of the corrugated strips are 20mm, and the wall thicknesses of the hollow prisms are 0.05mm, namely the thicknesses of the corrugated strips are 0.05mm. In addition, the diameter D of the roll body 201 of the roll-in mold for molding corrugated strips corresponding to the hollow structure is 63mm, the teeth 202 are three kinds of teeth 202 with different sizes, the heights of the teeth 202 are 12mm, 6mm and 3mm respectively, the included angle between the teeth 202 is 118-120 degrees, and the number of the teeth 202 is 3, 6 and 4 respectively. Meanwhile, the above three teeth 202 are sequentially arranged in size, that is, the tooth 202 having a height of 12mm is adjacent to the tooth 202 having a height of 6mm, and the tooth 202 having a height of 6mm is adjacent to the tooth 202 having a height of 3 mm. The rolling die is made of structural steel and is formed by processing through a conventional machining method. In addition, according to the proportion of 30% of zirconium element, 15% of titanium element, 11% of tin element and the balance of silver element, weighing and mixing the elemental elements, preparing into cast ingots by adopting a conventional smelting means, and preparing into powdered low-melting-point solder alloy by adopting an atomization powder making method.
Further, the pure titanium TA1 foil strip is processed into a foil strip with the preset width of 20mm by using a slitting machine according to the requirement of a hollow structure product, and the edge of the foil strip is ensured to be free from burrs, oxides or other inclusion substances. And rolling the foil strip through the rolling die at room temperature to obtain TA1 corrugated strips with tooth impressions of which the heights are 12mm, 6mm and 3mm respectively and the three tooth impressions are arranged according to the sequence of the sizes. The powdered low-melting-point solder alloy is uniformly arranged on one side surface of the TA1 corrugated strip by mixing the adhesive. According to the specification requirement of the product, conventional scissors are used as tools to cut TA1 corrugated strips required by the product to form TA1 strips, and the cutting position is ensured not to have burrs. Each TA1 strip is spliced successively through laser spot welding, so that a weak-connection honeycomb structure which is arranged in a gradient mode is formed. And (3) placing the weakly connected honeycomb structure into a vacuum heat treatment furnace in a vacuum low-temperature heat treatment mode, preserving heat for 25min in an environment with the temperature of 15 ℃ above the phase line temperature of the low-melting-point solder alloy, melting the low-melting-point solder alloy, and brazing and connecting the spliced positions of the honeycomb structure through the capillary action of molten metal to form the hollow structure body 100 with higher bonding strength. The hollow structural body 100 is subjected to post-welding detection, the continuity of each welding position is visually inspected, and repair welding is required when the prepared hollow structural body 100 does not meet the standard of the qualified hollow structural body 100 so as to improve the internal connection strength of the hollow structural body 100. Compared with a hexagonal hollow structure with a simple core lattice size of 24mm, the hollow structure made of the pure titanium TA1 material has the advantages that the rigidity is improved by 30%, and the temperature resistance is improved by 40%.
In another embodiment, the hollow structure is made of pure titanium TA1, and the hollow structure body 100 includes three dimensions of hollow prisms with regular hexagonal cross-sectional shapes according to product performance requirements. The opposite side distances of the regular hexagons are 18mm, 9mm and 4.5mm respectively, the heights of the hollow prisms are 14mm, namely the heights of the corrugated strips are 14mm, and the wall thicknesses of the hollow prisms are 0.02mm, namely the thicknesses of the corrugated strips are 0.02mm. In addition, the diameter D of the roller 201 of the roller mold for molding corrugated strips corresponding to the hollow structure is 90mm, the teeth 202 are three teeth 202 with different sizes, the heights of the teeth 202 are 9mm, 4.5mm and 2.2 mm-2.3 mm respectively, the included angle between the teeth 202 is 118-120 degrees, and the number of the teeth 202 is 3, 6 and 4 respectively. Meanwhile, the above three teeth 202 are sequentially arranged according to the size, that is, the teeth 202 with the height of 9mm are adjacent to the teeth 202 with the height of 4.5mm, and the teeth 202 with the height of 4.5mm are adjacent to the teeth 202 with the height of 2.2mm to 2.3 mm. The rolling die is made of structural steel and is formed by processing through a conventional machining method. In addition, according to the proportion of 42% of zirconium element, 15% of titanium element, 20% of tin element and the balance of silver element, weighing and mixing the elemental elements, preparing into cast ingots by adopting a conventional smelting means, and preparing the foil strip material with the thickness of 20-25 mu m by adopting a rapid solidification method.
