Ultrasonic detection of melting and debonding of interface between skin and ice layer

Yuan WANG; Yang ZHANG; Yan WANG; Chengxiang ZHU; Chunling ZHU

doi:10.1051/jnwpu/20254320241

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Volume 43 / No 2 (April 2025)

JNWPU, 43 2 (2025) 241-249

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Issue		JNWPU Volume 43, Number 2, April 2025


Page(s)		241 - 249
DOI		https://doi.org/10.1051/jnwpu/20254320241
Published online		04 June 2025

JNWPU 2025, 43(2): 241–249

Ultrasonic detection of melting and debonding of interface between skin and ice layer

蒙皮-冰层界面融化脱粘超声探测

Yuan WANG (王渊), Yang ZHANG (张杨), Yan WANG (王岩), Chengxiang ZHU (朱程香) and Chunling ZHU (朱春玲)

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received: 18 April 2024

Abstract

In order to solve the problem that it is difficult to detect the local ice layer debonding when the thermal protection system is working, an on-line ultrasonic detection method for the melting degree of interface between skin and ice layer based on the theory of ultrasonic transmission in multi-layer media was studied. A multi-layer medium acoustic model including skin, water film, ice water transition layer, ice layer and air layer is constructed. Ultrasonic pulse waves with different center frequencies are used as excitation sources, and the echo signals of multi-layer medium interface are obtained by using the numerical calculation. The ultrasonic signal processing algorithm for ice melting and debonding measurement is developed. The original echo signal is processed and the characteristic parameters of the echo signal of interface between skin and ice layer are extracted. The ultrasonic reflection coefficient of interface between skin and ice layer is proposed to evaluate the degree of ice melting. The ultrasonic ice detection system was built, and the low-temperature ultrasonic sensor was designed and fabricated. The ability of the system to measure the degree of ice melting under the action of electric heating was verified in the low-temperature environment. The ultrasonic ice detection system was built, and the low-temperature ultrasonic sensor was designed and fabricated. The ability of the system to measure the degree of ice melting under the action of electric heating was verified in the low-temperature environment. The theoretical results show that when the ice on the skin melts and produces a thin water film, the degree of ice melting can be reflected by the change of ultrasonic reflection coefficient at the skin-attachment interface. In this paper, the ultrasonic reflection coefficient more than 0.8 is used as the criterion of ice melting. With the increasing of center frequency of the ultrasonic signal, the thinner water film can be identified. The identification thickness of the water film corresponding to 7.5 MHz center frequency signal is 10 μm. The experimental results show that under the conditions of clear ice, mixed ice and frost ice, the ultrasonic detection system can out-put the ice layer debonding signal at the initial stage of electric heating. The propagation characteristics of ultrasonic pulse wave of interface between skin and ice layer in the thermal protection are preliminarily explored. The present method for detecting the degree of ice melting is expected to further reduce the energy consumption of thermal protection.

摘要

为解决热防护系统工作时局部冰层脱粘难以在线探测的问题, 开展了基于多层介质内超声传递理论的蒙皮-冰层界面融化程度在线超声探测方法研究。构建了包含蒙皮、水膜、冰水过渡层、冰层和空气层的多层介质声学模型, 采用不同中心频率的超声脉冲波作为激励源, 通过数值计算获得多层介质界面回波信号; 发展用于冰层融化脱粘测量的超声信号处理算法, 对原始回波信号进行处理并提取蒙皮-冰层界面回波信号特征参数, 提出采用蒙皮-冰层界面超声反射系数评估冰层融化程度; 搭建超声结冰探测系统, 设计并制备耐低温超声传感器, 在低温环境验证电加热作用下系统对冰层融化程度的测量能力。理论研究结果表明: 当蒙皮表面冰层融化产生薄水膜时, 可通过蒙皮-附着物界面超声反射系数变化反映冰层融化程度; 将超声反射系数大于0.8作为冰层融化判据, 随超声信号中心频率增大, 可对更薄的水膜进行识别, 7.5 MHz中心频率信号对应的水膜识别厚度为10 μm。实验研究结果表明, 在明冰、混合冰和霜冰结冰气象条件下, 超声探测系统均可在电加热工作初期输出冰层脱粘信号。初步探索了热防护作用过程中蒙皮-冰层界面超声脉冲波传播特性, 提出的冰融化程度探测方法有望进一步降低热防护能耗。

Key words: ice layer debonding / ice detection / online ultrasonic detection / ultrasonic pulse wave / reflection coefficient / melting degree

关键字 : 冰层脱粘 / 结冰探测 / 在线超声探测 / 超声脉冲波 / 反射系数 / 融化程度

This is an Open Access article distributed under the terms of the Creative Commons Attribution License (https://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

