CN113147107B - Honeycomb sandwich structure formed by C/C composite material and alloy and preparation method thereof - Google Patents

Honeycomb sandwich structure formed by C/C composite material and alloy and preparation method thereof Download PDF

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Publication number
CN113147107B
CN113147107B CN202110253127.4A CN202110253127A CN113147107B CN 113147107 B CN113147107 B CN 113147107B CN 202110253127 A CN202110253127 A CN 202110253127A CN 113147107 B CN113147107 B CN 113147107B
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composite material
honeycomb core
material panel
alloy
metal layer
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CN113147107A (en
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宋晓国
罗云
李子寒
李函霖
周文龙
胡胜鹏
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Harbin Institute of Technology Weihai
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Harbin Institute of Technology Weihai
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
    • B23K1/0014—Brazing of honeycomb sandwich structures
    • 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
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/005—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile
    • B32B9/007—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile comprising carbon, e.g. graphite, composite carbon
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B9/041—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/306—Resistant to heat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/70—Other properties
    • B32B2307/714—Inert, i.e. inert to chemical degradation, corrosion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/70—Other properties
    • B32B2307/718—Weight, e.g. weight per square meter

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Ceramic Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Laminated Bodies (AREA)

Abstract

The invention discloses a honeycomb sandwich structure formed by C/C composite materials and alloy and a preparation method thereof, wherein the honeycomb sandwich structure comprises a first C/C composite material panel, a second C/C composite material panel and an alloy honeycomb core, the alloy honeycomb core is connected between the first C/C composite material panel and the second C/C composite material panel, a first brazing filler metal layer is connected between the first C/C composite material panel and the alloy honeycomb core, and a second brazing filler metal layer is connected between the second C/C composite material panel and the alloy honeycomb core. The honeycomb sandwich structure prepared by the method is made of panels and honeycomb cores made of different materials, has the excellent characteristics of light weight, high strength, high temperature resistance, corrosion resistance and the like, can be used for non-main bearing parts of ships and high-speed trains and rudder wings of ultrahigh-speed aircrafts, and greatly widens the engineering application of the honeycomb sandwich structure.

Description

Honeycomb sandwich structure formed by C/C composite material and alloy and preparation method thereof
Technical Field
The invention relates to the technical field of connection forming of thin-wall honeycomb sandwich structures, in particular to a honeycomb sandwich structure formed by light-weight high-strength C/C composite materials and alloys and a preparation method thereof.
Background
The honeycomb sandwich structure has higher specific strength, specific rigidity, good impact performance, special performances of sound absorption, energy absorption, heat dissipation, electromagnetic shielding and the like, and is widely applied to industries of automobiles, aerospace and the like. Currently, honeycomb sandwich structures are composed of honeycomb core materials and face sheets, wherein the materials of the honeycomb core materials and the face sheets are the same, such as Nomex honeycomb, aluminum honeycomb, titanium honeycomb, superalloy honeycomb, and the like, but the same honeycomb core materials and face sheets also greatly limit the applications thereof, such as aluminum honeycomb and titanium honeycomb cannot be used in high temperature environments above 600 ℃.
Disclosure of Invention
Therefore, the invention provides a honeycomb sandwich structure formed by C/C composite materials and alloys and a preparation method thereof, which aim to solve the problems.
The invention provides a honeycomb sandwich structure formed by C/C composite materials and alloy, which comprises a first C/C composite material panel, a second C/C composite material panel and an alloy honeycomb core, wherein the alloy honeycomb core is connected between the first C/C composite material panel and the second C/C composite material panel, a first brazing filler metal layer is connected between the first C/C composite material panel and the alloy honeycomb core, and a second brazing filler metal layer is connected between the second C/C composite material panel and the alloy honeycomb core.
In some embodiments, the first solder layer and the second solder layer are both comprised of a Ti-containing active solder and a pure Cu solder.
In some embodiments, the materials of the first and second braze layers each include AgCuTi, tizronicu, tiNiNb, and Cu.
In some embodiments, the first and second solder layers each have a thickness of 100 μm to 150 μm.
In some embodiments, the alloy honeycomb core is one of a nickel-based alloy honeycomb core, an aluminum alloy honeycomb core, and a titanium alloy honeycomb core.