Further, the pure titanium TA1 foil strip is processed into a foil strip with the preset width of 14mm by using a slitting machine according to the requirement of a hollow structure product, and the edge of the foil strip is ensured to be free from burrs, oxides or other inclusion substances. And rolling the foil strip through the rolling die at room temperature to obtain TA1 corrugated strips with tooth impressions of which the heights are 9mm, 4.5mm and 2.2-2.3 mm respectively and the three tooth impressions are arranged according to the size sequence. A low melting point solder alloy in the form of a foil strip having a thickness of 20 μm to 25 μm was fixed on one side surface of the TA1 corrugated strip by resistance spot welding. According to the specification requirement of the product, conventional scissors are used as tools to cut TA1 corrugated strips required by the product to form TA1 strips, and the cutting position is ensured not to have burrs. Each TA1 strip is spliced successively through laser spot welding, so that a weak-connection honeycomb structure which is arranged in a gradient mode is formed. And (3) placing the weakly connected honeycomb structure into a vacuum heat treatment furnace in a vacuum low-temperature heat treatment mode, preserving heat for 20min in an environment of 16 ℃ above the phase line temperature of the low-melting-point solder alloy, melting the low-melting-point solder alloy, and brazing and connecting the spliced positions of the honeycomb structure through the capillary action of molten metal to form the hollow structure body 100 with higher bonding strength. The hollow structural body 100 is subjected to post-welding detection, the continuity of each welding position is visually inspected, and repair welding is required when the prepared hollow structural body 100 does not meet the standard of the qualified hollow structural body 100 so as to improve the internal connection strength of the hollow structural body 100. Compared with a hexagonal hollow structure with a simple core lattice size of 18mm, the hollow structure made of pure titanium TA1 material has 35% improved rigidity and 42% improved heat resistance.
In another embodiment, the hollow structure is made of pure titanium TA1-TA2, and the hollow structure body 100 comprises three dimensions of hollow prisms with regular hexagonal cross-sectional shapes according to product performance requirements. The opposite side distances of the regular hexagon are 40mm, 20mm and 10mm respectively, the heights of the hollow prisms are 16mm, namely the heights of the corrugated strips are 16mm, and the wall thicknesses of the hollow prisms are 0.05mm, namely the thicknesses of the corrugated strips are 0.05mm. In addition, the diameter D of the roll body 201 of the roll-in mold for molding corrugated strips corresponding to the hollow structure is 100mm, the teeth 202 are three kinds of teeth 202 with different sizes, the heights of the teeth 202 are 20mm, 10mm and 5mm respectively, the included angle between the teeth 202 is 118-120 degrees, and the number of the teeth 202 is 3, 6 and 4 respectively. Meanwhile, the above three teeth 202 are sequentially arranged in size, that is, the tooth 202 having a height of 20mm is adjacent to the tooth 202 having a height of 10mm, and the tooth 202 having a height of 10mm is adjacent to the tooth 202 having a height of 5mm. The rolling die is made of structural steel and is formed by processing through a conventional machining method. In addition, the elemental elements are weighed and mixed according to the proportion of 32% of zirconium element, 18% of titanium element, 13% of tin element and the balance of silver element, and cast ingots are prepared by adopting a conventional smelting means and used as master alloy of a coating material.
Further, the pure titanium TA1-TA2 foil strips are processed into foil strips with preset width of 16mm by using a slitting machine according to the requirements of hollow structure products, and the edges of the foil strips are ensured to be free from burrs, oxides or other inclusion substances. And rolling the foil strip through the rolling die at room temperature to obtain TA1-TA2 corrugated strips with tooth impressions of which the heights are 20mm, 10mm and 5mm respectively and the three tooth impressions are arranged according to the sequence of the sizes. The low-melting point solder alloy is placed on one side surface of the TA1-TA2 corrugated strip in a plating mode by adopting an electroplating method, and the thickness of the plating layer is 20-25 mu m. According to the specification of the product, conventional scissors are used as tools to cut TA1-TA2 corrugated strips required by the product to form TA1-TA2 strips, and the cutting position is ensured not to have burrs. And (3) gradually splicing the TA1-TA2 strips through laser spot welding, so that the weakly connected honeycomb structure with gradient arrangement is formed. And (3) placing the weakly connected honeycomb structure into a vacuum heat treatment furnace in a vacuum low-temperature heat treatment mode, preserving heat for 22min in an environment of 18 ℃ above the phase line temperature of the low-melting-point solder alloy, melting the low-melting-point solder alloy, and brazing and connecting the spliced positions of the honeycomb structure through the capillary action of molten metal to form the hollow structure body 100 with higher bonding strength. The hollow structural body 100 is subjected to post-welding detection, the continuity of each welding position is visually inspected, and repair welding is required when the prepared hollow structural body 100 does not meet the standard of the qualified hollow structural body 100 so as to improve the internal connection strength of the hollow structural body 100. Compared with a pure titanium TA1 material or a pure titanium TA2 material hexagonal hollow structure with a pure core lattice size of 40mm, the rigidity of the pure titanium TA1-TA2 material hollow structure is improved by 40%, and the temperature resistance is improved by 46%.
