Abstract
Abstract Composite material, supercritical aircraft wings, and multi-electrical technology represent the future development trend of civil aircraft. However, domestically, the use of electrical heating for anti-icing on civil aircraft made of composite materials has not yet been implemented. In this study, focusing on the anti-icing technology of a specific aircraft wing leading edge, the article initially designs a metal thermal spraying circuit based on the thermal load distribution on the surface of the anti-icing area. Next, the research explores the resistive properties of the electrical heating film on the composite material wing leading edge, examining how the porosity and oxide content of the coating affect its resistivity. Finally, the metal thermal spray test is completed on the leading edge of the composite material aircraft wing. The test results indicate that the adherence and deposition rate of the coating on the leading edge of the aircraft wing are reliable. The resistivity of the heating film meets the performance specifications. The article develops an integrated metal thermal spray control method based on high-curvature composite materials, resulting in an electrical heating film with excellent shape adaptability, varying power density, and strong bonding, providing support for the domestic advancement of wing electrical heating anti-icing technology.
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