KR-20260064047-A - LAYERED ASSEMBLY FOR PREVENTING ICING, AIRCRAFT WING, WIND TURBINE BLADE, AND AIRCRAFT INCLUDING THE SAME

Abstract

A laminated assembly for preventing freezing, an aircraft wing including the same, a wind power blade, and an aircraft are disclosed. According to one aspect of the present disclosure, a laminated assembly may be provided comprising: a leading edge having an outer surface and an inner surface; and a metal-plated carbon fiber provided on the leading edge to provide a heat source for preventing or removing freezing to the outer surface.

Inventors

• 박일주

Assignees

• 주식회사 지티에이에어로스페이스

Dates

Publication Date

20260507

Application Date

20241031

Claims (17)

1. A leading edge having an outer surface and an inner surface; and A laminated assembly comprising a metal-coated carbon fiber (MCF) provided on the leading edge and providing a heat source for preventing or removing freezing on the outer surface.
2. In claim 1, The above-mentioned metal-plated carbon fiber is a laminated assembly comprising a fibrous metal-plated carbon fiber extended in the longitudinal direction.
3. In claim 2, The above-mentioned fiber-type metal-plated carbon fiber comprises one or more of the following: a yarn-type metal-plated carbon fiber in which a plurality of carbon fibers with a metal-coated surface are woven, or a spread tow-type metal-plated carbon fiber in which the yarn-type metal-plated carbon fiber is flattened and pressure-molded.
4. In claim 2, The above-mentioned leading edge is a laminated assembly in which part or all of it is made of metal.
5. In claim 1, The above metal-plated carbon fiber is disposed on the inner surface, and The above laminated assembly further comprises an insulating material positioned opposite the inner surface with the metal-plated carbon fiber in between, thereby restricting the inflow of the heat source in the inner direction.
6. In claim 1, The above-mentioned metal-plated carbon fiber is a laminated assembly comprising a sheet-type metal-plated carbon fiber having a predetermined area.
7. In claim 6, The above sheet-type metal-plated carbon fiber comprises a nonwoven metal-plated carbon fiber formed by bonding a plurality of carbon fiber strands with a metal-coated surface, or a blanket-type metal-plated carbon fiber formed by impregnating a thermoplastic resin into one or more of a yarn-type metal-plated carbon fiber, a spread tow-type metal-plated carbon fiber, or a nonwoven metal-plated carbon fiber.
8. In claim 6, The above-mentioned leading edge is a laminated assembly in which part or all is made of a composite material.
9. In claim 1, The above metal-plated carbon fiber is disposed on the outer surface, and The above laminated assembly further comprises a rubber pad disposed on the outer surface and accommodating the metal-plated carbon fiber inside.
10. In claim 9, The above metal-plated carbon fiber is provided as a fibrous metal-plated carbon fiber extended in the longitudinal direction, and The above-mentioned fiber-type metal-plated carbon fiber comprises one or more of the following: a yarn-type metal-plated carbon fiber in which a plurality of carbon fibers with a metal-coated surface are woven, or a spread tow-type metal-plated carbon fiber in which the yarn-type metal-plated carbon fiber is flattened and pressure-molded.
11. In claim 1, The above metal-plated carbon fiber is disposed on the outer surface, and The laminated assembly further comprises a rubber pad integrally provided on the outer surface of the metal-plated carbon fiber to shield the metal-plated carbon fiber from the outside.
12. In claim 11, The above metal-plated carbon fiber is provided as a sheet-type metal-plated carbon fiber having a predetermined area, and The above sheet-type metal-plated carbon fiber comprises a laminated assembly including one or more of a nonwoven metal-plated carbon fiber, a yarn-type metal-plated carbon fiber, a spread tow-type metal-plated carbon fiber, or a blanket-type metal-plated carbon fiber in which a thermoplastic resin is impregnated into one or more of a plurality of carbon fiber strands with a metal-coated surface, or a nonwoven metal-plated carbon fiber.
13. In claim 1, The above leading edge is provided by joining multiple layers in a multilayer manner, and The above metal-plated carbon fiber is a laminated assembly disposed between the plurality of layers.
14. In claim 14, The above metal-plated carbon fiber comprises a laminated assembly including a mesh-type metal-plated carbon fiber in which a longitudinally extended fibrous metal-plated carbon fiber is supported through a mesh support.
15. An aircraft wing comprising any one of claims 1 to 14.
16. A wind power blade comprising any one of claims 1 to 14.
17. An aircraft comprising any one of claims 1 to 14, An aircraft comprising any one of an airplane, a helicopter, a gyroplane, an unmanned aerial vehicle (UAV), and a drone.

