CN118124213B - Wear-resistant light unmanned aerial vehicle casing composite metal material - Google Patents
Wear-resistant light unmanned aerial vehicle casing composite metal material Download PDFInfo
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- CN118124213B CN118124213B CN202410557961.6A CN202410557961A CN118124213B CN 118124213 B CN118124213 B CN 118124213B CN 202410557961 A CN202410557961 A CN 202410557961A CN 118124213 B CN118124213 B CN 118124213B
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- 239000002131 composite material Substances 0.000 title claims abstract description 57
- 239000007769 metal material Substances 0.000 title claims abstract description 30
- 239000003292 glue Substances 0.000 claims abstract description 23
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 14
- 239000004917 carbon fiber Substances 0.000 claims abstract description 14
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical group C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 13
- 239000011159 matrix material Substances 0.000 claims abstract description 11
- 238000000034 method Methods 0.000 claims abstract description 10
- 239000011156 metal matrix composite Substances 0.000 claims description 26
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 18
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 18
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 17
- 239000000835 fiber Substances 0.000 claims description 17
- 229910000861 Mg alloy Inorganic materials 0.000 claims description 16
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 14
- 239000000463 material Substances 0.000 claims description 14
- 229910021484 silicon-nickel alloy Inorganic materials 0.000 claims description 14
- 229910000640 Fe alloy Inorganic materials 0.000 claims description 13
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 13
- 238000001816 cooling Methods 0.000 claims description 6
- 238000002360 preparation method Methods 0.000 claims description 6
- 238000005245 sintering Methods 0.000 claims description 6
- 238000003892 spreading Methods 0.000 claims description 6
- 238000003756 stirring Methods 0.000 claims description 6
- 239000000758 substrate Substances 0.000 claims description 6
- 238000004519 manufacturing process Methods 0.000 claims description 5
- 239000011185 multilayer composite material Substances 0.000 claims description 5
- 238000013329 compounding Methods 0.000 claims description 4
- 239000002318 adhesion promoter Substances 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 238000001035 drying Methods 0.000 claims description 3
- 238000007731 hot pressing Methods 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims description 3
- 238000005260 corrosion Methods 0.000 abstract description 10
- 230000007797 corrosion Effects 0.000 abstract description 10
- 229910052751 metal Inorganic materials 0.000 abstract description 2
- 239000002184 metal Substances 0.000 abstract description 2
- 239000011257 shell material Substances 0.000 description 27
- 230000000052 comparative effect Effects 0.000 description 12
- 239000002994 raw material Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 208000019901 Anxiety disease Diseases 0.000 description 1
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000036506 anxiety Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000005543 nano-size silicon particle Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 235000012239 silicon dioxide Nutrition 0.000 description 1
Abstract
The invention provides a wear-resistant light unmanned aerial vehicle shell composite metal material, which belongs to the technical field of unmanned aerial vehicles, and comprises a plurality of layers of composite materials, wherein the plurality of layers of composite materials comprise a matrix layer, an intermediate layer and a composite layer, the matrix layer, the intermediate layer and the composite layer are sequentially compounded from bottom to top, the matrix layer is carbon fiber, the intermediate layer is electromagnetic shielding glue, and the composite layer is a metal-based composite material. The wear-resistant light unmanned aerial vehicle shell composite metal material can remarkably improve the impact strength of the unmanned aerial vehicle shell, has the advantages of being simple in forming process, wear-resistant, corrosion-resistant, light in weight and the like, can directly lighten the weight of the unmanned aerial vehicle body when being applied to the unmanned aerial vehicle shell structure, ensures the effective load of the unmanned aerial vehicle, and plays an important role in the stealth performance and the safety performance of the unmanned aerial vehicle.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a wear-resistant light unmanned aerial vehicle shell composite metal material.
