Transactions of Nanjing University of Aeronautics & Astronautics
Distribution Characteristics of De-icing Shear Stress on Thin Plate with Out-of-Plane Flexural Vibration Mode
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Abstract:
Ice protection technology based on the mechanical vibration of piezoelectric actuators is a new lightweight and energy-efficient de-icing method. It is gaining increasing interest for use in aviation to mitigate ice-related hazards. The investigation of mechanical vibration de-icing technology encompasses two primary aspects： interface shear stress induced by mechanical vibration and corresponding vibration modes. Finding proper vibration modes to generate enough interface shear stress for de-icing efficiency improvement is a challenge. The vibration mode of the plate is often described by the values m and n， while m and n are the number of anti-nodes in the transversal axis and longitudinal axis separately. This paper is to investigate the distribution characteristics of de-icing shear stress and related vibration parameters （m and n） under different structural vibration modes， so as to establish the structure mode selection criteria for the detail designing process of the mechanical vibration-based ice protection system （IPS）. The relationship between interface shear stress and vibration mode parameters under the single force excitation is established by theoretical analysis and simulation methods. A finite element model （FEM）， depicting an aluminum plate with an ice layer attached to its surface， is used to simulate the stress-strain levels of the whole structure. According to the simulation outcomes and experimental verification， the distribution characteristics of de-icing parameters are analyzed. The selection of the initial de-icing modes based on the characteristics of m and n values of the flexural vibration modes is emphasized.
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Project Supported:
This work was funded by the National Natural Science Foundation of China （Nos.11832012， 12227802） and the Fundamental Research Funds for the Central Universities （No.3082020NP2020402）. The authors gratefully acknowledge the support of the State Key Laboratory of Mechanics and Control for Aerospace Structures， Nanjing University of Aeronautics and Astronautics because many of the vibration mode measurements presented in this paper were performed in this lab.
Clc Number:
V244.15
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