飞机在穿越含有过冷水滴的云层时，机翼前缘形成的积冰会造成升力下降、阻力增大，严重危害飞行安全[1–2]。现代飞机普遍装备了结冰防护系统(ice protection system, IPS)，可有效降低由结冰造成的致命事故[3–4]。热防/除冰系统在现代飞行器上应用最为广泛，热源包括发动机引气和电加热2种[5–6]。其中，通过机载电源供电的电加热防/除冰系统具有结构简单、体积和质量小、能耗低、升温速度快、可设计性强和可靠性高等优点，是近年来结冰防护领域研究的热点和焦点[7–8]。低碳、低能耗全电飞机是全球航空器发展趋势，如何合理利用有限的机载电源保证飞机在结冰环境中安全飞行是全电飞机研究热点和重点[9]。研究表明在机翼前缘结冰区域内采用分区加热的方式可有效降低IPS能耗[10–11]。现有热防护分区策略大多基于数值计算结果进行设计，由于冰物性、结冰气象参数多采用经验预设值，各分区防护热载荷偏离实际需求，造成能源的浪费或无法达到预期防护效果[12]。迫切需要发展一种能够原位探测冰层融化脱粘程度的技术，通过实时反馈的冰层融化程度信息控制IPS启停，降低能耗。

机载结冰探测系统(flight icing detection systems, FIDS)通过间接测量光、电、声等物理量随结冰过程变化的方式实现冰层厚度测量和冰类型识别[13–17]。其中，超声脉冲回波(ultrasonic pulse echo, UPE)技术配备的高频传感器具有尺寸小、保形安装在蒙皮内表面的优势[18]。该技术于1985年首次用于飞机结冰探测，通过获取冰内超声脉冲波渡越时间可实现飞机表面结冰厚度原位动态探测[19–20]。同时，高频超声脉冲回波信号的时频特征参数包含了丰富的冰层形态、孔隙分布和附着强度信息，已被用于定性识别明冰和霜冰[21–23]。2024年，张杨等[24]认为在热冲击作用下蒙皮表面冰层由于受热不均会局部脱粘，通过蒙皮-冰界面超声反射系数实现冰层脱粘程度评估。然而，冰层脱粘通常在采用机械除冰或大热流密度电加热除冰作用时发生，低能耗电热除冰系统工作时冰层会逐渐融化脱粘[25–26]。同时，由于电加热作用时冰内温度梯度会导致声阻抗沿冰厚度方向梯度分布，超声波在蒙皮、水膜、冰水过渡层、冰层和空气多层介质内传播机理尚不明确[27]。因此，有必要开展多层介质内超声脉冲波传播特性研究，揭示电加热作用时冰层融化程度对蒙皮-冰层界面超声回波信号影响规律。

本文开展了电加热作用时铝板表面融冰过程超声传播特性研究，建立了超声脉冲波在多层介质内传播声学模型，采用数值计算的方法分析了过渡层厚度、水膜厚度变化对不同中心频率超声信号影响规律，发展了用于冰层融化程度评估的超声信号处理方法，通过地面冷环境实验验证了UPE技术对于冰层融化程度在线测量的能力，为后续研制低能耗电热IPS提供了理论参考。

1 蒙皮-冰层融化程度超声探测原理

由铝制蒙皮、水膜、过渡层、冰层和空气层组成的多层介质结构如图 1所示，超声传感器布置在铝板下表面。电加热作用时，蒙皮-冰层界面处的冰层会逐渐融化形成由冰水混合物组成的过渡层，继续加热会在蒙皮和冰层界面形成薄水膜，过渡层位于水膜与冰层之间[28–29]。采用UPE技术进行冰层融化脱粘探测时需要考虑过渡层厚度和水膜厚度变化对超声脉冲回波信号的影响，建立蒙皮-附着物界面回波信号特征参数与融化脱粘程度关系。

图1

电加热作用多层结构示意图

1.1 超声波在异质介质界面反射和透射

在异质介质交界面由于2种材料压缩性不一致，一部分声波会透过界面继续行进，一部分声波会在界面处反射[30]。探测时超声波从介质Ⅰ(飞机蒙皮)垂直入射到介质Ⅱ(冰层)，如图 2所示，x=0处为2种介质分界面，Z_A和Z_I分别为蒙皮和冰层的特性声阻抗，可由材料密度ρ和纵波声速c相乘得到，单位为10⁶ N·s/m³。

图2

2种不同材料界面超声反射/透射示意图

根据一维波动方程可知介质Ⅰ中声波声场由沿x轴正向的入射波和沿x轴负向的反射波组成，介质Ⅱ内超声波主要来源于2层介质界面处的透射波, 两介质内声场表达式为[31]：

式中：p_ia和p_ra分别为界面处入射波和反射波声压幅值；p_ta为透射波声压幅值；k₁和k₂为介质Ⅰ和介质Ⅱ内超声波波数，波数也可通过介质内声波波长λ计算，即k=2π /λ。

