机动行为下飞机油箱晃动流固耦合动力学分析

doi:10.7527/S1000-6893.2018.22471

固体力学与飞行器总体设计

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

机动行为下飞机油箱晃动流固耦合动力学分析

杨尚霖¹, 陈晓峰², 杜发喜², 雷忠琦¹, 姚小虎¹

1. 华南理工大学土木与交通学院, 广州 510640;
2. 成都飞机工业(集团)有限责任公司技术中心, 成都 610092

收稿日期:2018-06-25 修回日期:2018-08-09 出版日期:2019-03-15 发布日期:2018-11-14
通讯作者: 姚小虎 E-mail:yaoxh@scut.edu.cn
基金资助:
国家自然科学基金（11372113，11472110，11672110）

Dynamic analysis of fluid-structure interaction on aircraft fuel tank sloshing during maneuver

YANG Shanglin¹, CHEN Xiaofeng², DU Faxi², LEI Zhongqi¹, YAO Xiaohu¹

1. School of Civil Engineering and Transportation, South China University of Technology, Guangzhou 510640, China;
2. Technology Center, Chengdu Aircraft Industrial (Group) Co., Ltd., Chengdu 610092, China

Received:2018-06-25 Revised:2018-08-09 Online:2019-03-15 Published:2018-11-14
Supported by:
National Natural Science Foundation of China (11372113,11472110,11672110)

摘要/Abstract

摘要： 飞机执行机动飞行时整体处于大过载状态，此时的油箱晃动流固耦合问题较为复杂。针对这一问题，以某型飞机整体油箱为研究对象，建立ABAQUS与Star-CCM+联合仿真流固耦合方法，对飞机半滚倒转机动行为下的油箱晃动流固耦合效应进行分析，得到了半滚倒转过程中燃油的形态变化，流体域压力以及油箱部件的应力时程曲线等结果，并探究了油箱充液率变化对流固耦合效应的影响。结果表明：机动过载对油箱部件应力应变的影响大于燃油晃动冲击，除上蒙皮外部件应力均随着充液率增加而增加。

关键词: 机动行为, 油箱晃动, 流固耦合, 半滚倒转, 过载

Abstract: When the aircraft performs the maneuver flight, the whole structure is in a large overload condition, and the problem of the fluid-structure interaction of the fuel tank sloshing is complicated. Based on a certain type of aircraft fuel tank, a fluid-structure interaction simulation method is proposed with ABAQUS and Star-CCM+ software. By investigating the fluid-structure interaction effect of the fuel tank sloshing during the Split-S maneuver, the morphological change of fuel, the pressure of the fluid filed and the time-history curves of the stress of tank components are obtained. The influence of the filling rate changes on tank sloshing is analyzed. The results indicate that the influence of the overload on the stress and strain of tank components is greater than that of the liquid sloshing, and the stress of all components increase with the increase of filling rate except the upper skin.

Key words: maneuver, fuel tank sloshing, fluid-structure interaction, Split-S, overload

中图分类号:

V222

杨尚霖, 陈晓峰, 杜发喜, 雷忠琦, 姚小虎. 机动行为下飞机油箱晃动流固耦合动力学分析[J]. 航空学报, 2019, 40(3): 222471-222471.

YANG Shanglin, CHEN Xiaofeng, DU Faxi, LEI Zhongqi, YAO Xiaohu. Dynamic analysis of fluid-structure interaction on aircraft fuel tank sloshing during maneuver[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(3): 222471-222471.

