3D printing precursor conversion ceramic superstructure for novel aircraft and preparation method of 3D printing precursor conversion ceramic superstructure

Abstract

The invention provides a 3D printing precursor conversion ceramic superstructure for a novel aircraft and a preparation method, and belongs to the technical field of superstructure ceramic material additive manufacturing. The method comprises the following steps: firstly, designing a superstructure model through modeling software, and slicing the model by utilizing slicing software; then preparing a precursor resin solution with a photocuring characteristic; the preparation method comprises the following steps: preparing a superstructure, performing photocuring printing on the superstructure by using a 3D printer, cleaning the cured precursor superstructure, and performing pyrolysis on the printed superstructure to obtain the 3D printing precursor conversion ceramic superstructure. The precursor conversion ceramic honeycomb superstructure and the precursor conversion ceramic dot matrix superstructure prepared by the invention have high mechanical strength, good thermal stability and excellent wave transmission performance, and have great application value in aerospace.

Description

Technical Field

[0001] The present invention relates to the technical field of superstructure additive manufacturing, and in particular to 3D printing ceramic superstructure materials and preparation methods for new aircraft. Background Art

[0002] With the development of aerospace technology, the flight speed of aircraft is constantly increasing, and aircraft need to withstand higher and higher temperatures and thermal shocks. Therefore, aircraft materials must have stable dielectric properties. How to effectively improve the material's temperature resistance, wave transmission, load-bearing and other properties is one of the key technologies for the development of a new generation of aircraft. The development of these materials is crucial to the design of a new generation of aircraft in the future. Wave-transmitting material systems include oxide systems, nitride systems, etc. These materials exhibit excellent physical and mechanical properties at high temperatures, such as high thermal shock resistance, oxidation resistance, good stability, and mechanical properties. However, as the use temperature continues to increase, material modification has been difficult to meet the needs of high temperature resistance and wave transmission, and structural design of the material is required.

[0003] In recent years, ceramic material superstructures have been favored by researchers because their artificially designed periodic structures can achieve the required functions. Traditional ceramic material superstructures are realized by mold forming or mechanical processing, which makes it difficult to achieve small-scale complex structure 3D molding. Existing studies have shown that photocuring 3D printing technology can integrate complex structures at the micro-nano scale, providing a new method for superstructure 3D manufacturing. At present, there is little research on new superstructures at home and abroad, and there is an urgent need to develop new ceramic structural materials and preparation methods. Summary of the invention

[0004] In order to overcome the above-mentioned deficiencies in the prior art, the present invention provides a 3D printed precursor-converted ceramic superstructure and a preparation method for a new aircraft, so as to realize 3D manufacturing of high-performance ceramic superstructures.

[0005] To achieve the above object, the present invention provides the following solutions:

[0006] One of the technical solutions of the present invention is to provide a method for preparing a 3D printed precursor-converted ceramic superstructure for a new aircraft, comprising the following steps:

[0007] (1) Establishing a superstructure model by using modeling software, and slicing the superstructure model by using slicing software;

[0008] (2) preparing a precursor resin solution having light-curing properties;

[0009] (3) using the slicing results of the superstructure model and the precursor resin solution, using a 3D printer to perform photocuring printing on the superstructure, and then cleaning the cured precursor superstructure;

[0010] (4) The printed precursor superstructure is pyrolyzed to obtain a 3D printed precursor-converted ceramic superstructure with high-temperature wave-transmitting performance.

[0011] As a further preferred embodiment of the present invention, the superstructure is a periodically arranged honeycomb superstructure.

[0012] As a further preferred embodiment of the present invention, the superstructure is a periodically arranged Octet lattice superstructure.

[0013] As a further preferred embodiment of the present invention, in step (3), the solidified precursor superstructure is cleaned with isopropanol.

[0014] As a further preferred embodiment of the present invention, the precursor superstructure obtained in step (3) is a precursor honeycomb superstructure, and the unit cell size of the precursor honeycomb superstructure is 373 μm, the wall thickness is 92 μm, and the thickness is 2 mm.

[0015] As a further preferred embodiment of the present invention, the precursor superstructure obtained in step (3) is a precursor Octet lattice superstructure, and the unit cell size of the precursor Octet lattice superstructure is 1.9 mm, the wall thickness is 350 μm, and the thickness is 2 mm.

[0016] As a further preference of the present invention, the ceramic superstructure obtained in step (4) is a ceramic honeycomb superstructure, wherein the unit cell size of the ceramic honeycomb superstructure is 197 μm, the wall thickness is 42 μm, and the thickness is 1.8 mm.

[0017] As a further preference of the present invention, the ceramic superstructure obtained in step (4) is a ceramic Octet lattice superstructure, and the unit cell size of the ceramic Octet lattice superstructure is 550 μm, the wall thickness is 190 μm, and the thickness is 1.8 mm.