Background
At present, along with the development of informatization, the unmanned aerial vehicle is rapidly applied to various industries, such as reconnaissance and target plane for military use, and is used for civil aerial photography, agriculture, plant protection, miniature self-timer, express delivery transportation, disaster relief, wild animal observation, infectious disease monitoring, mapping, news reporting, power inspection, disaster relief, video shooting, romantic manufacturing and the like, so that the application of the unmanned aerial vehicle is greatly expanded, and developed countries are also actively expanding the application and development of unmanned aerial vehicle technology in industries.
Although unmanned aerial vehicles are widely applied and popularized in the market, the unmanned aerial vehicles are easily rusted due to the influence of external factors, and the use requirements of people cannot be met in certain specific environments, in addition, the unmanned aerial vehicle shell is used as an important component of the unmanned aerial vehicle, in winter, metal materials are often reduced due to the influence of weather, the metal materials are often damaged due to low temperature, so that various unexpected situations are caused, the wear resistance of the existing metal materials cannot meet ideal requirements, the quality is heavy, and the corrosion resistance is cause anxiety, so that the requirements of the development of various industries of society on the unmanned aerial vehicle materials are far met.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide the wear-resistant light unmanned aerial vehicle shell composite metal material which can obviously improve the impact strength of the unmanned aerial vehicle shell, has the advantages of simple forming process, wear resistance, corrosion resistance, light weight and the like, can directly lighten the weight of the unmanned aerial vehicle body when being applied to the unmanned aerial vehicle shell structure, ensures the effective load of the unmanned aerial vehicle, and has an important effect on the stealth performance and the safety performance of the unmanned aerial vehicle.
In order to achieve the above object, the present invention provides the following solutions:
The utility model provides a wear-resisting light unmanned aerial vehicle casing combined metal material, combined metal material comprises multilayer combined material, multilayer combined material includes basal body layer, intermediate level and composite bed, basal body layer, intermediate level and composite bed are compound from top to bottom in proper order, the basal body layer is carbon fiber, the intermediate level is electromagnetic shield glue, the composite bed is metal matrix combined material.
Preferably, the thickness of the multilayer composite is 6-8 mm, wherein the thickness of the substrate layer is 2-2.5 mm, the thickness of the intermediate layer is 2.5-3.5 mm, and the thickness of the composite layer is 1.5-2 mm.
Preferably, the preparation method of the multilayer composite material comprises the following steps: firstly preheating carbon fiber, spreading and coating a uniform adhesion promoter on the surface, then placing electromagnetic shielding glue on the surface, adjusting the thickness of the electromagnetic shielding glue, placing a metal matrix composite above the electromagnetic shielding glue, pressurizing and standing for 24 hours to obtain the multilayer composite.
Preferably, the preheating treatment process for the carbon fiber comprises the following steps: and drying the carbon fiber, and then carrying out hot pressing treatment for 15min under the conditions of 100-120 ℃ and 0.1-0.2 MPa.
Preferably, the compounding process of the electromagnetic shielding glue is as follows: and adjusting the thickness of the electromagnetic shielding glue through a four-side coater or a coater, then spreading the metal matrix composite on the surface of the electromagnetic shielding glue, and pressurizing for 15-20 min under the condition of 0.01-0.02 MPa.
Preferably, the metal matrix composite is prepared from the following components in parts by weight:
16-28 parts of copper powder, 5-10 parts of iron powder, 5-10 parts of aluminum powder, 12-18 parts of nickel-silicon alloy, 5-8 parts of magnesium alloy, 5-8 parts of multi-element iron alloy, 20-35 parts of fiber reinforced titanium alloy and 5-10 parts of nano-scale silicon dioxide powder.
Preferably, the preparation process of the metal matrix composite material comprises the following steps: placing the copper powder, the iron powder and the aluminum powder into a stirring tank, adding viscous liquid, stirring at a high speed for 20min to obtain gel, then placing the gel into a sintering tank, sequentially adding nickel-silicon alloy, magnesium alloy, multi-element iron alloy, fiber reinforced titanium alloy and nano-scale silicon dioxide powder into the gel, performing roll forming at the temperature of 1100-1300 ℃, then performing cooling treatment on the sintering tank at the speed of 10 ℃/min, and cooling along with a furnace to obtain the metal matrix composite.