In some embodiments, the nickel-based alloy forming the nickel-based alloy honeycomb core is one of GH3536, GH5188, GH99, the titanium alloy forming the titanium alloy honeycomb core is one of TC1, TC4, TA15, TA60, and the aluminum alloy forming the aluminum alloy honeycomb core is one of AA3003 and AA 5052.
The invention also provides a preparation method of the honeycomb sandwich structure formed by the C/C composite material and the alloy, which comprises the following steps:
obtaining a first C/C composite material panel, a second C/C composite material panel and an alloy honeycomb core through wire cut electrical discharge machining;
stacking the first C/C composite panel, the second C/C composite panel and the alloy honeycomb core, arranging a first brazing filler metal layer between the first C/C composite panel and the alloy honeycomb core, and arranging a second brazing filler metal layer between the second C/C composite panel and the alloy honeycomb core;
and brazing the first C/C composite material panel, the first brazing filler metal layer, the alloy honeycomb core, the second brazing filler metal layer and the second C/C composite material panel to ensure that two opposite side surfaces of the first brazing filler metal layer are respectively and fixedly connected with one side surface of the alloy honeycomb core and the first C/C composite material panel and two opposite side surfaces of the second brazing filler metal layer are respectively and fixedly connected with the other side surface of the alloy honeycomb core and the second C/C composite material panel, and obtaining a honeycomb sandwich structure formed by C/C composite materials and alloys.
In some embodiments, after the step of obtaining a first C/C composite panel, a second C/C composite panel, and an alloy honeycomb core by wire electrical discharge machining, the method further comprises:
and grinding and polishing the surfaces to be welded of the first C/C composite material panel, the alloy honeycomb core and the second C/C composite material panel by using sand paper, and then placing the surfaces in an acetone solution for ultrasonic cleaning.
In some embodiments, after the step of disposing the first C/C composite face sheet, the second C/C composite face sheet, and the alloy honeycomb core in a stack, and disposing a first braze layer between the first C/C composite face sheet and the alloy honeycomb core, and disposing a second braze layer between the second C/C composite face sheet and the alloy honeycomb core, the method further comprises:
respectively aligning the first C/C composite panel and the second C/C composite panel
Applying opposite pressure of 0.01-0.03MPa.
In some embodiments, the step of brazing specifically comprises:
subjecting the first C/C composite panel, the first solder layer, and the second C/C composite panel to pressure application,
And placing the alloy honeycomb core, the second brazing filler metal layer and the second C/C composite material panel in a vacuum furnace for heating, raising the temperature to the brazing temperature at a heating rate of 10 ℃/min after the vacuum degree is lower than 3.0 x 10 < -3 > Pa, preserving the heat for 5-20min, then reducing the temperature to 500 ℃ at a cooling rate of 5 ℃/min, cooling to the room temperature along with the vacuum furnace, taking out the sample, and completing brazing.
The honeycomb sandwich structure prepared by the method is made of panels and honeycomb cores made of different materials, has the excellent characteristics of light weight, high strength, high temperature resistance, corrosion resistance and the like, can be used for non-main bearing parts of ships and high-speed trains and rudder wings of ultrahigh-speed aircrafts, and greatly widens the engineering application of the honeycomb sandwich structure.
Drawings
FIG. 1 is an exploded view of a honeycomb sandwich structure formed of C/C composite materials and alloys according to the present invention.
FIG. 2 is a front view of the honeycomb sandwich structure formed of the C/C composite and alloy shown in FIG. 1.
Fig. 3 is a flow chart of a method for preparing a honeycomb sandwich structure formed by the C/C composite material and the alloy provided by the invention.
Detailed Description
Reference will now be made in detail to embodiments of the present application, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative and are only for the purpose of explaining the present application and are not to be construed as limiting the present application.
In the description of the present application, it is to be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the application and for simplicity in description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and thus should not be considered limiting. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as the case may be.
In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact of the first and second features, or may comprise contact of the first and second features not directly but through another feature in between. Also, the first feature "on," "above" and "over" the second feature may include the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly above and obliquely above the second feature, or simply meaning that the first feature is at a lesser level than the second feature.