The terms first and second and the like in the description and in the claims and in the above-described figures are used for distinguishing between different objects and not necessarily for describing a sequential or chronological order. Furthermore, the terms "comprise" and "have," as well as any variations thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to the listed steps or elements but may include steps or elements not expressly listed.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A hollow structure, comprising:
the hollow structure body (100), the hollow structure body (100) at least comprises a first honeycomb structure unit (101) and a second honeycomb structure unit (102), the first honeycomb structure unit (101) comprises a plurality of first hollow prisms (1011), each first hollow prism (1011) is spliced to form the first honeycomb structure unit (101), the second honeycomb structure unit (102) comprises a plurality of second hollow prisms (1021), each second hollow prism (1021) is spliced to form the second honeycomb structure unit (102), and the cross-sectional area of the first hollow prisms (1011) is larger than the cross-sectional area of the second hollow prisms (1021), so that the first honeycomb structure unit (101) and the second honeycomb structure unit (102) are spliced to form a honeycomb structure which is in gradient arrangement.
2. The hollow structure of claim 1, wherein the firstThe cross-sectional shape of the hollow prism (1011) and the cross-sectional shape of the second hollow prism (1021) are regular hexagons, the cross-section of the first hollow prism (1011) is a first cross-section, and the cross-section of the second hollow prism (1021) is a second cross-section; the distance between the opposite sides of the first cross section is D 1 The distance between the opposite sides of the second cross section is D 2 And D is 1 ＞D 2 。
3. The hollow structure according to claim 1, wherein the first hollow prism (1011) and the second hollow prism (1021) are formed by splicing corrugated strips, and the corrugated strips are pre-provided with a low-melting solder alloy; the low-melting-point solder alloy comprises 30-45% of zirconium element, 10-15% of titanium element, 10-25% of tin element and the balance of silver element, wherein the phase line temperature of the low-melting-point solder alloy is lower than 820 ℃.
4. A hollow structure according to claim 3, wherein the corrugated strips are formed by rolling pure titanium foil strips with a height of 3mm to 50mm and a thickness of 0.02mm to 0.5mm by means of a rolling die.
5. A hollow structure according to claim 3, wherein the low melting point solder alloy is fixed to the surface of the corrugated strip by means of resistance spot welding; or alternatively, the first and second heat exchangers may be,
the low-melting-point solder alloy is in a powder shape and is uniformly distributed on the surface of the corrugated strip through a mixed adhesive; or alternatively, the first and second heat exchangers may be,
the low-melting-point solder alloy is arranged on the surface of the corrugated strip in an electroplating manner to form a solder coating, and the thickness of the solder coating is 20-25 mu m.
6. A method for producing a hollow structure according to any one of claims 1 to 5, comprising the steps of:
splitting, namely machining a pure titanium foil belt into foil strips with preset widths through splitting, and removing impurities of the foil strips, wherein the impurities comprise burrs and oxides;
forming corrugated strips, namely rolling the foil strips through a rolling die to form corrugated strips for splicing the first hollow prism (1011) and the second hollow prism (1021);
presetting a low-melting-point solder alloy, and fixing the low-melting-point solder alloy on the surface of the corrugated strip;
cutting the corrugated strip, namely cutting the corrugated strip through a cutting tool, and removing burrs at the cutting part of the corrugated strip to form a strip;
Splicing and assembling, namely splicing the strips through a positioning tool to form the first hollow prism (1011) and the second hollow prism (1021) respectively, and splicing the first hollow prism (1011) and the second hollow prism (1021) in sequence to form the honeycomb structure which is arranged in a gradient manner;
and (3) brazing, namely placing the honeycomb structure into a vacuum heat treatment furnace, and brazing and connecting the spliced position of the honeycomb structure through the melted low-melting-point solder alloy to form the hollow structure body (100).