对于两厚度无限大的介质，超声波在2种物质交界面传递时必须满足2个边界条件：界面两边压力连续；垂直于界面的质点速度分量连续。经过推导，可获得声波在2种媒质交界面处声压反射系数R_A-I和透射系数T_A-I[31]，如(2)式所示。

对于由蒙皮材料与冰层组成的2层结构，界面超声波反射系数和透射系数仅与材料声阻抗相关。蒙皮采用航空铝材时声阻抗约16.9×10⁶ N·s/m³，冰层声阻抗受温度和冰密度影响在一定范围内波动，约为3.4×10⁶ N·s/m³。当超声波从铝制蒙皮入射到冰层内时，蒙皮与冰界面超声波反射系数为R_A-I=-0.665，负号表示反射波与入射波声压相位相差180°。当蒙皮表面为水膜时，反射系数为R_A-W=-0.85，理论上可通过蒙皮-冰/水界面超声反射系数定性识别表面附着物。

1.2 超声波在多层介质内传播模型

采用UPE技术进行冰层融化脱粘探测需考虑加热初期界面冰层逐渐融化形成的冰水过渡层和薄水膜对超声回波信号影响。

电加热开启后首先在蒙皮与冰界面形成由冰水混合物组成的过渡层，过渡层密度与声速沿厚度方向梯度变化。过渡层内由固相树枝状冰晶和液态水组成，在微观尺度上表现出各向异性特征[28]。在计算时，考虑了过渡层内固体相(冰)纵向体积占比对超声回波信号的影响。由于过渡层内固体相体积占比沿水层到冰层方向梯度连续增大，为简化模型，忽略过渡层中的树枝状结构，采用层状功能梯度材料模型描述过渡层内材料属性[27]，如图 3所示。

图3

冰水间过渡层功能材料梯度模型

过渡层被分为n个子层，与蒙皮相邻的子层编号为1，与冰层相邻的子层编号为n，单个子层厚度为1 μm，由于过渡层厚度远小于声波波长，超声波在子层间界面全透射。蒙皮上表面与过渡层之间的界面编号为0，过渡层与冰层之间的界面编号为m。过渡层中材料的性质呈多层梯度分布。子层的材料属性M(i)可以用(3)式表达。

式中：M_I和M_W分别为冰层和水层的物理参数，可以是密度、纵波声速或声阻抗；V_I(i)和V_W(i)分别为编号i的子层中冰和水的体积占比。编号为n的子层温度与冰层一致，因此物理属性与冰层一致。子层1内冰体积分数V_I(1)随温度升高逐渐减小，当蒙皮与过渡层界面温度达到0 ℃时，蒙皮和过渡层之间产生水膜，按照最小飞机结冰密度610 kg/m³计算子层1内固体相占比为V_I(1)=0.67[29]。

电加热持续作用，蒙皮与过渡层之间会逐渐形成微米级薄水膜。当存在薄水膜时，透射进入水膜层的声波会在蒙皮-水膜与水膜-过渡层界面多次反射，如图 4所示。x=0处传感器接收到回波信号实际是蒙皮-水膜界面一次反射波W₀和来自水膜-蒙皮界面多次透射波W₁, W₂, …, W_m叠加形成。

图4

薄水膜存在时超声波传递示意图

本文数值计算采用幅值为1的Ricker脉冲波作为激励源，f_c的脉冲波f(t)可用(4)式表达。

假设冰层厚度远大于超声脉冲波波长，超声传感器布置在x=0处，接收到的蒙皮和水膜界面一次反射超声脉冲波表达式为

式中: H_A为蒙皮厚度; c_A为铝制蒙皮内纵波声速。

水膜内多次反射后透射入蒙皮到x=0处的超声脉冲波可用(6)式表达。

式中: H_W为水膜厚度; c_W为水膜内纵波声速; R_W-T为水膜-过渡层界面反射系数; T′_AW=T_A-W·T_W-A为蒙皮-水膜界面超声波往复透射系数, i=1, 2, …, m为超声波反射次数。

冰层厚度远大于水膜和过渡层厚度，x=0处传感器仅接收到冰层-空气界面一次超声回波信号，其表达式为

式中: R_I-a为冰层-空气界面超声反射系数，约等于1；H_T, H_I分别为过渡层和冰层厚度; c_T, c_I分别为过渡层和冰内纵波声速; T′_WT=T_W-T·T_T-W为水膜-过渡层界面超声波往复透射系数。