The following disclosure provides many different embodiments or examples for implementing different features of the application. In order to simplify the disclosure of the present application, specific example components and arrangements are described below. Of course, they are merely examples and are not intended to limit the present application. Moreover, the present application may repeat reference numerals and/or letters in the various examples, such repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. In addition, examples of various specific processes and materials are provided herein, but one of ordinary skill in the art may recognize applications of other processes and/or use of other materials.
Referring to fig. 1 and fig. 2, an embodiment of the present invention provides a honeycomb sandwich structure 100 formed by C/C composite materials and alloys, including a first C/C composite material panel 10, a second C/C composite material panel 20, an alloy honeycomb core 30, a first solder layer 40, and a second solder layer 50.
Wherein the alloy honeycomb core 30 is connected between the first C/C composite panel 10 and the second C/C composite panel 20, a first brazing filler metal layer 40 is connected between the first C/C composite panel 10 and the alloy honeycomb core 30, and a second brazing filler metal layer 50 is connected between the second C/C composite panel 20 and the alloy honeycomb core 30.
In some embodiments, the first solder layer 40 and the second solder layer 50 are both comprised of Ti-containing active solder and pure Cu solder.
In some embodiments, the materials of the first and second braze layers 40, 50 each include Cu and one of AgCuTi, tizronicu, tiNiNb. Wherein the AgCuTi and the TiZrNiCu are foils, and the thicknesses of the AgCuTi and the TiZrNiCu are both 100 mu m. The TiNiNb brazing filler metal consists of a thick Ti foil, a thick Ni foil and a thick Nb foil. The thickness of the Cu layer was 5 μm.
In some embodiments, the first and second solder layers 40 and 50 each have a thickness of 100 μm to 150 μm.
In some embodiments, the alloy honeycomb core 30 is one of a nickel-based alloy honeycomb core 30, an aluminum alloy honeycomb core 30, and a titanium alloy honeycomb core 30.
In some embodiments, the nickel-based alloy forming the nickel-based alloy honeycomb core 30 is one of GH3536, GH5188, GH99, the titanium alloy forming the titanium alloy honeycomb core 30 is one of TC1, TC4, TA15, TA60, and the aluminum alloy forming the aluminum alloy honeycomb core 30 is one of AA3003 and AA 5052.
It should be noted that GH3536, GH5188 and GH99 are respectively the type of nickel-based alloy, TC1, TC4, TA15 and TA60 are respectively the type of titanium alloy, and AA3003 and AA5052 are the type of aluminum alloy.
Referring to fig. 3, an embodiment of the present invention further provides a method for preparing a honeycomb sandwich structure 100 formed by C/C composite materials and alloys, including the following steps:
step S10: the first C/C composite material panel 10, the second C/C composite material panel 20 and the alloy honeycomb core 30 are obtained through wire cut electrical discharge machining.
Step S20: and (3) grinding and polishing the surfaces to be welded of the first C/C composite material panel 10, the alloy honeycomb core 30 and the second C/C composite material panel 20 by using sand paper, and then placing the panels in an acetone solution for ultrasonic cleaning.
Step S30: the first C/C composite panel 10, the second C/C composite panel 20, and the alloy honeycomb core 30 are stacked, and a first brazing filler metal layer 40 is provided between the first C/C composite panel 10 and the alloy honeycomb core 30, and a second brazing filler metal layer 50 is provided between the second C/C composite panel 20 and the alloy honeycomb core 30.
In some embodiments, the method further comprises:
respectively facing the first C/C composite material panel 10 and the second C/C composite material face
The plate 20 applies a pressure in the opposite direction, said pressure being between 0.01 and 0.03MPa.
Step S40: and brazing the first C/C composite material panel 10, the first brazing filler metal layer 40, the alloy honeycomb core 30, the second brazing filler metal layer 50 and the second C/C composite material panel 20, so that two opposite side surfaces of the first brazing filler metal layer 40 are respectively and fixedly connected with one side surface of the alloy honeycomb core 30 and two opposite side surfaces of the first C/C composite material panel 10 and the second brazing filler metal layer 50 are respectively and fixedly connected with the other side surface of the alloy honeycomb core 30 and the second C/C composite material panel 20, and a honeycomb sandwich structure 100 formed by C/C composite materials and alloys is obtained.
