基于CFD的民用飞机水上迫降动力学仿真研究  

DYNAMIC SIMULATION OF CIVIL AIRCRAFT DITCHING BASED ON CFD METHOD

作　　者：罗文莉[1] 陈皓宇 LUO Wenli;CHEN Haoyu(Aircraft Structure and Stress Division,Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海飞机设计研究院飞机结构强度工程技术所,上海201210

出　　处：《力学与实践》2022年第2期293-302,共10页Mechanics in Engineering

摘　　要：针对民用飞机水上迫降动态冲击问题,采用数值仿真方法进行了研究。基于计算流体力学采用雷诺平均N–S方程求解,结合流体体积模型和全流场运动网格捕捉水-气交界面,求解六自由度方程获得飞机的位置和姿态。采用该方法研究了尾吊-高平尾布局飞机的水上迫降过程。结果表明,该方法可以较好地模拟水上迫降的运动和受力,入水早期飞机受到较大水冲击载荷,后体吸力使得飞机抬头,之后随着速度降低吸力减小,飞机逐渐低头并趋于稳定。A numerical simulation was carried out to investigate the dynamic impact for civil aircraft ditching.The simulation used Reynolds averaged N–S equation from the computational fluid dynamics(CFD). Water-air interface and ditching process were modeled through the combination of volume of fluid(VOF) method and full-flow moving mesh. The position and attitude of aircraft were determined by solving 6-degrees-of-freedom equations. Firstly, the method was validated through typical examples, and then it was used for ditching simulation and analysis of a regional aircraft. The tail-mounted-engine and high-tail layout was focused when researching ditching characteristics. The results show that ditching movement and load characteristics can be well simulated. During water entry period, the regional aircraft is subjected to a large water impact load,while the suction force generated by rear fuselage makes the aircraft pitching up. Afterwards, the suction force decreases as speed decreases, and the aircraft gradually pitches down and approaches to a stable state.

关 键 词：民用飞机 水上迫降 计算流体力学 水冲击载荷 

分 类 号：V215.1[航空宇航科学与技术—航空宇航推进理论与工程] V221.4