大过载机动下飞机油箱晃动冲击效应的流固耦合分析  

Fluid-structure interaction analysis of sloshing impact effect of aircraft fuel tank under high overload maneuvering

作　　者：钟连 支亚非 杨莹 杨尚霖 姚小虎[1] ZHONG Lian;ZHI Yafei;YANG Ying;YANG Shanglin;YAO Xiaohu(School of Civil Engineering and Transportation,South China University of Technology,510640 Guangzhou,China;Chengdu Aircraft Industrial(Group)Co.,Ltd.,610092 Chengdu,China)

机构地区：[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,成都610092

出　　处：《应用力学学报》2025年第1期40-53,共14页Chinese Journal of Applied Mechanics

基　　金：国家杰出青年科学基金资助项目(No.11925203)。

摘　　要：搭建Abaqus与Star-ccm+联合仿真流固耦合方法对某型飞机全复合材料油箱在弹射起飞与拦阻着陆过程中的晃动问题进行研究。首先通过模拟液舱晃动实验验证了所搭建流固耦合分析方法的可靠性。根据飞机油箱原型建立了全复合材料油箱精细结构模型和流体域模型,探究了3种不同充液率下的油箱晃动冲击效应,得到了弹射起飞与拦阻着陆过程中油箱内油液的晃动形态、压力分布、油箱应力应变及油箱蒙皮变形等结果。分析表明:弹射起飞与拦阻着陆过程中油液晃动有堆积、晃动、平稳3个阶段,油箱内燃油的晃动集中于前1.3 s内;2种工况中燃油冲击油箱产生的冲击压力均随充液率提升而增大,弹射起飞和拦阻着陆工况中最大冲击压力分别为19.135 kPa和11.102 kPa;飞机在大过载过程中油箱结构响应由过载主导;拦阻着陆过程中油箱结构响应大于弹射起飞,因此拦阻着陆对于油箱结构强度的要求更为严格。This study performed a series of fluid-structure interaction simulations based on Abaqus and Star-ccm+to explore the sloshing effect of a certain type of aircraft composite fuel tank.This method was validated using the tank sloshing experimental data.Based on the aircraft fuel tank prototype,the refined structural model and fluid model of the composite fuel tank were established.The dynamic response of the fuel tank under three different filling levels was explored.Furthermore,the pressure distribution,stress-strain relationship and skin deformation of the tank were obtained.The results showed that the fuel sloshing depicted three stages during the process of catapult take-off and arresting landing,i.e.,accumulation,sloshing and stabilization.Moreover,the sloshing of the fuel mainly happened in the first 1.3 s.The sloshing impact pressure increased with the fuel filling level,and the maximum impact pressure in Catapult take-off and arresting landing conditions was 19.135 kPa and 11.102 kPa,respectively.The response of the fuel tank was dominated by the overload during the two processes.The stress and strain of the fuel tank during the arresting landing were greater than those during the catapult take-off,so the requirements for the structural strength of the fuel tank in arresting landing are more stringent.

关 键 词：弹射起飞 拦阻着陆 大过载 油箱晃动 流固耦合 

分 类 号：V222[航空宇航科学与技术—飞行器设计]