[0018] As a further preferred embodiment of the present invention, the precursor resin solution with photocuring properties is composed of: 30-50 parts by mass of polynitrogen silane, 50-70 parts by mass of acrylic resin, 0.4 parts by mass of (2,4,6-trimethylbenzoyl) diphenylphosphine oxide photoinitiator, and 0.06 parts by mass of Sudan III light absorber.

[0019] As a further preferred embodiment of the present invention, the process parameters of the light-curing 3D printing are: light intensity is 30-50mW / cm 2 , exposure time is 2-6s, and layer thickness is 15-35μm.

[0020] As a further preferred embodiment of the present invention, the ceramic is Si3N4 ceramic material.

[0021] As a further preferred embodiment of the present invention, the pyrolysis is carried out in a tubular furnace, the pyrolysis temperature is 1200° C., the heating rate is 0.5-3° C. / min, the pyrolysis time is 1-5 h, and the pyrolysis atmosphere is argon.

[0022] The second technical solution of the present invention is to provide a 3D printed precursor-converted ceramic superstructure for a new aircraft prepared according to the above method.

[0023] The present invention has the following technical effects:

[0024] The present invention realizes 3D manufacturing of precursor-converted ceramic superstructures with different structures. The unit cell size of the prepared ceramic honeycomb superstructure is 197μm and the wall thickness is 42μm; the unit cell size of the prepared ceramic lattice superstructure is 550μm and the wall thickness is 190μm. The preparation method is simple, the scale is small, and the structure is complex. The precursor-converted ceramic superstructure provided by the present invention has high strength and good temperature resistance, a three-point bending strength of 170-220MPa, and can still maintain its structure at a high temperature of 1200-1400℃. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0026] Figure 1 A model diagram of a honeycomb superstructure in Example 1 of the present invention;

[0027] Figure 2 This is a micrograph of a precursor-converted ceramic honeycomb superstructure prepared in Example 1 of the present invention;

[0028] Figure 3 This is a micrograph of a precursor-converted ceramic honeycomb superstructure according to Example 2 of the present invention;

[0029] Figure 4 This is a model diagram of the Octet lattice superstructure in Example 3 of the present invention. DETAILED DESCRIPTION

[0030] The present invention is further described below in conjunction with the accompanying drawings and examples. The embodiments of the present invention include but are not limited to the following examples.

[0031] Example 1

[0032] (1) Use modeling software to build a honeycomb superstructure model with a honeycomb unit cell size of 373 μm, a wall thickness of 92 μm, and a thickness of 2 mm. Then use slicing software to slice the model with a slice thickness of 20 μm;

[0033] (2) Weigh 600 g of acrylic resin solution, add 400 g of polynitrosilane, add 2.4 g of (2,4,6-trimethylbenzoyl) diphenylphosphine oxide powder as a photoinitiator and stir until dissolved, then add 0.36 g of Sudan Red III powder as a light absorber, stir for 30 min, and then ultrasonicate for 10 min;

[0034] (3) The solution obtained in step (2) was transferred to a material tank, and the honeycomb superstructure was printed using a surface projection micro-stereoscopic light-curing 3D printer. The printing parameters were as follows: layer thickness 20 μm, exposure intensity 40 mW / cm 2 , exposure time 3s. After printing is completed, the precursor honeycomb superstructure is obtained, and the cured precursor superstructure is cleaned with isopropanol;

[0035] (4) The precursor honeycomb superstructure obtained in step (3) is placed in a tube furnace and treated at 1200° C. for 3 h in an argon atmosphere to obtain a precursor-converted ceramic superstructure. The bending strength thereof is then measured.

[0036] The composition of the 3D printed precursor transformed ceramic honeycomb superstructure into a periodically arranged hexagonal honeycomb structure, e.g. Figure 1 , Figure 2 shown.

[0037] The 3D printed precursor-converted ceramic honeycomb superstructure has a bending strength of approximately 170 MPa and a dielectric constant of approximately 3.0, which can be used as a wave-transmitting material with high mechanical strength and low dielectric constant.

[0038] Example 2

[0039] The only difference from Example 1 is that the 3D printed precursor obtained in step (4) of Example 1 is converted into a ceramic honeycomb superstructure and treated at 1200° C., 1300° C., and 1400° C. for 1 h in an argon atmosphere.

[0040] After high-temperature treatment, the 3D printed precursor-converted ceramic honeycomb superstructure has no cracks on its surface and its structure is not destroyed, showing excellent high-temperature resistance.

[0041] Example 3

[0042] The only difference from Example 1 is that the model established by the modeling software in step (1) is an Octet lattice superstructure, the Octet lattice unit cell size is 1.9 mm, the wall thickness is 350 μm, and the thickness is 2 mm.

