Abstract
In order to solve the accidents caused by aircraft icing, electro-impulse de-icing technology was studied through numerical simulation and experimental verification. In addition, this paper analyzed in detail the influence of the number, placement arrangement, and starting time of pulse coils on the de-icing effect, which plays a guidance role in the design and installation of the subsequent electro-impulse de-icing system. In an artificial climate chamber, the new de-icing criteria were obtained by tensile test, and the platform for the electro-impulse de-icing system was built. Replacing the skin with an aluminum plate, an electro-impulse de-icing system with a single coil was used. A three-dimensional skin-ice layer model was established by using Solidworks software. The finite element method was adapted. Through comparison between the de-icing prediction results and the test results in the natural environment, it was proven that the calculation process of de-icing prediction was correct, which laid a theoretical foundation for the selection of the number, placement arrangement, and starting time of the pulse coils. Finally, in this paper, by choosing the leading edge of NACA0012 wing as the research object, the influence of the number, placement arrangement, and starting time of pulse coils on the de-icing effect was analyzed. The results show that to get a better de-icing effect, the electro-impulse de-icing system with two impulse coils should be selected. The two coils were installed in the central position of the top and bottom surfaces of the leading edge, respectively. In addition, one of the impulse coils started working 1200 μs later than the other one.
Highlights
Since the earliest days of aeronautics, icing was found to be a crucial problem for aircraft flight.In-flight ice accretion occurs on the leading edge of an aircraft wing and usually covers only 2% of the wing chord, with the thickness of the ice layer being about a few centimeters
In the was the effectthe of the number, placement arrangement, andskin the was start-up time ofby pulse coils sameestablished; icing environment, adhesion between the ice layer and the measured a tensile on the de-icing ratio was analyzed, which provided a reference for the design and installation of the test, and the new de-icing criteria was obtained
Layer modelelectro-impulse was established;de-icing the effect of the number, placement arrangement, and the start-up time of pulse coils on the de-icing ratio was analyzed, which provided a reference for the design and installation of the subsequent electro-impulse de-icing system
Summary
Since the earliest days of aeronautics, icing was found to be a crucial problem for aircraft flight. Researchers havecoil studied the phenomenon ice layer peelingthan on the the EIDI skin systemthe is installed onathe aircraft thenumber positionof arrangement and start-up of the multiple under action of single coil[12,13,14], system.so. The environment, adhesion the ice layer andpulse the skin measured by the a tensile test, and the de-icing rangethe obtained bybetween experiments after each waswas compared with calculated result, newitde-icing criteria three-dimensional. In the was the effectthe of the number, placement arrangement, andskin the was start-up time ofby pulse coils sameestablished; icing environment, adhesion between the ice layer and the measured a tensile on the de-icing ratio was analyzed, which provided a reference for the design and installation of the test, and the new de-icing criteria was obtained. Layer modelelectro-impulse was established;de-icing the effect of the number, placement arrangement, and the start-up time of pulse coils on the de-icing ratio was analyzed, which provided a reference for the design and installation of the subsequent electro-impulse de-icing system
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