Wherein the brazing step specifically comprises:
and (3) placing the first C/C composite material panel 10, the first brazing filler metal layer 40, the alloy honeycomb core 30, the second brazing filler metal layer 50 and the second C/C composite material panel 20 after pressure is applied in a vacuum furnace for heating, raising the temperature to the brazing temperature at a heating rate of 10 ℃/min when the vacuum degree is lower than 3.0 multiplied by 10 < -3 > Pa, preserving the temperature for 5-20min, then reducing the temperature to 500 ℃ at a cooling rate of 5 ℃/min, cooling the temperature to the room temperature along with the vacuum furnace, taking out a sample, and completing brazing.
The honeycomb sandwich structure prepared by the method is made of panels and honeycomb cores made of different materials, has the excellent characteristics of light weight, high strength, high temperature resistance, corrosion resistance and the like, can be used for non-main bearing parts of ships and high-speed trains and rudder wings of ultrahigh-speed aircrafts, and greatly widens the engineering application of the honeycomb sandwich structure.
The technical solution of the present invention is not limited to the following embodiments, but includes any combination of the embodiments.
Example 1
A method for manufacturing a honeycomb sandwich structure 100 formed by C/C composite materials and alloys, wherein the alloy forming an alloy honeycomb core 30 is AA3003 aluminum alloy, the size of the alloy honeycomb core is 40mm multiplied by 30mm multiplied by 12mm, the size of the core grid is 1.6mm, and the thickness of the material is 0.05mm. The dimensions of the first C/C composite panel 10 and the second C/C composite panel 20 are 42mm x 32mm x 1mm. The material of the first and second solder layers 40, 50 is AgCuTi, and the dimensions of the first and second solder layers 40, 50 are 42mm × 32mm × 0.1mm.
And (3) grinding the surfaces to be welded of the first C/C composite material panel 10, the second C/C composite material panel 20, the first brazing filler metal layer 40 and the second brazing filler metal layer 50 by using 2000-mesh waterproof abrasive paper, polishing by using 0.5M diamond grinding fluid, finally cleaning in acetone by using ultrasonic waves for 20min, and drying for later use.
Then, a first brazing filler metal layer 40 is placed on the surface to be welded of the first C/C composite material panel 10, a second brazing filler metal layer 50 is placed on the surface to be welded of the second C/C composite material panel 20, then the placed first brazing filler metal layer 40 and the first C/C composite material panel 10, and the placed second brazing filler metal layer 50 and the second C/C composite material panel 20 are placed into a vacuum brazing furnace together, when the vacuum degree is lower than 3.0 x 10 < -3 > Pa, the temperature is increased to 900 ℃ at the temperature increasing speed of 10 ℃/min, the temperature is kept for 20min, then the temperature is decreased to 500 ℃ at the temperature decreasing speed of 5 ℃/min, and after the temperature is cooled to room temperature along with the furnace, the sample is taken out, and metallization is completed.
Respectively electroplating 5-micrometer-thick Cu layers on two opposite surfaces to be welded of the alloy honeycomb core 30, then sequentially assembling a first metalized brazing filler metal layer 40 and a first C/C composite material panel 10, the alloy honeycomb core 30, a second metalized brazing filler metal layer 50 and a second C/C composite material panel 20, applying 0.1MPa pressure, putting the assembled parts into a vacuum brazing furnace, raising the temperature to 580 ℃ at a heating rate of 10 ℃/min after the vacuum degree is lower than 3.0 x 10 < -3 > Pa, preserving the temperature for 15min, lowering the temperature to 500 ℃ at a cooling rate of 5 ℃/min, cooling the assembled parts to room temperature along with the furnace, taking out a sample, and completing brazing.
The test results show that the test realizes the effective connection of the first C/C composite material panel 10, the second C/C composite material panel 20 and the alloy honeycomb core 30. The interface structure is a typical Al-Cu eutectic structure, the maximum tensile strength of the honeycomb sandwich structure is 18MPa, and the compressive strength of the honeycomb sandwich structure is 6MPa.
Example 2
A method for manufacturing a honeycomb sandwich structure 100 formed by C/C composite materials and alloys, wherein the alloy forming an alloy honeycomb core 30 is GH3536 nickel alloy, the size of the alloy honeycomb core is 40mm multiplied by 30mm multiplied by 12mm, the size of the core grid is 1.6mm, and the thickness of the material is 0.05mm. The dimensions of the first C/C composite panel 10 and the second C/C composite panel 20 are 42mm x 32mm x 1mm. The material of the first and second solder layers 40, 50 is AgCuTi, and the dimensions of the first and second solder layers 40, 50 are 42mm × 32mm × 0.1mm.