将(5)~(7)式进行求和可得到x=0处接收到的超声脉冲回波信号W_r，如(8)式所示。

2 数值计算

2.1 数值计算参数设置

采用MatLab软件对多层介质内平面超声脉冲波进行求解。计算时设置激励超声脉冲波中心频率在5~15 MHz变化，间隔2.5 MHz。设置铝制蒙皮厚度为2 mm，初始冰层厚度为1 mm。假设电加热开启后，先在蒙皮与冰层逐渐形成过渡层。过渡层厚度由上下表面温差决定，飞机结冰过程中，过渡层上下表面温度差范围5 ℃≤ΔT≤20 ℃，厚度约60 ~ 80 μm[32]。计算时设置过渡层厚度从0~70 μm变化，间隔10 μm。当过渡层厚度达到70 μm后保持厚度不变，在蒙皮与过渡层之间逐渐形成水膜。由于水膜厚度大于100 μm时，蒙皮-水膜界面回波幅值均趋于稳定，因此设置水膜厚度从0~100 μm变化，间隔10 μm。多层介质材料物性参数如表 1所示。

表1

多层介质材料参数

2.2 过渡层对超声回波信号影响规律

采用中心频率5 MHz的超声脉冲激励源时，随着过渡层厚度增长，来自蒙皮上表面和冰层上表面超声回波信号包络线如图 5所示，其中第1个回波为来自蒙皮-过渡层界面的一次回波信号，第2个回波为来自冰层-空气界面的一次回波信号。无过渡层时蒙皮与冰层界面声波反射系数R_A-I=0.665，当过渡层厚度逐渐增大时，蒙皮与冰层界面回波幅值逐渐增大，主要是由于该界面处过渡层声阻抗低于冰层声阻抗。

图5

过渡层厚度增长时超声回波信号

采用不同中心频率超声脉冲信号作为激励脉冲信号，通过理论计算获得多层介质界面回波信号。计算蒙皮-过渡层界面声波反射系数随过渡层厚度增长变化曲线，如图 6所示。当过渡层厚度达到70 μm时蒙皮上表面声波反射系数最大值小于0.75。由于过渡层本质是冰和水的混合物，因此过渡层存在时冰层尚未完全脱粘失效。当过渡层厚度达到一定值时蒙皮上表面开始出现水膜，水膜的声阻抗小于过渡层，蒙皮上表面声波反射系数会进一步增大。

图6

界面声波反射系数随过渡层厚度增长变化曲线

2.3 水膜厚度对超声回波信号影响规律

当蒙皮与过渡层之间水膜厚度从0~100 μm逐渐增大时，超声回波信号包络线如图 7所示，其中第1个回波为来自蒙皮-水膜界面的一次回波信号，第2个回波为来自冰层-空气界面的一次回波信号。蒙皮-水膜界面超声波反射系数随水膜厚度变化规律如图 8所示。水膜厚度增长初期界面反射系数迅速增大之后趋于稳定。

图7

水膜厚度增长时超声回波信号

图8

超声波反射系数随水膜厚度增长变化规律

根据上述理论研究结果，设置反射系数阈值R_A-I=0.8用于识别冰层融化脱粘。超声脉冲信号中心频率与界面融化产生的水膜厚度关系如图 9所示。拟合中心频率与冰层脱粘检出限，其关系如(9)式所示。

图9

水膜检出限随激励信号中心频率变化规律

式中, S_IM为界面水膜识别灵敏度。

理论信号处理结果表明UPE技术对于冰层融化膜粘识别灵敏度高，可用于蒙皮表面冰层融化测量。理论研究结果表明UPE技术对于冰层融化脱粘识别灵敏度高，由于7.5 MHz中心频率传感器可对0.3 mm以上冰层进行准确测量，满足航空航天标准[27, 33]。后续采用7.5 MHz传感器进行冰层融化脱粘实验验证。

3 实验研究

3.1 超声探测系统搭建

电加热作用界面融化超声探测实验装置如图 10所示，图中自下而上分别为保温层、电加热层、铝板和冰层。中心频率7.5 MHz的超声传感器粘接在铝板中心位置；直径15 cm的圆形合金电加热膜粘接在铝板下表面，加热膜厚度为0.3 mm，电阻为70 Ω；保温层采用聚酰亚胺泡沫，厚度为10 mm，通过双面胶粘接在电加热层下表面；矩形铝板厚度为2 mm，边长20 cm；采用标准模具通过喷雾结冰制备冰样本，模具长宽高分别为50 mm×50 mm×3 mm。超声探测系统每秒采集8组回波数据并进行处理，温度采样频率为50 Hz；电源输出电压为78 V，电加热功率密度为0.5 W/cm²，加热电源通过布置在铝板-冰界面的温度传感器控制启停，当界面温度达到5 ℃时电源关闭，小于5 ℃时电源开启。

