The structure of the fuselage, wings and their frame and propeller blades of a drone

Abstract

This invention provides a fuselage, wing, frame, and propeller blade structure for a drone. The structure is characterized by comprising a carbon fiber layer and at least one metal sheet. Specifically, in existing drone fuselage, wing, frame, and propeller blade structures entirely made of carbon fiber, a portion of the carbon fiber material is removed and replaced with a metal sheet to create a composite material with a carbon fiber layer and at least one metal sheet. The carbon fiber layer consists of at least one layer of carbon fiber prepreg. This carbon fiber layer overlaps with the at least one metal sheet, and each material layer is covered by a prepreg matrix. This pre-forms the initial appearance of the drone fuselage, wing, frame, and propeller blades, which are then cured by heat. After curing, the transverse cross-section of the entire drone fuselage, wing, frame, and propeller blade structure resembles a sandwich structure.

Claims

1. A fuselage structure for a drone, characterized in that: the fuselage of the drone comprises a carbon fiber layer and at least one metal sheet, that is, in an existing drone fuselage structure made entirely of carbon fiber, a certain percentage of the carbon fiber material is removed and replaced with a metal sheet to form a composite material having a carbon fiber layer and at least one metal sheet, wherein the carbon fiber layer is composed of at least one layer of carbon fiber prepreg; the carbon fiber layer overlaps with the at least one metal sheet, and each material layer is covered by a prepreg matrix, pre-forming the initial appearance of the drone fuselage, and then curing it by heating, so that the transverse cross-section of the entire drone fuselage structure after covering is similar to a sandwich structure.

2. The fuselage structure of the drone as described in claim 1, wherein the thickness of the carbon fiber layer is greater than the thickness of the metal sheet, and they overlap and cover each other.

3. The fuselage structure of the UAV as described in claim 1, wherein the metal sheet is selected from one of silver (Ag), copper (Cu), gold (Au), aluminum (Al), nickel (Ni), zinc (Zn), magnesium (Mg), iron (Fe), steel (Steel), brass (Brass), bronze (Bronze), cobalt (Co), molybdenum (Mo), tungsten (W), and titanium (Ti), and each layer has a thickness of less than 0.2 mm (200 µm; 0.0079 inch), and overlaps with the fiber layer, and each material layer is covered by a prepreg matrix.

4. The fuselage structure of the UAV as described in claim 3, wherein the thickness of each layer of the metal sheet material is preferably 0.004 mm (4 µm; 0.00016 inch) to 0.006 mm (6 µm; 0.00024 inch).

5. A wing structure for a drone, characterized in that: the wing structure of the drone includes a carbon fiber layer and at least one metal sheet, that is, in an existing drone wing structure that is entirely made of carbon fiber, a certain percentage of the carbon fiber material is removed and replaced with a metal sheet to form a composite material having a carbon fiber layer and at least one metal sheet, wherein the carbon fiber layer is composed of at least one layer of carbon fiber prepreg; the carbon fiber layer overlaps with the at least one metal sheet, and each material layer is covered by a prepreg matrix, and the initial appearance of the drone wing is pre-formed, and then cured by heating. After the covering is formed, the transverse cross-section of the entire drone wing structure is similar to a sandwich structure.

6. The wing structure of the UAV as described in claim 5, wherein the thickness of the carbon fiber layer is greater than the thickness of the metal sheet, and they overlap and cover each other.

7. The wing structure of the UAV as described in claim 5, wherein the metal sheet is selected from one of silver (Ag), copper (Cu), gold (Au), aluminum (Al), nickel (Ni), zinc (Zn), magnesium (Mg), iron (Fe), steel (Steel), brass (Brass), bronze (Bronze), cobalt (Co), molybdenum (Mo), tungsten (W), and titanium (Ti), and each layer has a thickness of less than 0.2 mm (200 µm; 0.0079 inch), and overlaps with the fiber layer, with each material layer having a prepreg matrix in contact with and covering each other.

8. The wing structure of the UAV as described in claim 7, wherein the thickness of each layer of the metal sheet material is preferably 0.004 mm (4 µm; 0.00016 inch) to 0.006 mm (6 µm; 0.00024 inch).

9. A skeleton structure for a drone, characterized in that: the skeleton structure of the drone comprises a carbon fiber layer and at least one metal sheet, that is, in an existing drone skeleton structure that is entirely made of carbon fiber, a certain percentage of the carbon fiber material is removed and replaced with a metal sheet to form a composite material having a carbon fiber layer and at least one metal sheet, wherein the carbon fiber layer is composed of at least one layer of carbon fiber prepreg; the carbon fiber layer overlaps with the at least one metal sheet, and each material layer is covered by a prepreg matrix, and the initial appearance of the drone skeleton is pre-formed, and then cured by heating. After the covering is formed, the transverse cross-section of the entire drone skeleton structure is similar to a sandwich structure.

10. The skeleton structure of the drone as described in claim 9, wherein the thickness of the carbon fiber layer is greater than the thickness of the metal sheet, and they overlap and cover each other.

11. The skeleton structure of the UAV as described in claim 9, wherein the metal sheet is selected from one of silver (Ag), copper (Cu), gold (Au), aluminum (Al), nickel (Ni), zinc (Zn), magnesium (Mg), iron (Fe), steel (Steel), brass (Brass), bronze (Bronze), cobalt (Co), molybdenum (Mo), tungsten (W), and titanium (Ti), and each layer has a thickness of less than 0.2 mm (200 µm; 0.0079 inch), and overlaps with the fiber layer, and each material layer is covered by a prepreg matrix in contact with each other.

12. The skeleton structure of the UAV as described in claim 11, wherein the thickness of each layer of the metal sheet material is preferably 0.004 mm (4 µm; 0.00016 inch) to 0.006 mm (6 µm; 0.00024 inch).

13. A spiral blade structure for a drone, characterized in that: the spiral blade structure of the drone comprises a carbon fiber layer and at least one metal sheet, that is, in the existing drone spiral blade structure which is entirely made of carbon fiber, a certain percentage of the carbon fiber material is removed and replaced with a metal sheet to form a composite material having a carbon fiber layer and at least one metal sheet, wherein the carbon fiber layer is composed of at least one layer of carbon fiber prepreg; the carbon fiber layer overlaps with the at least one metal sheet, and each material layer is covered by a prepreg matrix, and the initial appearance of the drone spiral blade is pre-formed, and then cured by heating. After the covering is formed, the transverse cross-section of the entire drone spiral blade structure is similar to a sandwich structure.

14. The rotor blade structure of the UAV as described in claim 13, wherein the thickness of the carbon fiber layer is greater than the thickness of the metal sheet, and the layers overlap and cover each other.

15. The propeller blade structure of the UAV as described in claim 13, wherein the metal sheet is selected from one of silver (Ag), copper (Cu), gold (Au), aluminum (Al), nickel (Ni), zinc (Zn), magnesium (Mg), iron (Fe), steel (Steel), brass (Brass), bronze (Bronze), cobalt (Co), molybdenum (Mo), tungsten (W), and titanium (Ti), and each layer has a thickness of less than 0.2 mm (200 µm; 0.0079 inch), overlaps with the fiber layer, and each material layer is covered by a prepreg matrix.

16. The rotor blade structure of the UAV as described in claim 15, wherein the thickness of each layer of the metal sheet material is preferably 0.004 mm (4 µm; 0.00016 inch) to 0.006 mm (6 µm; 0.00024 inch).

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