参考文献

[1] 苟兴宇, 王本利, 马兴瑞, 等. 航天工程中的贮箱类液固耦合动力学建模及耦合机理研究[J]. 强度与环境, 1998(1):9-16. GOU X Y, WANG B L, MA X R, et al. Dynamic modelling of liquid-solid coupling system with container in spacecraft engineering and investigation of its coupling mechanism[J]. Structure & Environment Engineering, 1998(1):9-16(in Chinese).
[2] ABRAMSON H N. The dynamic behavior of liquids in moving containers:NASA-SP-106[R]. Washington, D.C.:NASA, 1966.
[3] 尹立中, 王本利, 邹经湘. 航天器液体晃动与液固耦合动力学研究概述[J]. 哈尔滨工业大学学报, 1999(2):118-122. YIN L Z, WANG B L, ZOU J X. Introduction to investigation of liquid sloshing and liquid-solid coupled dynamics of spacecraft[J]. Journal of Harbin Institute of Technology, 1999(2):118-122(in Chinese).
[4] 李青, 王天舒, 马兴瑞. 充液航天器液体晃动和液固耦合动力学的研究与应用[J]. 力学进展, 2012, 42(4):472-481. LI Q, WANG T S, MA X R. Reviews on liquid sloshing dynamics and liquid-structure coupling dynamics in liquid-filled spacecrafts[J]. Advances in Mechanics, 2012, 42(4):472-481(in Chinese).
[5] 毛志祥, 杨觉敏. 飞机整体油箱的液固耦合振动计算[J]. 航空学报, 1990, 11(11):589-594. MAO Z X, YANG J M. Numerical analysis of solid-fluid interactive vibration of an aircraft integral tank[J]. Acta Aeronautica et Astronautica Sinica, 1990, 11(11):589-594(in Chinese).
[6] 王力, 谢辉, 张琳. 无人机发射过程燃油晃动分析[J]. 航空科学技术, 2016, 27(1):36-40. WANG L, XIE H, ZHANG L. Analysis of fuel sloshing in UAV launching process[J]. Aeronautical Science & Technology, 2016, 27(1):36-40(in Chinese).
[7] 杨瑞. 基于ALE有限元法的飞机整体油箱燃油晃动特性研究[D]. 哈尔滨:哈尔滨工业大学, 2016. YANG R. Research of fuel sloshing in aircraft integral tanks by the ALE finite element method[D]. Harbin:Harbin Institute of Technology, 2016(in Chinese).
[8] YANG X, ZHANG Z, YANG J, et al. Fluid-structure interaction analysis of the drop impact test for helicopter fuel tank[J]. Springerplus, 2016, 5(1):1573.
[9] 刘富, 童明波, 赵宏韬. 飞机副油箱液体晃动动力学分析[J]. 航空计算技术, 2011, 41(3):54-56. LIU F, TONG M B, ZHAO H T. Dynamic analysis of liquid sloshing in an aircraft auxiliary fuel tank[J]. Aeronautical Computing Technique, 2011, 41(3):54-56(in Chinese).
[10] 唐浩, 徐建, 朱建辉, 等. 导弹油箱燃油晃动仿真分析[J]. 无线互联科技, 2015, 2(3):76-79. TANG H, XU J, ZHU J H, et al. Study of liquid sloshing in missile fuel tank based on SPH method[J]. Wireless Internet Technology, 2015, 2(3):76-79(in Chinese).
[11] 黄愉太. 飞机油箱晃动流固耦合动力学研究[D]. 广州:华南理工大学, 2015. HUANG Y T. Dynamics research on the fluid-structure interaction sloshing system in aircraft fuel tank[D]. Guangzhou:South China University of Technology, 2015(in Chinese).
[12] VELDMAN A E P, GERRITS J, LUPPES R, et al. The numerical simulation of liquid sloshing on board spacecraft[J]. Journal of Computational Physics, 2007, 224(1):82-99.
[13] HV S, SG S, SG M. Simulation of sloshing in rigid rectangular tank and a typical aircraft drop tank[J/OL]. Journal of Aeronautics & Aerospace Engineering, 2017, 06(1):1-9[2018-03-15].http://www.omicsonline.org/aeronautics-aerospace-engineering.php.DOI:10.4172/2168-9792.1000186.
[14] FARHAT C, CHIU E K, AMSALLEM D, et al. Modeling of fuel sloshing and its physical effects on flutter[J]. AIAA Journal, 2013, 51(9):2252-2265.
[15] 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, 2015, 1115:527-530.
[16] 岳宝增, 李笑天. ALE有限元方法研究及应用[J]. 力学与实践, 2002, 24(2):7-11. YUE B Z, LI X T. Study of the ALE finite element method and its applications[J]. Mechanics in Engineering, 2002, 24(2):7-11(in Chinese).
[17] 邵绪强, 刘艳, 赵美花, 等. 基于SPH方法的流体物理模拟技术综述[J]. 自然科学, 2016, 4(2):171-181. SHAO X Q, LIU Y, ZHAO M H, et al. A survey on fluid physical simulation technology based on SPH method[J]. Open Journal of Nature Science, 2016, 4(2):171-181(in Chinese).
[18] 张健, 方杰, 范波芹. VOF方法理论与应用综述[J]. 水利水电科技进展, 2005, 25(2):67-70. ZHANG J, FANG J, FAN B Q. Advances in research of VOF method[J]. Advances in Science & Technology of Water Resources, 2005, 25(2):67-70(in Chinese).
[19] SOUTO-IGLESIAS A, BOTIA-VERA E, MARTIN A, et al. A set of canonical problems in sloshing. Part 0:Experimental setup and data processing[J]. Ocean Engineering, 2011, 38(16):1823-1830.
[20] DELORME, COLAGROSSI, SOUTO-IGLESIAS, 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.
[21] ANSARI M R, FIROUZ-ABADI R D, GHASEMI M. Two phase modal analysis of nonlinear sloshing in a rectangular container[J]. Ocean Engineering, 2011, 38(11):1277-1282.
[22] PEREGRINE D H. Water-wave impact on walls[J]. Annual Review of Fluid Mechanics, 2003, 35(1):23-43.
[23] 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 B Z. Aircraft design manual book 10:Structure design[M]. Beijing:Aviation Industry Press, 2000:601-602(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

