正常盘旋飞机油箱液面晃动与结构动力学分析
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摘要
针对飞机油箱晃动流固耦合问题,采用ABAQUS与Star-CCM+联合仿真流固耦合方法,通过对比验证单向和双向流固耦合,确定了采用单向流固耦合方法分析油箱晃动流固耦合问题的可行性,并对某型飞机正常盘旋过程中的油箱晃动流固耦合问题进行研究。验证了满油状态下飞机油箱的结构安全性,并探究了不同充液率对飞机油箱晃动流固耦合效应的影响。结果表明:满油状态下飞机油箱结构安全性满足要求;充液率不同,各因素对油箱部件应力的影响程度不同。
For the fluid-solid coupling problem of aircraft fuel tank sloshing,the ABAQUS and Star-CCM+combined fluid-solid coupling simulation method was utilized to solve this problem.By comparing the one-way and two-way fluid-solid coupling methods,the feasibility of using one-way method to analyze the fluid-solid coupling problem of aircraft fuel tank sloshing was confirmed,and the fuel tank sloshing during the normal hover process of an aircraft was studied.The safety of tank structure at fully filled condition was verified,and the influence of filling rate on the fluid-solid coupling effect was investigated.The results indicate that the tank structural safety meets the requirement under full load,and the influence of various factors on the stress of components is different at different filling rate.
For the fluid-solid coupling problem of aircraft fuel tank sloshing,the ABAQUS and Star-CCM+combined fluid-solid coupling simulation method was utilized to solve this problem.By comparing the one-way and two-way fluid-solid coupling methods,the feasibility of using one-way method to analyze the fluid-solid coupling problem of aircraft fuel tank sloshing was confirmed,and the fuel tank sloshing during the normal hover process of an aircraft was studied.The safety of tank structure at fully filled condition was verified,and the influence of filling rate on the fluid-solid coupling effect was investigated.The results indicate that the tank structural safety meets the requirement under full load,and the influence of various factors on the stress of components is different at different filling rate.
引文
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[3]LI Baotong,LIU Honglei,ZHENG Shuai.Multidisciplinary topology optimization for reduction of sloshing in aircraft fuel tanks based on SPH simulation[J].Structural&Multidisciplinary Optimization,2018,58(4):1719-1736.
[4]何欢,陈国平,张家滨.带油箱结构的机身框段坠撞仿真分析[J].航空学报,2008,29(3):627-633.HE Huan,CHEN Guoping,ZHANG Jiabin.Crash simulation of fuselage section with fuel tank[J].Acta Aeronautica et Astronautica Sinica,2008,29(3):627-633.(in Chinese)
[5]方振平.飞机飞行动力学[M].北京:北京航空航天大学出版社,2005:42-46.FANG Zhenping.Aircraft flight dynamics[M].Beijing:Beihang University Press,2005:42-46.(in Chinese)
[6]卢军,杨翊仁.平放圆柱体内液体晃动特性及横向受力分析[J].科学技术与工程,2009,9(14):3945-3949.LU Jun,YANG Yiren.Characteristics of liquid sloshing and transverse force analysis of horizontal liquidfilled cylindrical tank[J].Science Technology and Engineering,2009,9(14):3945-3949.(in Chinese)
[7]HV S,SG S,SG M.Simulation of sloshing in rigid rectangular tank and a typical aircraft drop tank[J/OL].[2018-03-15].http:∥sci-hub.tw/10.4172/2168-9792.1000186.
[8]王珏,高原,朱洪涛,等.飞机机身整体油箱晃动初步分析[C]∥中国航空学会.探索创新交流---第六届中国航空学会青年科技论坛文集.北京:航空工业出版社,2014:489-497.WANG Jue,GAO Yuan,ZHU Hongtao,et al.Primary analysis of aircraft integral fuselage tank[C]∥Chinese Society of Aeronautics and Astronautics.Discovery,innovation and Communication,the 6th CSAA Science and Technique Youth Forum.Beijing:Aviation Industry Press,2014:489-497.(in Chinese)
[9]REDDY D R,ADITYA N M V,GUPTA M S N.Stress and deformation analysis of aircraft’s fuel tank under different inertia load cases in addition to a static test pressure using FEA[J].Advanced Materials Research,DOI:https:∥doi,org/10.4028/www.scientific.net/AMR.1115.527.
[10]SOUTO-IGLESIAS A,BOTIA-VERA E,MARTINA,et al.A set of canonical problems in sloshing.Part0:Experimental setup and data processing[J].Ocean Engineering,2011,38(16):1823-1830.
[11]DELORME L,COLAGROSSI A,SOUTO-IGLESIASA,et al.A set of canonical problems in sloshing,Part I:Pressure field in forced roll-comparison between experimental results and SPH[J].Ocean Engineering,2009,36(2):168-178.
[12]王宝忠.飞机设计手册.第10册:结构设计[M].北京:航空工业出版社,2000:601-602.WANG Baozhong.Aircraft design manual book 10:structure design[M].Beijing:Aviation Industry Press,2000:601-602.(in Chinese)