Preferably, the composite metal material is applied to unmanned aerial vehicle shell manufacturing.
In view of the foregoing, a metal matrix composite includes: copper powder, iron powder, aluminum powder, nickel-silicon alloy, magnesium alloy, multi-element iron alloy, fiber reinforced titanium alloy and nano silicon dioxide, and the copper powder has the characteristics of good electrical conductivity, thermal conductivity and wear resistance, and can improve the wear resistance of unmanned aerial vehicle shell materials by being used as a raw material, but the consumption of the copper powder can not be used in a large amount, so that the weight of the shell can be increased, and the use of the unmanned aerial vehicle is affected.
Secondly, aluminum powder is also involved in the raw materials, and is used as one of the materials of the unmanned aerial vehicle shell, so that light weight, high strength and good wear resistance are provided for the unmanned aerial vehicle shell, and meanwhile, the addition of nickel-silicon alloy can also improve the high-temperature performance and corrosion resistance of the unmanned aerial vehicle shell; the addition of the magnesium alloy can improve the light weight degree, strength and corrosion resistance of the shell, and the fiber reinforced titanium alloy combines the high strength and light weight characteristics of the titanium alloy and the excellent performance of the fiber reinforced material, so that the strength and rigidity of the unmanned aerial vehicle shell are improved, and the unmanned aerial vehicle shell is kept to have lighter weight; while nanoscale silica powders are used to improve the abrasion, impact and corrosion resistance of unmanned aerial vehicle enclosures.
Finally, according to the excellent properties of the components of each part of the raw materials, the raw materials are compounded to prepare the unmanned aerial vehicle shell material, so that the unmanned aerial vehicle shell has the characteristics of wear resistance, light weight and corrosion resistance.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
The invention provides a wear-resistant light unmanned aerial vehicle shell composite metal material which is composed of a plurality of layers of composite materials, wherein the plurality of layers of composite materials comprise a matrix layer, a middle layer and a composite layer, the matrix layer, the middle layer and the composite layer are sequentially compounded from bottom to top, the matrix layer is made of carbon fibers, the middle layer is made of electromagnetic shielding glue, and the composite layer is made of a metal matrix composite material. Can obviously improve the impact strength of the unmanned aerial vehicle shell, has simpler molding process, has the advantages of wear resistance, corrosion resistance, light weight and the like, the unmanned aerial vehicle can be applied to the unmanned aerial vehicle shell structure to directly lighten the weight of the unmanned aerial vehicle body, ensure the effective load of the unmanned aerial vehicle and play an important role in stealth performance and safety performance of the unmanned aerial vehicle.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic structural view of a wear-resistant lightweight unmanned aerial vehicle chassis composite metal material according to the present invention;
1-substrate layer, 2-intermediate layer and 3-composite layer.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide the wear-resistant light unmanned aerial vehicle shell composite metal material, which can remarkably improve the impact strength of the unmanned aerial vehicle shell, has the advantages of simple forming process, wear resistance, corrosion resistance, light weight and the like, can directly lighten the weight of the unmanned aerial vehicle body when being applied to the unmanned aerial vehicle shell structure, ensures the effective load of the unmanned aerial vehicle, and has important effects on the stealth performance and the safety performance of the unmanned aerial vehicle.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Example 1
As shown in fig. 1, the invention provides a wear-resistant light unmanned aerial vehicle shell composite metal material, wherein the composite metal material is composed of a plurality of layers of composite materials, each layer of composite materials comprises a substrate layer 1, a middle layer 2 and a composite layer 3, the substrate layer 1, the middle layer 2 and the composite layer 3 are sequentially compounded from top to bottom, the substrate layer 1 is carbon fiber, the middle layer 2 is electromagnetic shielding glue, and the composite layer 3 is a metal matrix composite material.