图10

电加热作用界面融化超声探测实验装置示意图

3.2 实验参数选取

为了研究超声结冰探测系统对于不同冰型界面相变的测量能力，在铝板表面通过间接喷雾形式制备3个典型的冰型(明冰、混合冰和霜冰)，3组实验状态参数如表 2所示。冷环境箱内温度低于铝板-冰界面温度，温度采集以铝板-冰界面温度为准。喷雾结冰时受冻结速度影响，制备不同冰型样本时2次喷雾间隔时间不同，明冰喷雾间隔时间大于混合冰和霜冰，以保证单次喷雾后冰层能完全冻结。当冰层和铝板界面温度达到预设值时开启超声结冰探测系统进行数据采集。

表2

实验状态参数

3.3 实验结果分析

3组实验超声系统采集到的铝板-冰界面温度变化曲线如图 11所示，结冰环境温度越高，除冰时界面温度越早达到0 ℃。

图11

电加热作用时铝板-冰界面温度变化曲线

实验时超声传感器-铝板界面声波透射和反射系数为定值，不影响蒙皮-附着物界面声波反射系数。仅考虑蒙皮-附着物界面声波反射系数，其变化量与蒙皮表面附着物厚度和物理参数相关。电加热作用时，超声结冰探测系统获取的铝板-附着物界面回波反射系数变化曲线如图 12所示。电加热尚未开启时，铝板-冰界面回波反射系数约等于0.67。当铝板-冰界面持续升温时，反射系数会在冰层融化瞬间达到0.8以上，此时判断蒙皮表面冰层融化。可以看出3组工况反射系数大于0.8之后会持续增大，达到最大值后减小并趋于稳定，该规律也与理论计算结果一致。

图12

电加热作用时铝板-冰界面反射系数变化曲线

飞机分区加热除冰时，局部区域冰层融化后通常会因为与相邻区域冰层连为一体，在强对流作用下不会随气流脱落。采用超声探测局部区域冰层是否融化可进一步提高分区电加热除冰效率，在提高系统可靠性的同时降低能耗。

4 结论

本文对超声脉冲波在多层介质内传播过程进行了数值建模计算，通过实验验证了UPE技术探测蒙皮-冰层界面融化可行性，得出以下结论：

1) 电加热作用初期，蒙皮-冰层界面形成的冰水混合物过渡层会导致蒙皮-冰界面超声反射系数增大，最大值小于0.75。

2) 持续加热，蒙皮表面冰层融化形成薄水膜，蒙皮-附着物界面超声反射系数会迅速达到0.8以上。通过界面反射系数可有效识别冰层融化，可根据局部水膜融化判断探测区域冰层脱粘。

3) 采用中心频率5~15 MHz超声脉冲信号时，冰层融化检出限与超声波信号中心频率负相关，中心频率7.5 MHz超声传感器可识别厚度10 μm以上的水膜。

4) 实验研究结果表明，对于明冰、混合冰和霜冰，蒙皮-附着物界面超声反射系数均在电加热作用初期达到0.8以上，其反射系数随加热时间变化规律与理论计算结果一致，采用7.5 MHz中心频率传感器可有效识别铝板表面不同类型冰层融化。