And (3) grinding the surfaces to be welded of the first C/C composite panel 10, the second C/C composite panel 20, the first brazing filler metal layer 40 and the second brazing filler metal layer 50 by using 2000-mesh waterproof abrasive paper, polishing by using 0.5M diamond grinding fluid, finally cleaning in acetone for 20min by using ultrasonic waves, and drying for later use.
Then, a first brazing filler metal layer 40 is placed on the surface to be welded of the first C/C composite material panel 10, a second brazing filler metal layer 50 is placed on the surface to be welded of the second C/C composite material panel 20, then the placed first brazing filler metal layer 40 and the first C/C composite material panel 10, and the placed second brazing filler metal layer 50 and the second C/C composite material panel 20 are placed into a vacuum brazing furnace together, when the vacuum degree is lower than 3.0 x 10 < -3 > Pa, the temperature is increased to 900 ℃ at the temperature increasing speed of 10 ℃/min, the temperature is kept for 20min, then the temperature is decreased to 500 ℃ at the temperature decreasing speed of 5 ℃/min, and after the temperature is cooled to room temperature along with the furnace, the sample is taken out, and metallization is completed.
Respectively electroplating 5-micrometer-thick Cu layers on two opposite surfaces to be welded of the alloy honeycomb core 30, then sequentially assembling a first metalized brazing filler metal layer 40 and a first C/C composite material panel 10, the alloy honeycomb core 30, a second metalized brazing filler metal layer 50 and a second C/C composite material panel 20, applying 0.1MPa pressure, putting the materials into a vacuum brazing furnace, raising the temperature to 900 ℃ at a heating rate of 10 ℃/min when the vacuum degree is lower than 3.0 x 10 < -3 > Pa, keeping the temperature for 15min, lowering the temperature to 500 ℃ at a cooling rate of 5 ℃/min, cooling the materials to room temperature along with the furnace, taking out a sample, and completing brazing.
The test results show that the test realizes the effective connection of the first C/C composite material panel 10, the second C/C composite material panel 20 and the alloy honeycomb core 30. The interface structure is a typical Ag-Cu eutectic structure, the maximum tensile strength of the honeycomb sandwich structure is 22MPa, and the compressive strength of the honeycomb sandwich structure is 33MPa.
Example 3
A method for manufacturing a honeycomb sandwich structure 100 formed by C/C composite materials and alloys, wherein the alloy forming an alloy honeycomb core 30 is TC4 titanium alloy, the size is 40mm multiplied by 30mm multiplied by 12mm, the size of the core grid is 1.6mm, and the thickness of the material is 0.05mm. The dimensions of the first C/C composite panel 10 and the second C/C composite panel 20 are 42mm x 32mm x 1mm. The material of the first and second braze layers 40, 50 is tizrncu, the dimensions of the first and second braze layers 40, 50 are 42mm x 32mm x 0.1mm, where tizrncu is the nominal chemical composition (mass fraction) of Ti-18Zr-15Cu-10Ni.
And (3) grinding the surfaces to be welded of the first C/C composite panel 10, the second C/C composite panel 20, the first brazing filler metal layer 40 and the second brazing filler metal layer 50 by using 2000-mesh waterproof abrasive paper, polishing by using 0.5M diamond grinding fluid, finally cleaning in acetone for 20min by using ultrasonic waves, and drying for later use.
And then placing a first brazing filler metal layer 40 on a to-be-welded surface of a first C/C composite material panel 10, placing a second brazing filler metal layer 50 on a to-be-welded surface of a second C/C composite material panel 20, then placing the placed first brazing filler metal layer 40, the first C/C composite material panel 10, the second brazing filler metal layer 50 and the second C/C composite material panel 20 into a vacuum brazing furnace, raising the temperature to 900 ℃ at a heating rate of 10 ℃/min when the vacuum degree is lower than 3.0 x 10 < -3 > Pa, preserving the temperature for 20min, then reducing the temperature to 500 ℃ at a cooling rate of 5 ℃/min, cooling the temperature to room temperature along with the furnace, taking out the sample, and completing metallization.