The thickness of the multilayer composite material is 6-8 mm, the thickness of the matrix layer 1 is 2-2.5 mm, the thickness of the intermediate layer 2 is 2.5-3.5 mm, and the thickness of the composite layer 3 is 1.5-2 mm.
Specifically, the preparation method of the multilayer composite material comprises the following steps: firstly preheating carbon fiber, spreading and coating a uniform adhesion promoter on the surface, then placing electromagnetic shielding glue on the surface, adjusting the thickness of the electromagnetic shielding glue, placing a metal matrix composite above the electromagnetic shielding glue, pressurizing and standing for 24 hours to obtain the multilayer composite.
Wherein, the preheating treatment of the carbon fiber comprises: and drying the carbon fiber, and then carrying out hot pressing treatment for 15min at 110 ℃ under the condition of 0.1-0.2 MPa.
Specifically, the compounding process of the electromagnetic shielding glue comprises the following steps: adjusting the thickness of the electromagnetic shielding glue by a four-side coater or a coater, then spreading a metal matrix composite on the surface of the electromagnetic shielding glue, and pressurizing for 15-20 min under the condition of 0.01-0.02 MPa.
Specifically, the metal matrix composite is prepared from the following components in parts by weight:
16 parts of copper powder, 10 parts of iron powder, 10 parts of aluminum powder, 18 parts of nickel-silicon alloy, 8 parts of magnesium alloy, 8 parts of multi-element iron alloy, 20 parts of fiber reinforced titanium alloy and 10 parts of nano-scale silicon dioxide powder.
The preparation method of the metal matrix composite material comprises the following steps: placing copper powder, iron powder and aluminum powder in a stirring tank, adding viscous liquid, stirring at high speed for 20min to obtain gel, then placing the gel in a sintering tank, sequentially adding nickel-silicon alloy, magnesium alloy, multi-element iron alloy, fiber reinforced titanium alloy and nanoscale silicon dioxide powder, performing roll forming at 1200 ℃, performing cooling treatment at 10 ℃/min on the sintering tank, and cooling along with a furnace to obtain the metal matrix composite.
And (3) sequentially compounding the materials from bottom to top to finally obtain a composite metal material, and applying the composite metal material to manufacturing of the unmanned aerial vehicle shell.
Example 2
Unlike example 1, the metal matrix composite is prepared from the following components in parts by weight:
25 parts of copper powder, 8 parts of iron powder, 8 parts of aluminum powder, 17 parts of nickel-silicon alloy, 8 parts of magnesium alloy, 8 parts of multi-element iron alloy, 20 parts of fiber reinforced titanium alloy and 6 parts of nano-scale silicon dioxide powder.
Example 3
Unlike example 1, the metal matrix composite is prepared from the following components in parts by weight:
20 parts of copper powder, 7 parts of iron powder, 7 parts of aluminum powder, 15 parts of nickel-silicon alloy, 7 parts of magnesium alloy, 7 parts of multi-element iron alloy, 30 parts of fiber reinforced titanium alloy and 7 parts of nano-scale silicon dioxide powder.
Example 4
Unlike example 1, the metal matrix composite is prepared from the following components in parts by weight:
28 parts of copper powder, 5 parts of iron powder, 5 parts of aluminum powder, 12 parts of nickel-silicon alloy, 5 parts of magnesium alloy, 5 parts of multi-element iron alloy, 35 parts of fiber reinforced titanium alloy and 5 parts of nano-scale silicon dioxide powder.
Comparative example 1
Unlike example 1, the addition of iron powder was omitted and the metal matrix composite was prepared from the following components in parts by weight:
21 parts of copper powder, 15 parts of aluminum powder, 18 parts of nickel-silicon alloy, 8 parts of magnesium alloy, 8 parts of multi-element iron alloy, 20 parts of fiber reinforced titanium alloy and 10 parts of nano-scale silicon dioxide powder.