7. The method of manufacturing a hollow structure according to claim 6, further comprising the steps of:
welding detection, namely detecting the continuity of the welding position of the hollow structure body (100), screening out qualified hollow structure bodies (100), and ensuring that the size of the discontinuous welding position of the qualified hollow structure bodies (100) is not more than 0.2mm.
8. The method of manufacturing a hollow structure according to claim 6, wherein in the step of splice-assembling, the corrugated strips are formed into the first hollow prism (1011) and the second hollow prism (1021) respectively by means of resistance spot welding; the first hollow prism (1011) and the second hollow prism (1021) are connected by spot welding to form the honeycomb structure with weak connection.
9. The method of manufacturing a hollow structure according to claim 6, wherein in the step of molding the corrugated strip, the rolling die includes two rolling wheels (200), and the rolling wheels (200) include a roller body (201) and teeth (202) provided outside the roller body (201), so that the two rolling wheels (200) roll the foil strip to form the corrugated strip by a biting action, the teeth (202) include at least a first tooth (2021) and a second tooth (2022), and the first tooth (2021) has a height H 1 The height of the second tooth (2022) is H 2 The cross-sectional shape of the first hollow prism (1011) and the cross-sectional shape of the second hollow prism (1021) are regular hexagons, the cross-section of the first hollow prism (1011) is a first cross-section, the cross-section of the second hollow prism (1021) is a second cross-section, and the distance between the opposite sides of the first cross-section is D 1 The distance between the opposite sides of the second cross section is D 2 And H is 1 ＝D 1 /2，H 2 ＝D 2 /2。
10. The method for manufacturing a hollow structure according to claim 9, wherein in the step of splicing and assembling, the positioning tool is made of pure copper, and the positioning tool is provided with concave grooves which are identical in shape and consistent in arrangement sequence with teeth (202) of the rolling die.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311394066.9A CN117450416A (en) | 2023-10-25 | 2023-10-25 | Hollow structure and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311394066.9A CN117450416A (en) | 2023-10-25 | 2023-10-25 | Hollow structure and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117450416A true CN117450416A (en) | 2024-01-26 |
Family
ID=89582908
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311394066.9A Pending CN117450416A (en) | 2023-10-25 | 2023-10-25 | Hollow structure and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117450416A (en) |
-
2023
- 2023-10-25 CN CN202311394066.9A patent/CN117450416A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4411380A (en) | Metal matrix composite structural panel construction | |
| US10363592B2 (en) | Method for preparing metal composite plate strip by rolling | |
| US3072225A (en) | Honeycomb sandwich structure | |
| CN104759625B (en) | A kind of material and the method that use laser 3D printing technique to prepare aluminum alloy junction component | |
| US3071853A (en) | Method and apparatus for making brazed honeycomb | |
| KR102279203B1 (en) | brazing sheet | |
| EP2598277B1 (en) | Method of connecting two aircraft fuselage segments by means of friction twist welding and a cover plate | |
| RU2456526C2 (en) | Side material and method for its manufacture, and manufacturing method of plated element for heat exchanger | |
| CN107009096B (en) | A method of manufacturing multi-layer hollow structure using closed cross-section pipe | |
| JPH1147859A (en) | Production of aluminum alloy panel | |
| CN117450416A (en) | Hollow structure and preparation method thereof | |
| CN100586641C (en) | Preparation method of rectangular pyramid metal lattice material | |
| WO2020179520A1 (en) | Method for producing sintered compact | |
| CN201489227U (en) | LCD panel framework | |
| CN109355511B (en) | Electrode material for TiNiFe alloy vacuum consumable melting and preparation thereof | |
| CN102059512B (en) | Manufacturing method of aluminium alloy workpiece with complex inner cavity body | |
| WO2010123402A1 (en) | Bimetallic billet and a method for manufacturing a clad metal sheet | |
| CN108480400B (en) | Heterogeneous metal spliced composite plate strip and preparation method thereof | |
| EP3452245B1 (en) | Method of forming objects by diffusion welding of foils | |
| JPS6362325B2 (en) | ||
| CN105234235B (en) | A kind of manufacturing process of titanium alloy cylindrical dot matrix lightweight structure part and application | |
| EP3023189B1 (en) | Brazing sheet for surface joining | |
| CN109676283A (en) | A kind of diamond saw blade active solder | |
| CN218926114U (en) | Prefabricated blank capable of avoiding cross flow of low-power tissue of bracket forging for airplane | |
| JPH08174111A (en) | Production of brazing panel with curved face |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |