机翼电脉冲除冰系统电磁力及其除冰过程仿真研究

发布时间：2018-01-26 05:49

本文关键词： 多电飞机电脉冲除冰电路仿真电磁场仿真动力学模型　出处：《南京航空航天大学》2017年博士论文　论文类型：学位论文

【摘要】：Boeing787飞机开启了多电飞机的新纪元,也为飞机防除冰系统变革提出了新的要求。由于多电飞机除短舱防冰外,取消了飞机发动机的引气,使用电力成为机翼防除冰系统的唯一可能的能源提取方式。电脉冲除冰系统具有效能高、重量轻、维修性好等优点,越来越得到重视和研究。本文采用理论分析、仿真计算和试验相结合的方法,研究了多电飞机防除冰的电磁力作用、除冰结构动力学建模和除冰率优化的分析方法,具体内容如下:根据电脉冲工作原理搭建电路仿真模型,对电脉冲的发生电路进行仿真。采用分析电流随时间变化的方法,来研究电脉冲放电的过程。在给定电路参数的条件下,求解电脉冲发生电路输出的电流响应。通过调整各电路元件的参数,研究脉冲电流与各电路参数之间的相关关系。模拟电脉冲发生电路输出的电流,为电磁场仿真进行参数选择。利用有限元分析软件建立了电脉冲除冰装置与蒙皮之间的电磁场仿真模型,用于模拟系统工作时的电磁场变化、结构受力情况等,并对二维和三维的电磁场和动力学结果进行了对比分析。在给定电流激励条件下,利用麦克斯韦方程计算电流密度、磁感应强度等物理量在电磁场中的瞬态分布,并进一步求解各有限单元在每个时刻的受力情况。研究了电路参数、线圈匝数、导线参数、蒙皮与线圈的间距对蒙皮受力的影响,分析得到了蒙皮感应电流密度、加速度、位移与位置的关系。通过建立典型平板除冰有限元模型,模拟脉冲力的分布,对除冰过程进行仿真分析。研究了不同的冰层松脱准则对计算结果的影响,通过实验比较的方法,确定了适用于电脉冲除冰过程的冰层松脱准则。使用真实的机翼前缘除冰结构,建立机翼前缘电脉冲除冰结构动力学分析模型,采用瞬态动力学方法,模拟机翼前缘除冰过程。通过改变施加在前缘除冰结构上的脉冲载荷峰值,研究脉冲载荷大小对除冰效果以及结构受力的影响,获取机翼前缘局部危险部位的应力场分布及最大局部应力。确定了输入能量、除冰率与结构应力之间的关系,并对双脉冲作用和四脉冲作用下的除冰率、蒙皮的最大等效应力及结构最大等效应力进行了对比分析,获得了相关参数的优化结果,提出了单位载荷除冰率、单位载荷蒙皮等效最大应力和单位载荷结构等效最大应力等概念。开展了多脉冲不同组合打击模式下机翼前缘除冰仿真计算,确定了结构两侧打击不同时间差以及不同峰值载荷情况下对整个结构的除冰率的影响,为电脉冲装机应用涉及到线圈布置、系统逻辑控制、除冰率选择等提供了设计与优化依据。
[Abstract]:Boeing787 aircraft has opened a new era of multi-electric aircraft, and has put forward new requirements for the change of anti-icing system of aircraft. The use of electric power has become the only possible energy extraction method for the anti-icing system of wing. The electric pulse deicing system has the advantages of high efficiency, light weight, good maintainability and so on. More and more attention has been paid to it. In this paper, the electromagnetic force of anti-icing of multi-electric aircraft is studied by the method of theoretical analysis, simulation and experiment. The dynamic modeling of deicing structure and the analysis method of deicing rate optimization are as follows: the circuit simulation model is built according to the working principle of electric pulse. The generation circuit of electric pulse is simulated. The method of analyzing the change of current with time is used to study the process of electric pulse discharge. Under the condition of given circuit parameters. By adjusting the parameters of each circuit component, the correlation between the pulse current and the circuit parameters is studied, and the output current of the electric pulse generator circuit is simulated. Using the finite element analysis software, the electromagnetic field simulation model between the electric pulse deicing device and the skin is established, which can be used to simulate the electromagnetic field change and the structure force situation when the system works. The electromagnetic and dynamic results of two and three dimensions are compared and analyzed. The current density is calculated by Maxwell equation under given current excitation conditions. The transient distribution of magnetic induction intensity and other physical quantities in the electromagnetic field, and further solve the stress of each finite element at each moment. The circuit parameters, coil turns, wire parameters are studied. The influence of the distance between the skin and the coil on the force on the skin is analyzed and the relationship between the current density acceleration displacement and position of the skin is obtained. The distribution of pulse force is simulated by establishing the finite element model of the typical plate deicing. The simulation analysis of deicing process was carried out, and the influence of different ice loosening criteria on the calculation results was studied, and the method of experimental comparison was used. The deicing criterion suitable for the electric pulse deicing process is determined. Using the real deicing structure of the front edge of the wing, the dynamic analysis model of the electric pulse deicing structure on the front edge of the wing is established, and the transient dynamic method is adopted. By changing the peak value of pulse load applied on the leading edge deicing structure, the effect of pulse load on deicing effect and structure force is studied. The distribution of the stress field and the maximum local stress at the dangerous part of the front edge of the wing are obtained. The relationship among the input energy, the deicing rate and the structural stress is determined, and the deicing rate under the action of double pulse and four pulses is determined. The maximum equivalent stress of the skin and the maximum equivalent stress of the structure were compared and analyzed. The optimization results of the related parameters were obtained and the deicing rate per unit load was proposed. Based on the concepts of equivalent maximum stress of unit load skin and equivalent maximum stress of unit load structure, the deicing simulation calculation of wing leading edge under multi-pulse and different combined attack mode was carried out. The influence of different time difference and different peak load on the deicing rate of the whole structure is determined. The application of the electric pulse loader involves the coil arrangement and the logic control of the system. The selection of deicing rate provides the basis for design and optimization.
【学位授予单位】：南京航空航天大学
【学位级别】：博士
【学位授予年份】：2017
【分类号】：V244.15

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