Comparative example 2
Unlike example 1, the addition amount of copper powder was reduced, and the metal matrix composite was prepared from the following components in parts by weight:
11 parts of copper powder, 10 parts of iron powder, 10 parts of aluminum powder, 18 parts of nickel-silicon alloy, 8 parts of magnesium alloy, 8 parts of multi-element iron alloy, 25 parts of fiber reinforced titanium alloy and 10 parts of nano-scale silicon dioxide powder.
Comparative example 3
Unlike example 1, the raw materials only selected from copper powder, magnesium alloy, fiber reinforced titanium alloy and nanoscale silicon dioxide powder, the metal matrix composite material is prepared from the following components in parts by weight:
30 parts of copper powder, 20 parts of magnesium alloy, 25 parts of fiber reinforced titanium alloy and 25 parts of nanoscale silicon dioxide powder.
Comparative example 4
Unlike example 1, the metal matrix composite is prepared from the following components in parts by weight:
16 parts of copper powder, 3 parts of iron powder, 3 parts of aluminum powder, 20 parts of nickel-silicon alloy, 12 parts of magnesium alloy, 14 parts of multi-element iron alloy, 14 parts of fiber reinforced titanium alloy and 18 parts of nano-scale silicon dioxide powder.
The raw material ratios in this embodiment are also corresponding to a plurality of groups of comparison tests, which are not described in detail herein, and four optimal comparison examples are selected to further describe the results of the present invention.
The composite metal materials obtained in examples 1 to 4 and comparative examples 1 to 4 were respectively applied to the fabrication of the unmanned aerial vehicle chassis, and were respectively tested, and the test results are shown in table 1.
Table 1 test results
| Examples | Tensile Strength (MPa) | Elongation at break (%) | Abrasion loss (%) | Weight (kg) |
| Example 1 | 2800 | 4.67 | 19 | 7.5 |
| Example 2 | 2750 | 4.72 | 16 | 8.2 |
| Example 3 | 2850 | 4.63 | 18 | 7.3 |
| Example 4 | 2700 | 4.74 | 13 | 8.1 |
| Comparative example 1 | 2950 | 4.53 | 22 | 9.4 |
| Comparative example 2 | 2900 | 4.55 | 20 | 10.5 |
| Comparative example 3 | 2985 | 4.40 | 34 | 9.7 |
| Comparative example 4 | 2925 | 4.49 | 17 | 11.3 |
As can be seen from Table 1, the composite metal materials prepared in examples 1 to 4 and comparative examples 1 to 4 are lower in tensile strength and increased in elongation at break compared with the composite metal materials prepared in examples 1 to 4, which means that the composite metal materials are better in softness, higher in elasticity and strong in impact resistance, and are suitable for unmanned aerial vehicle shells. Meanwhile, the composite metal materials prepared in comparative examples 1-4 and comparative examples 1-4 have the characteristics of wear resistance, light weight and the like.