Respectively electroplating 5-micrometer-thick Cu layers on two opposite surfaces to be welded of the alloy honeycomb core 30, then sequentially assembling a first metalized brazing filler metal layer 40 and a first C/C composite material panel 10, the alloy honeycomb core 30, a second metalized brazing filler metal layer 50 and a second C/C composite material panel 20, applying 0.1MPa pressure, putting the assembled parts into a vacuum brazing furnace, raising the temperature to 930 ℃ at a heating rate of 10 ℃/min after the vacuum degree is lower than 3.0 x 10 < -3 > Pa, preserving the heat for 15min, reducing the temperature to 500 ℃ at a cooling rate of 5 ℃/min, cooling the obtained product to room temperature along with the furnace, taking out a sample, and completing brazing.
The test results show that the test realizes the effective connection of the first C/C composite material panel 10, the second C/C composite material panel 20 and the alloy honeycomb core 30. The interface structure is a typical Ti-based solid solution and a fine widmannstatten structure, the maximum tensile strength of the honeycomb sandwich structure is 28MPa, and the compressive strength of the honeycomb sandwich structure is 15MPa.
Example 4
A method for manufacturing a honeycomb sandwich structure 100 formed by C/C composite materials and alloys, wherein the alloy forming an alloy honeycomb core 30 is GH5188 nickel alloy, the size is 40mm multiplied by 30mm multiplied by 12mm, the size of the core grid is 1.6mm, and the thickness of the material is 0.05mm. The dimensions of the first C/C composite panel 10 and the second C/C composite panel 20 are 42mm x 32mm x 1mm. The first brazing filler metal layer 40 and the second brazing filler metal layer 50 are made of TiNiNb, wherein the TiNiNb component is Ti-40Ni-20Nb (atomic fraction%), and the sizes of the first brazing filler metal layer 40 and the second brazing filler metal layer 50 are 42mm × 32mm × 0.1mm.
And (3) grinding the surface to be welded of the matrix by using 2000-mesh waterproof abrasive paper, polishing by using 0.5M diamond grinding fluid, finally cleaning in acetone for 20min by using ultrasonic waves, and drying for later use.
Then, a first brazing filler metal layer 40 is placed on the surface to be welded of the first C/C composite material panel 10, a second brazing filler metal layer 50 is placed on the surface to be welded of the second C/C composite material panel 20, then the placed first brazing filler metal layer 40 and the first C/C composite material panel 10, and the placed second brazing filler metal layer 50 and the second C/C composite material panel 20 are placed into a vacuum brazing furnace together, when the vacuum degree is lower than 3.0 x 10 < -3 > Pa, the temperature is increased to 900 ℃ at the temperature increasing speed of 10 ℃/min, the temperature is kept for 20min, then the temperature is decreased to 500 ℃ at the temperature decreasing speed of 5 ℃/min, and after the temperature is cooled to room temperature along with the furnace, the sample is taken out, and metallization is completed.
Respectively electroplating 5-micrometer-thick Cu layers on two opposite surfaces to be welded of the alloy honeycomb core 30, then sequentially assembling a first metalized brazing filler metal layer 40 and a first C/C composite panel 10, the alloy honeycomb core 30, a second metalized brazing filler metal layer 50 and a second C/C composite panel 20, applying 0.1MPa pressure, putting into a vacuum brazing furnace, increasing the temperature to 1180 ℃ at a temperature increasing speed of 10 ℃/min when the vacuum degree is lower than 3.0 x 10 < -3 > Pa, preserving the temperature for 10min, decreasing the temperature to 500 ℃ at a temperature decreasing speed of 10 ℃/min, cooling to room temperature along with the furnace, taking out a sample, and completing brazing.
The test results show that the test realizes the effective connection of the first C/C composite material panel 10, the second C/C composite material panel 20 and the alloy honeycomb core 30. The interface structure is typical Nb (s, s) and TiNi phase, the maximum tensile strength of the honeycomb sandwich structure is 27MPa, and the compressive strength is 19MPa.
The present patent is not limited to the alloy honeycomb core 30 and corresponding active braze system described herein, and researchers can select the optimum active braze for a particular joint substrate.