综上，本文提出的基于UPE技术的蒙皮表面冰层融化脱粘测量方法有效，后续工作准备将超声测量方法与电热控制系统深入结合，有望进一步降低除冰能耗。

References

CAO Yihua, TAN Wenyuan, WU Zhenlong. Aircraft icing: an ongoing threat to aviation safety[J]. Aerospace Science and Technology, 2018, 75(2): 353385 [Google Scholar]
LI S, PAOLI R. Aircraft icing severity evaluation[J]. Encyclopedia, 2022, 2(1): 5669 [Article] [Google Scholar]
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LI X, FAIRUZ I R, SYARIL A M Aet al.. An overview of civil aviation accidents and risk analysis[J]. Proceedings of Aerospace Society Malaysia, 2023, 1(1): 53–62 [Google Scholar]
KHALIL E E, SAID E, ALSAHEH A, et al. Effect of hot air jet arrangement from a piccolo tube in aircraft wing anti-icing system[C]//Proceedings of the AIAA Propulsion and Energy 2020 Forum, 2020: 1-13 [Google Scholar]
ZHAO Zehui, CHEN Huawei, LIU Xiaolinet al.. The development of electric heating coating with temperature controlling capability for anti-icing/de-icing[J]. Cold Regions Science and Technology, 2021, 184(11): 103234 [Google Scholar]
WANG Ran, XU Zhen, ZHUANG Jihan, et al. Highly stretchable graphene fibers with ultrafast electrothermal response for low-voltage wearable heaters[J]. Advanced Electronic Materials, 2017, 3(2): 1–7 [Google Scholar]
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SHEN Yizhou, HE Junjian, WU Bingquanet al.. Research progress of active passive coupling anti icing/de-icing technology and energy consumption control[J]. Science Technology and Engineering, 2023(35): 1490514915 (in Chinese) [Google Scholar]
HANN R, ENACHE A, NIELSEN M Cet al.. Experimental heat loads for electrothermal anti-icing and de-icing on UAVs[J]. Aerospace, 2021, 8(3): 115 [Google Scholar]
ZANON A, DE G M. Design of the thermoelectric ice protection system for a tiltrotor application[J]. Journal of Aircraft, 2022, 59(5): 1337–1350 [Article] [Google Scholar]
DING Liang, CHANG Shinan, YI Xian, et al. Coupled thermo-mechanical analysis of stresses generated in impact ice during in-flight de-icing[J]. Applied Thermal Engineering, 2020, 181(3): 111 [Google Scholar]
CALISKAN Fikret, HAJIYEV Chingiz. A review of in-flight detection and identification of aircraft icing and reconfigurable control[J]. Progress in Aerospace Sciences, 2013, 60(1): 12–34 [Google Scholar]
GE Junfeng, CHENG Xin, GUI Kang, et al.. Oblique end face coupling optical fiber sensor for point fuel level measurement[J]. Sensors and Actuators A: Physical, 2019, 297: 111505 [Article] [Google Scholar]
ZHENG Dongsheng, LI Ziyin, DU Zhenyu, et al. Design of capacitance and impedance dual-parameters planar electrode sensor for thin ice detection of aircraft wings[J]. IEEE Sensors Journal, 2022, 22(11): 11006–11015 [Google Scholar]
RIEMAN L, GUK E, KIM T, et al. Development of a novel multi-channel thermocouple array sensor for in-situ monitoring of ice accretion[J]. Sensors, 2020, 20(8): 2165–2183 [Google Scholar]
MENDIG C, RIEMENSCHNEIDER J, MONNER H P, et al. Ice detection by ultrasonic guided waves[J]. CEAS Aeronautical Journal, 2018, 9(3): 405–415 [Google Scholar]
LIU Yang, CHEN Wenli, BOND L J, et al. An experimental study on the characteristics of wind-driven surface water film flows by using a multi-transducer ultrasonic pulse-echo technique[J]. Physics of Fluids, 2017, 29(1): 012101–012114 [Google Scholar]
HANSMAN J R, KIRBY Mark. Measurement of ice accretion using ultrasonic pulse-echo techniques[J]. Journal of Aircraft, 1985, 22(6): 530–535 [Google Scholar]
HANSMAN J R, KIRBY Mark, LICHTENFELTS Fred. Ultrasonic techniques for aircraft ice accretion measurement[C]//Proceedings of the Sensor and Measurements Techniques for Aeronautical Applications, Atlanta, 1988: 1-12 [Google Scholar]
LIU Yang, BOND L J, HU Hui. Ultrasonic-attenuation-based technique for ice characterization pertinent to aircraft icing phenomena[J]. AIAA Journal, 2017, 55(5): 1602–1609 [Google Scholar]
OMID Y, WHITE R D, YASAMIN K, et al. The effect of pore size and density on ultrasonic attenuation in porous structures with mono-disperse random pore distribution: a two-dimensional in-silico study[J]. The Journal of the Acoustical Society of America, 2018, 144(2): 709–719 [Google Scholar]
GUI Kang, ZHANG Yabo, GE Junfeng, et al. Ice porosity measurement utilizing dynamic wavelet fingerprint technology[J]. Transactions of Nanjing University of Aeronautics & Astronautics, 2023, 40(suppl. 1): 118–128 [Google Scholar]
ZHANG Yang, WANG Yuan, WANG Yanet al.. Ultrasonic echo detection of local debonding of aircraft icing[J]. Journal of Vibration, Measurement & Diagnosis, 2024, 44(1): 166–171 (in Chinese) [Google Scholar]
TIAN Tian, WANG Yuan, TAO Mingjieet al.. Experimental study on electrothermal deicing of graphene Composites[J]. Science Technology and Engineering, 2019, 19(28): 390–395 (in Chinese) [Google Scholar]
JIANG Xingliang, WANG Yangyang. Studies on the electro-impulse de-icing system of aircraft[J]. Aerospace, 2019, 6(1): 67–82 [Google Scholar]
WANG Y, WANG Y, LI W, et al. Study on freezing characteristics of the surface water film over glaze ice by using an ultrasonic pulse-echo technique[J]. Ultrasonics, 2022, 126(12): 106804 [CrossRef] [PubMed] [Google Scholar]
LI Xin, BAI Junqiang, HUA Jun, et al. A spongy icing model for aircraft icing[J]. Chinese Journal of Aeronautics, 2014, 27(1): 40–51 [Google Scholar]
JANJUA Z A, TURNBULL B, HIBBERD Set al.. Mixed ice accretion on aircraft wings[J]. Physics of Fluids, 2018, 30(2): 027101 [Google Scholar]
FOLDS D L, LOGGINS C D. Transmission and reflection of ultrasonic waves in layered media[J]. The Journal of the Acoustical Society of America, 1977, 62(5): 1102–1109 [Google Scholar]
DU Gonghuan, ZHU Zhemin, GONG Xiufen. Fundamentals of acoustics[M]. NanJing: Nanjing University Press, 2001 (in Chinese) [Google Scholar]
TIRMIZI S H, GILL W N. Effect of natural convection on growth velocity and morphology of dendritic ice crystals[J]. Journal of Crystal Growth, 1987, 85(3): 488–502 [Google Scholar]
Committee AC-9C Aircraft Icing Technology. Minimum operational performance specification for inflight icing detection systems[S]. SAE Standard AS5498, 2009 [Google Scholar]

