本文關(guān)鍵詞： 多電飛機 電脈沖除冰 電路仿真 電磁場仿真 動力學(xué)模型　出處：《南京航空航天大學(xué)》2017年博士論文　論文類型：學(xué)位論文

【摘要】：Boeing787飛機開啟了多電飛機的新紀元,也為飛機防除冰系統(tǒng)變革提出了新的要求。由于多電飛機除短艙防冰外,取消了飛機發(fā)動機的引氣,使用電力成為機翼防除冰系統(tǒng)的唯一可能的能源提取方式。電脈沖除冰系統(tǒng)具有效能高、重量輕、維修性好等優(yōu)點,越來越得到重視和研究。本文采用理論分析、仿真計算和試驗相結(jié)合的方法,研究了多電飛機防除冰的電磁力作用、除冰結(jié)構(gòu)動力學(xué)建模和除冰率優(yōu)化的分析方法,具體內(nèi)容如下:根據(jù)電脈沖工作原理搭建電路仿真模型,對電脈沖的發(fā)生電路進行仿真。采用分析電流隨時間變化的方法,來研究電脈沖放電的過程。在給定電路參數(shù)的條件下,求解電脈沖發(fā)生電路輸出的電流響應(yīng)。通過調(diào)整各電路元件的參數(shù),研究脈沖電流與各電路參數(shù)之間的相關(guān)關(guān)系。模擬電脈沖發(fā)生電路輸出的電流,為電磁場仿真進行參數(shù)選擇。利用有限元分析軟件建立了電脈沖除冰裝置與蒙皮之間的電磁場仿真模型,用于模擬系統(tǒng)工作時的電磁場變化、結(jié)構(gòu)受力情況等,并對二維和三維的電磁場和動力學(xué)結(jié)果進行了對比分析。在給定電流激勵條件下,利用麥克斯韋方程計算電流密度、磁感應(yīng)強度等物理量在電磁場中的瞬態(tài)分布,并進一步求解各有限單元在每個時刻的受力情況。研究了電路參數(shù)、線圈匝數(shù)、導(dǎo)線參數(shù)、蒙皮與線圈的間距對蒙皮受力的影響,分析得到了蒙皮感應(yīng)電流密度、加速度、位移與位置的關(guān)系。通過建立典型平板除冰有限元模型,模擬脈沖力的分布,對除冰過程進行仿真分析。研究了不同的冰層松脫準則對計算結(jié)果的影響,通過實驗比較的方法,確定了適用于電脈沖除冰過程的冰層松脫準則。使用真實的機翼前緣除冰結(jié)構(gòu),建立機翼前緣電脈沖除冰結(jié)構(gòu)動力學(xué)分析模型,采用瞬態(tài)動力學(xué)方法,模擬機翼前緣除冰過程。通過改變施加在前緣除冰結(jié)構(gòu)上的脈沖載荷峰值,研究脈沖載荷大小對除冰效果以及結(jié)構(gòu)受力的影響,獲取機翼前緣局部危險部位的應(yīng)力場分布及最大局部應(yīng)力。確定了輸入能量、除冰率與結(jié)構(gòu)應(yīng)力之間的關(guān)系,并對雙脈沖作用和四脈沖作用下的除冰率、蒙皮的最大等效應(yīng)力及結(jié)構(gòu)最大等效應(yīng)力進行了對比分析,獲得了相關(guān)參數(shù)的優(yōu)化結(jié)果,提出了單位載荷除冰率、單位載荷蒙皮等效最大應(yīng)力和單位載荷結(jié)構(gòu)等效最大應(yīng)力等概念。開展了多脈沖不同組合打擊模式下機翼前緣除冰仿真計算,確定了結(jié)構(gòu)兩側(cè)打擊不同時間差以及不同峰值載荷情況下對整個結(jié)構(gòu)的除冰率的影響,為電脈沖裝機應(yīng)用涉及到線圈布置、系統(tǒng)邏輯控制、除冰率選擇等提供了設(shè)計與優(yōu)化依據(jù)。
[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.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2017
【分類號】：V244.15

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