[0043] The 3D printed precursor-converted ceramic lattice superstructure has a bending strength of 220MPa, a dielectric constant of approximately 3.5, and excellent mechanical properties.

[0044] Comparative Example 1

[0045] The only difference from Example 1 is that this comparative example does not use photocuring 3D printing to prepare the precursor-converted ceramic superstructure, and step (1) of Example 1 is not performed.

[0046] The preparation steps of the precursor-converted ceramic material in this embodiment are as follows: Take a small amount of the solution obtained in step (2) of Example 1 and directly cure it in a UV curing box. The cured precursor ceramic is placed in a tube furnace for pyrolysis, and the pyrolysis conditions are the same as those in step (3) of Example 1. Then, the pyrolyzed precursor-converted ceramic material is placed in a ball mill for 12 hours, sieved, ground with a mortar, and the obtained powder is pressed into a dense sheet using a tablet press, and its dielectric constant is tested.

[0047] Compared with the results of Examples 1-3 of the present invention, the precursor-converted ceramic material without a superstructure cannot measure the bending strength, and the dielectric constant is 4.3.

[0048] Comparative Example 2

[0049] The only difference from Comparative Example 1 is that the powder obtained in this comparative example is pressed into a dense sheet by a tablet press, sintered at 1400°C for 3h, and its bending strength and dielectric constant are tested. Compared with the results of Examples 1-3 of the present invention, the precursor-converted ceramic material without a superstructure has a bending strength of 120MPa and a dielectric constant of 4.5. It is proved that the precursor-converted ceramic metamaterial prepared by the present invention can effectively improve the wave transmission performance of the material.

[0050] Finally, it should be noted that what is disclosed above is only a specific embodiment of the present invention, which is only used to illustrate the technical solution of the present invention rather than to limit it. Those skilled in the art should understand that the technical solution of the present invention can be modified or replaced by equivalents without departing from the purpose and scope of the technical solution of the present invention, which should be included in the scope of the claims of the present invention.

Claims

1. A method for preparing a 3D printed precursor-converted ceramic superstructure for a new aircraft, characterized in that: The following steps are involved: A superstructure model is established by using modeling software, and the superstructure model is sliced ​​by using slicing software; preparing a precursor resin solution having light-curing properties; Using the slicing results of the superstructure model and the precursor resin solution, the superstructure is photocured by a 3D printer, and the cured precursor superstructure is cleaned; The printed precursor superstructure is pyrolyzed to obtain a 3D printed precursor-converted ceramic superstructure with high-temperature wave-transmitting performance.

2. The method according to claim 1, characterized in that The superstructure is a periodically arranged honeycomb superstructure or a periodically arranged Octet lattice superstructure.

3. The method according to claim 1, characterized in that The cleaning of the solidified precursor superstructure is carried out by using isopropanol.

4. The method according to claim 1, characterized in that: The precursor superstructure is a precursor honeycomb superstructure, and the unit cell size of the precursor honeycomb superstructure is 373 μm, the wall thickness is 92 μm, and the thickness is 2 mm.

5. The method according to claim 1, characterized in that The precursor superstructure is a precursor Octet lattice superstructure, and the unit cell size of the precursor Octet lattice superstructure is 1.9 mm, the wall thickness is 350 μm, and the thickness is 2 mm.

6. The method according to claim 1, characterized in that The ceramic superstructure is a ceramic honeycomb superstructure, and the unit cell size of the ceramic honeycomb superstructure is 197 μm, the wall thickness is 42 μm, and the thickness is 1.8 mm.

7. The method according to claim 1, characterized in that The ceramic superstructure is a ceramic Octet lattice superstructure, and the unit cell size of the ceramic Octet lattice superstructure is 550 μm, the wall thickness is 190 μm, and the thickness is 1.8 mm.

8. The method according to claim 1, characterized in that The precursor resin solution with photocuring properties is composed of: 30-50 parts by weight of polynitrosilane, 50-70 parts by weight of acrylic resin, 0.4 parts by weight of (2,4,6-trimethylbenzoyl) diphenylphosphine oxide photoinitiator, and 0.06 parts by weight of Sudan III light absorber.

9. The method according to claim 1, characterized in that: The process parameters of the light-curing printing are: light intensity is 30-50mW / cm 2 , exposure time is 2-6s, layer thickness is 15-35μm; the pyrolysis is carried out in a tubular furnace, the pyrolysis temperature is 1200°C, the heating rate is 0.5-3°C / min, the pyrolysis time is 1-5h, and the pyrolysis atmosphere is argon.

10. A 3D printed precursor-converted ceramic superstructure for a new aircraft prepared by the method of any one of claims 1 to 9.

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