All Tables

多层介质材料参数

实验状态参数

All Figures

	图1 电加热作用多层结构示意图
In the text

	图2 2种不同材料界面超声反射/透射示意图
In the text

	图3 冰水间过渡层功能材料梯度模型
In the text

	图4 薄水膜存在时超声波传递示意图
In the text

	图5 过渡层厚度增长时超声回波信号
In the text

	图6 界面声波反射系数随过渡层厚度增长变化曲线
In the text

	图7 水膜厚度增长时超声回波信号
In the text

	图8 超声波反射系数随水膜厚度增长变化规律
In the text

	图9 水膜检出限随激励信号中心频率变化规律
In the text

	图10 电加热作用界面融化超声探测实验装置示意图
In the text

	图11 电加热作用时铝板-冰界面温度变化曲线
In the text

	图12 电加热作用时铝板-冰界面反射系数变化曲线
In the text

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[1] CAO Yihua, TAN Wenyuan, WU Zhenlong. Aircraft icing: an ongoing threat to aviation safety[J]. Aerospace Science and Technology, 2018, 75(2): 353385 [Google Scholar]

[2] LI S, PAOLI R. Aircraft icing severity evaluation[J]. Encyclopedia, 2022, 2(1): 5669 [Article] [Google Scholar]

[3] LEE J W, CHO M Y, KIM Y Het al.. Current status and prospect of aircraft ice protection systems[J]. Journal of the Korean Society for Aeronautical Space Sciences, 2020, 48(11): 911–925 [Google Scholar]

[4] LI X, FAIRUZ I R, SYARIL A M Aet al.. An overview of civil aviation accidents and risk analysis[J]. Proceedings of Aerospace Society Malaysia, 2023, 1(1): 53–62 [Google Scholar]

[5] KHALIL E E, SAID E, ALSAHEH A, et al. Effect of hot air jet arrangement from a piccolo tube in aircraft wing anti-icing system[C]//Proceedings of the AIAA Propulsion and Energy 2020 Forum, 2020: 1-13 [Google Scholar]

[6] ZHAO Zehui, CHEN Huawei, LIU Xiaolinet al.. The development of electric heating coating with temperature controlling capability for anti-icing/de-icing[J]. Cold Regions Science and Technology, 2021, 184(11): 103234 [Google Scholar]

[7] WANG Ran, XU Zhen, ZHUANG Jihan, et al. Highly stretchable graphene fibers with ultrafast electrothermal response for low-voltage wearable heaters[J]. Advanced Electronic Materials, 2017, 3(2): 1–7 [Google Scholar]

[8] TANG Chao, XIE Wenjun, YUAN Peiyu, et al. Development and verification of a conformal electrothermal deicing functional structure for leading edge of airfoil[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(12): 427872 (in Chinese) [Google Scholar]

[9] SHEN Yizhou, HE Junjian, WU Bingquanet al.. Research progress of active passive coupling anti icing/de-icing technology and energy consumption control[J]. Science Technology and Engineering, 2023(35): 1490514915 (in Chinese) [Google Scholar]

[10] HANN R, ENACHE A, NIELSEN M Cet al.. Experimental heat loads for electrothermal anti-icing and de-icing on UAVs[J]. Aerospace, 2021, 8(3): 115 [Google Scholar]

[11] ZANON A, DE G M. Design of the thermoelectric ice protection system for a tiltrotor application[J]. Journal of Aircraft, 2022, 59(5): 1337–1350 [Article] [Google Scholar]

[12] DING Liang, CHANG Shinan, YI Xian, et al. Coupled thermo-mechanical analysis of stresses generated in impact ice during in-flight de-icing[J]. Applied Thermal Engineering, 2020, 181(3): 111 [Google Scholar]

[13] CALISKAN Fikret, HAJIYEV Chingiz. A review of in-flight detection and identification of aircraft icing and reconfigurable control[J]. Progress in Aerospace Sciences, 2013, 60(1): 12–34 [Google Scholar]

