Piezo-actuated Vibratory Deicing System For TC4/PEEK/C_f Laminate Structures Based On Dynamic Behaviors

Due to excellent resistance to impact and fatigue,alternating metal and composite layering is a promising technique for application in exposed aircraft structures,especially in leading edge structure.While it is inevitable for these windward structures to face inflight icing problems,which will degrade aerodynamic behaviours and even cause fatal disasters.Accordingly,this paper has studied the feasibility and optimization design of piezo-actuated low-energy-consuming deicing method on TC4/PEEK/C_f laminate structures.Low-order dynamic behaviours of the simple flat TC4/PEEK/C_f laminate structure was firstly studied.In paticular,first 10 order eigenfrequencys,natural modes and modal damping ratios of this flat laminate structure were extracted through PSV experimental measurement,theoretical analysis and finite element method.Base on the finite element model established in ABAQUS,with average error only 3.22%,eigenfrequency of the flat TC4/PEEK/C_f laminate structure will chage with variation of fiber orientation,while the detailed trend depends on the particular mode shape.Here,the small-sized freezer ice placed in the center is chosen to be the target of deicing for this flat TC4/PEEK/C_f laminate structure.After determination of suitable natural modes and actuators layout scheme,the feasibility of piezo-actuated deicing method was verified both by deicng experiments in freezer and steady state dynamic analysis in ABAQUS.The required minimum actuating voltage behaved similarly in experiment and simulation,with instantly peeling off in experiment and average interfacial shear stress component achieving 0.42 MPa in simulation as criterion for effective deicing.The maximum error is about 20%,mainly attributed to initial crack in attached interface,over conservatism of criteria in simulation and effect of strain or stress rate.Also,results showed that,for the flat TC4/PEEK/C_f laminate structure with different fiber arrangement,optimal deicing mode can be obtained when minimum antinodes exist in the direction of maximum equivalent stiffness of the structure.Finally,the feasibility was also verified on a NACA0012 leading edge structure made by TC4/PEEK/C_f laminates with long freezer ice strip accreted on the tip.Based on the conclusion on a flat structure,the deicing scheme P2-Mode2(excited on 2^nd mode with actuators parallel to the straight edge in the middle)is the optimal plan both for TC4/PEEK/0?_f and TC4/PEEK/90?_f leading edge structures with minimum driving voltages are 203 V and 208 V,respectively.And ice debonding mothod for each deicing scheme depends on the position of maximum interfacial shear stress.Furthermore,the power consumption density was calculated at1.780 kW/m² only,which shows a 64.4%drop compared with the electro-thermal deicing method based on graphene.And the power required by this piezo-actuated vibratory system can be further reduced with just seconds of working time.This paper provides experimental and theoretical basic research for engineering application and optimization design for piezo-actuated deicing method on composite structures.