Description

Layered assembly for preventing ice, aircraft wing, wind turbine blade, and aircraft including the same Embodiments of the present disclosure relate to a laminated assembly for preventing freezing, an aircraft wing including the same, a wind power blade, and an aircraft. Icing on aircraft wings can alter the surface shape of the wings and affect aerodynamic characteristics. Accordingly, it is necessary to properly remove icing from the wings or to suppress its formation. One known conventional method for preventing icing is the spray coating of anti-icing fluid onto the wings. In other words, anti-icing fluid is directly sprayed onto the outer surface of the wings as a temporary measure, such as before the aircraft's takeoff. Another known method involves spraying liquid de-icing fluid through a spray mechanism equipped on the wings. For instance, fine spray holes are formed on the leading edge of the wing, allowing the de-icing fluid to be sprayed onto the wing surface through these holes. Yet another method involves installing pneumatic de-icing boots, in which pneumatic tubes inflate to break and remove ice from the surface using pressure. Other known methods include removing ice by spraying high-temperature air from inside the wing or using heat from electric heaters. However, conventionally known de-icing methods have the problem of significantly increasing aircraft weight and being structurally complex. They are also inefficient in terms of energy consumption. Consequently, conventional de-icing methods are difficult to apply appropriately in small or micro aircraft that are sensitive to weight and energy efficiency. For example, the adoption of conventional de-icing methods in unmanned aerial vehicles (UAVs) and drones can be a direct cause of reduced flight time or distance. Accordingly, there is a demand for methods capable of performing de-icing more energy-efficiently. The foregoing description is provided to aid in understanding the technical background of the present disclosure. Accordingly, the foregoing description should not be interpreted as reducing, limiting, or restricting the technical concept of the present disclosure. Furthermore, the contents described or suggested in the foregoing description do not necessarily constitute prior art. The foregoing description may include contents that do not constitute prior art. FIG. 1 is an exemplary diagram of an unmanned aerial vehicle including a laminated assembly according to one embodiment of the present disclosure. FIG. 2 is a schematic cross-sectional view showing a laminated assembly according to one embodiment of the present disclosure. FIG. 3 is a schematic cross-sectional view showing a laminated assembly according to another embodiment of the present disclosure. FIG. 4 is a schematic cross-sectional view showing a laminated assembly according to another embodiment of the present disclosure. FIG. 5 is a schematic cross-sectional view showing a laminated assembly according to another embodiment of the present disclosure. FIG. 6 is a schematic cross-sectional view showing a laminated assembly according to another embodiment of the present disclosure. FIG. 7 is a schematic cross-sectional view showing a laminated assembly according to another embodiment of the present disclosure. FIG. 8 is an exemplary illustration of a helicopter including a laminated assembly according to one embodiment of the present disclosure. FIG. 9 is an exemplary diagram of a wind power blade including a laminated assembly according to one embodiment of the present disclosure. Embodiments of the present disclosure will be described below with reference to the drawings. The following embodiments are provided to more faithfully and completely explain the technical concept of the present disclosure to those skilled in the art to which the present disclosure pertains. Accordingly, the technical concept of the present disclosure is not necessarily limited to the following embodiments. The present disclosure should be understood to broadly include various equivalents, substitutions, modifications, etc., that embody the technical concept to be described below. The terms used in the following description are intended to describe specific embodiments more faithfully and completely in the same light as above. Accordingly, the terms used in the following description should not be interpreted to reduce, limit, or restrict the technical scope of the present disclosure. In the following description, terms such as "first," "second," etc., may be used to refer to specific components to distinguish them from other components. However, such terms are used for clarity of explanation, and the technical concept of the present disclosure should not be interpreted as being limited by such terms. In the following description, singular expressions may be interpreted to include the plural unless explicitly excluded by the context. Furthermore, in the following description, the expression "i