It will be evident to those skilled in the art that the present application is not limited to the details of the foregoing illustrative embodiments, and that the present application may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the application being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present application and not for limiting, and although the present application is described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions can be made to the technical solutions of the present application without departing from the spirit and scope of the technical solutions of the present application.

Claims (6)

1. A honeycomb sandwich structure formed by C/C composite materials and alloys is characterized by comprising a first C/C composite material panel, a second C/C composite material panel and an alloy honeycomb core, wherein the alloy honeycomb core is one of a nickel-based alloy honeycomb core, an aluminum alloy honeycomb core and a titanium alloy honeycomb core, the alloy honeycomb core is connected between the first C/C composite material panel and the second C/C composite material panel, a first brazing filler metal layer is connected between the first C/C composite material panel and the alloy honeycomb core, a second brazing filler metal layer is connected between the second C/C composite material panel and the alloy honeycomb core, the first brazing filler metal layer and the second brazing filler metal layer are made of one of AgCuTi, tiZrNiCu and TiNiNb and Cu, and the first brazing filler metal layer and the second brazing filler metal layer are both 100-150 mu m thick.
2. The honeycomb sandwich structure formed from the C/C composite materials and alloys of claim 1 wherein the nickel-based alloy forming the nickel-based alloy honeycomb core is one of GH3536, GH5188, GH99, the titanium alloy forming the titanium alloy honeycomb core is one of TC1, TC4, TA15, TA60, and the aluminum alloy forming the aluminum alloy honeycomb core is one of AA3003 and AA 5052.
3. A method for preparing a honeycomb sandwich structure of the C/C composite material and alloy according to any of claims 1-2, comprising the steps of:
obtaining a first C/C composite material panel, a second C/C composite material panel and an alloy honeycomb core through wire cut electrical discharge machining;
the first C/C composite material panel, the second C/C composite material panel and the alloy honeycomb core are arranged in a laminated mode, a first brazing filler metal layer is arranged between the first C/C composite material panel and the alloy honeycomb core, and a second brazing filler metal layer is arranged between the second C/C composite material panel and the alloy honeycomb core;
and brazing the first C/C composite material panel, the first brazing filler metal layer, the alloy honeycomb core, the second brazing filler metal layer and the second C/C composite material panel to ensure that two opposite side surfaces of the first brazing filler metal layer are respectively and fixedly connected with one side surface of the alloy honeycomb core and the first C/C composite material panel and two opposite side surfaces of the second brazing filler metal layer are respectively and fixedly connected with the other side surface of the alloy honeycomb core and the second C/C composite material panel, and obtaining a honeycomb sandwich structure formed by C/C composite materials and alloys.
4. The method of making a honeycomb sandwich structure of C/C composite materials and alloys according to claim 3 wherein after the step of obtaining a first panel of C/C composite material, a second panel of C/C composite material and an alloy honeycomb core by wire electrical discharge machining, the method further comprises:
and grinding and polishing the surfaces to be welded of the first C/C composite material panel, the alloy honeycomb core and the second C/C composite material panel by using sand paper, and then placing the surfaces in an acetone solution for ultrasonic cleaning.
5. A method of making a honeycomb sandwich structure of C/C composite and alloy according to claim 3 wherein the steps of stacking the first C/C composite face sheet, the second C/C composite face sheet, and the alloy honeycomb core with a first braze layer disposed therebetween and a second braze layer disposed therebetween further comprises:
respectively aligning the first C/C composite material panel and the second C/C composite material panel
Applying opposite pressure of 0.01-0.03MPa.
6. The method of making the honeycomb sandwich structure of C/C composites and alloys of claim 5 wherein the brazing step comprises:
the first C/C composite material panel, the first solder layer and the second solder layer are pressed,
The alloy honeycomb core, the second brazing filler metal layer and the second C/C composite material panel are placed in a vacuum furnace for heating, and when the vacuum degree is lower than 3.0 multiplied by 10 -3 And after Pa, raising the temperature to the brazing temperature at the heating rate of 10 ℃/min, preserving the heat for 5-20min, then lowering the temperature to 500 ℃ at the cooling rate of 5 ℃/min, cooling the sample to room temperature along with the vacuum furnace, and taking out the sample to finish brazing.
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