[14] GE Junfeng, CHENG Xin, GUI Kang, et al.. Oblique end face coupling optical fiber sensor for point fuel level measurement[J]. Sensors and Actuators A: Physical, 2019, 297: 111505 [Article] [Google Scholar]

[15] ZHENG Dongsheng, LI Ziyin, DU Zhenyu, et al. Design of capacitance and impedance dual-parameters planar electrode sensor for thin ice detection of aircraft wings[J]. IEEE Sensors Journal, 2022, 22(11): 11006–11015 [Google Scholar]

[16] RIEMAN L, GUK E, KIM T, et al. Development of a novel multi-channel thermocouple array sensor for in-situ monitoring of ice accretion[J]. Sensors, 2020, 20(8): 2165–2183 [Google Scholar]

[17] MENDIG C, RIEMENSCHNEIDER J, MONNER H P, et al. Ice detection by ultrasonic guided waves[J]. CEAS Aeronautical Journal, 2018, 9(3): 405–415 [Google Scholar]

[18] LIU Yang, CHEN Wenli, BOND L J, et al. An experimental study on the characteristics of wind-driven surface water film flows by using a multi-transducer ultrasonic pulse-echo technique[J]. Physics of Fluids, 2017, 29(1): 012101–012114 [Google Scholar]

[19] HANSMAN J R, KIRBY Mark. Measurement of ice accretion using ultrasonic pulse-echo techniques[J]. Journal of Aircraft, 1985, 22(6): 530–535 [Google Scholar]

[20] HANSMAN J R, KIRBY Mark, LICHTENFELTS Fred. Ultrasonic techniques for aircraft ice accretion measurement[C]//Proceedings of the Sensor and Measurements Techniques for Aeronautical Applications, Atlanta, 1988: 1-12 [Google Scholar]

[21] LIU Yang, BOND L J, HU Hui. Ultrasonic-attenuation-based technique for ice characterization pertinent to aircraft icing phenomena[J]. AIAA Journal, 2017, 55(5): 1602–1609 [Google Scholar]

[22] OMID Y, WHITE R D, YASAMIN K, et al. The effect of pore size and density on ultrasonic attenuation in porous structures with mono-disperse random pore distribution: a two-dimensional in-silico study[J]. The Journal of the Acoustical Society of America, 2018, 144(2): 709–719 [Google Scholar]

[23] GUI Kang, ZHANG Yabo, GE Junfeng, et al. Ice porosity measurement utilizing dynamic wavelet fingerprint technology[J]. Transactions of Nanjing University of Aeronautics & Astronautics, 2023, 40(suppl. 1): 118–128 [Google Scholar]

[24] ZHANG Yang, WANG Yuan, WANG Yanet al.. Ultrasonic echo detection of local debonding of aircraft icing[J]. Journal of Vibration, Measurement & Diagnosis, 2024, 44(1): 166–171 (in Chinese) [Google Scholar]

[25] TIAN Tian, WANG Yuan, TAO Mingjieet al.. Experimental study on electrothermal deicing of graphene Composites[J]. Science Technology and Engineering, 2019, 19(28): 390–395 (in Chinese) [Google Scholar]

[26] JIANG Xingliang, WANG Yangyang. Studies on the electro-impulse de-icing system of aircraft[J]. Aerospace, 2019, 6(1): 67–82 [Google Scholar]

[27] WANG Y, WANG Y, LI W, et al. Study on freezing characteristics of the surface water film over glaze ice by using an ultrasonic pulse-echo technique[J]. Ultrasonics, 2022, 126(12): 106804 [CrossRef] [PubMed] [Google Scholar]

[28] LI Xin, BAI Junqiang, HUA Jun, et al. A spongy icing model for aircraft icing[J]. Chinese Journal of Aeronautics, 2014, 27(1): 40–51 [Google Scholar]

[29] JANJUA Z A, TURNBULL B, HIBBERD Set al.. Mixed ice accretion on aircraft wings[J]. Physics of Fluids, 2018, 30(2): 027101 [Google Scholar]

[30] FOLDS D L, LOGGINS C D. Transmission and reflection of ultrasonic waves in layered media[J]. The Journal of the Acoustical Society of America, 1977, 62(5): 1102–1109 [Google Scholar]

[31] DU Gonghuan, ZHU Zhemin, GONG Xiufen. Fundamentals of acoustics[M]. NanJing: Nanjing University Press, 2001 (in Chinese) [Google Scholar]

[32] TIRMIZI S H, GILL W N. Effect of natural convection on growth velocity and morphology of dendritic ice crystals[J]. Journal of Crystal Growth, 1987, 85(3): 488–502 [Google Scholar]

[33] Committee AC-9C Aircraft Icing Technology. Minimum operational performance specification for inflight icing detection systems[S]. SAE Standard AS5498, 2009 [Google Scholar]