The beneficial effects of the invention are as follows:
The wear-resistant light unmanned aerial vehicle shell composite metal material provided by the invention can obviously improve the impact strength of the unmanned aerial vehicle shell, has the advantages of being simple in forming process, wear-resistant, corrosion-resistant, light in weight and the like, can directly lighten the weight of the unmanned aerial vehicle body when being applied to the unmanned aerial vehicle shell structure, ensures the effective load of the unmanned aerial vehicle, and has an important effect on the stealth performance and the safety performance of the unmanned aerial vehicle.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the methods of the present invention and the core ideas thereof; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (4)
1. The wear-resistant light unmanned aerial vehicle shell composite metal material is characterized by comprising a plurality of layers of composite materials, wherein the plurality of layers of composite materials comprise a matrix layer, an intermediate layer and a composite layer, the matrix layer, the intermediate layer and the composite layer are sequentially compounded from top to bottom, the matrix layer is carbon fiber, the intermediate layer is electromagnetic shielding glue, and the composite layer is a metal matrix composite material;
The metal matrix composite is prepared from the following components in parts by weight:
16-28 parts of copper powder, 5-10 parts of iron powder, 5-10 parts of aluminum powder, 12-18 parts of nickel-silicon alloy, 5-8 parts of magnesium alloy, 5-8 parts of multi-element iron alloy, 20-35 parts of fiber reinforced titanium alloy and 5-10 parts of nano-scale silicon dioxide powder;
The thickness of the multilayer composite material is 6-8 mm, wherein the thickness of the substrate layer is 2-2.5 mm, the thickness of the intermediate layer is 2.5-3.5 mm, and the thickness of the composite layer is 1.5-2 mm;
The preparation method of the multilayer composite material comprises the following steps: firstly preheating carbon fiber, spreading and coating a uniform adhesion promoter on the surface, then placing electromagnetic shielding glue on the surface, adjusting the thickness of the electromagnetic shielding glue, placing a metal matrix composite above the electromagnetic shielding glue, pressurizing and standing for 24 hours to obtain a multilayer composite;
The compounding process of the electromagnetic shielding glue comprises the following steps: and adjusting the thickness of the electromagnetic shielding glue through a four-side coater or a coater, then spreading the metal matrix composite on the surface of the electromagnetic shielding glue, and pressurizing for 15-20 min under the condition of 0.01-0.02 MPa.
2. The wear-resistant lightweight unmanned aerial vehicle shell composite metal material according to claim 1, wherein the carbon fiber is subjected to preheating treatment by the following steps: and drying the carbon fiber, and then carrying out hot pressing treatment for 15min under the conditions of 100-120 ℃ and 0.1-0.2 MPa.
3. The wear-resistant light unmanned aerial vehicle shell composite metal material according to claim 1, wherein the preparation process of the metal matrix composite material is as follows: placing the copper powder, the iron powder and the aluminum powder into a stirring tank, adding viscous liquid, stirring at a high speed for 20min to obtain gel, then placing the gel into a sintering tank, sequentially adding nickel-silicon alloy, magnesium alloy, multi-element iron alloy, fiber reinforced titanium alloy and nano-scale silicon dioxide powder into the gel, performing roll forming at the temperature of 1100-1300 ℃, then performing cooling treatment on the sintering tank at the speed of 10 ℃/min, and cooling along with a furnace to obtain the metal matrix composite.
4. The wear-resistant light unmanned aerial vehicle shell composite metal material according to any one of claims 1-3, wherein the composite metal material is applied to unmanned aerial vehicle shell manufacturing.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410557961.6A CN118124213B (en) | 2024-05-08 | Wear-resistant light unmanned aerial vehicle casing composite metal material |
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| CN202410557961.6A CN118124213B (en) | 2024-05-08 | Wear-resistant light unmanned aerial vehicle casing composite metal material |
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| CN118124213A CN118124213A (en) | 2024-06-04 |
| CN118124213B true CN118124213B (en) | 2024-07-12 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106535604A (en) * | 2016-11-28 | 2017-03-22 | 深圳市智璟科技有限公司 | Electromagnetic shielding structure used for unmanned aerial vehicle |
| CN108396216A (en) * | 2018-06-04 | 2018-08-14 | 芜湖征途电子科技有限公司 | A kind of wearable lightweight unmanned plane wing material |
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106535604A (en) * | 2016-11-28 | 2017-03-22 | 深圳市智璟科技有限公司 | Electromagnetic shielding structure used for unmanned aerial vehicle |
| CN108396216A (en) * | 2018-06-04 | 2018-08-14 | 芜湖征途电子科技有限公司 | A kind of wearable lightweight unmanned plane wing material |
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