机动行为下飞机油箱晃动流固耦合动力学分析

Dynamic analysis of fluid-structure interaction on aircraft fuel tank sloshing during maneuver

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	汪博, 高培鑫, 马辉, 孙伟, 林君哲, 李晖, 韩清凯, 刘中华. 航空发动机管路系统动力学特性综述[J]. 航空学报, 2022, 43(5): 25332-025332.
[2]	卢昱锦, 肖天航, 邓双厚, 支豪林, 朱震浩, 陆召严. 着水初始条件对水陆两栖飞机着水性能的影响[J]. 航空学报, 2021, 42(7): 124483-124483.
[3]	童明波, 陈吉昌, 李乐, 肖天航, 古彪, 董登科, 汪正中. 飞行器水载荷结构完整性数值模拟现状与展望-Part I:水上迫降和水上漂浮[J]. 航空学报, 2021, 42(5): 524530-524530.
[4]	艾邦成, 陈思员, 韩海涛, 胡龙飞, 鲁芹, 初敏, 邓代英, 俞继军. 疏导式热防护结构传热极限特性[J]. 航空学报, 2021, 42(2): 623989-623989.
[5]	肖惟, 于江龙, 董希旺, 李清东, 任章. 过载约束下的大机动目标协同拦截[J]. 航空学报, 2020, 41(S1): 723777-723777.
[6]	白志会, 黎克波, 苏文山, 陈磊. 现实真比例导引拦截任意机动目标捕获区域[J]. 航空学报, 2020, 41(8): 323947-323947.
[7]	赵欢, 焦忠泽, 孙丹, 刘永泉, 战鹏, 信琦. 多级刷式密封级间压降分配影响因素数值与实验研究[J]. 航空学报, 2020, 41(10): 123544-123544.
[8]	胡文刚, 林长亮, 王刚, 门坤发. 多欧拉域耦合法在平尾鸟撞中的应用[J]. 航空学报, 2020, 41(1): 222860-222860.
[9]	邱滋华, 徐敏, 张斌, 梁春雷. 适用于涡激振荡问题研究的并行高精度方法[J]. 航空学报, 2019, 40(3): 122483-122483.
[10]	周聪, 闫晓东, 唐硕. 圆弧预测变系数显式拦截中制导[J]. 航空学报, 2019, 40(10): 323122-323122.
[11]	黄江涛, 周铸, 刘刚, 高正红, 黄勇, 王运涛. 飞行器气动/结构多学科延迟耦合伴随系统数值研究[J]. 航空学报, 2018, 39(5): 121731-121731.
[12]	张伟伟, 高弈奇, 全金楼, 苏丹. 失谐叶栅的受迫振动响应特性分析[J]. 航空学报, 2017, 38(9): 521018-521018.
[13]	张帆, 郑津洋, 马利. 内压作用下的航空轮胎爆破碎片动力响应[J]. 航空学报, 2017, 38(8): 221032-221032.
[14]	李映坤, 韩珺礼, 陈雄, 周长省, 巩伦昆. 基于多物理场耦合的双脉冲发动机点火过程数值模拟[J]. 航空学报, 2017, 38(4): 120409-120409.
[15]	王运涛, 孙岩, 孟德虹, 张书俊, 杨小川. 包含支撑装置和机翼变形的CRM-WB构型气动特性数值模拟[J]. 航空学报, 2017, 38(10): 121202-121202.