某型双机身飞机水上迫降数值模拟

doi:10.12382/bgxb.2022.0111

摘要/Abstract

摘要：

飞机水上迫降过程是一个跨介质过程,即飞机从空气跨越到水的过程。探索和研究物体跨介质过程的物理现象和动态特性,对飞机水上迫降和跨介质飞行器入水砰击等问题具有重要的参考价值。针对某型双机身飞机水上迫降过程展开研究,综合运用URANS(unsteady Reynolds-averaged Navier- Stokes)方法、流体体积模型、动网格技术和6自由度模型对飞机水上迫降过程进行数值模拟。在三维平板水漂运动实验的验证基础上,研究俯仰角度这一关键参数对双机身飞机水上迫降过程的影响。研究结果表明:飞机在水上迫降过程中,俯仰角度越大,飞机的垂向速度峰值越大,垂向位移越大且俯仰偏转角度变化量越小;俯仰角度越小,飞机的水平速度减小得越快,飞机的水平位移越小;飞机以6°俯仰角度水上迫降时受到的水平作用力最大,可以在最短的时间内完成停靠;飞机以14°俯仰角度水上迫降时受到的垂向作用力最大,相同时刻的浸水位移最大。

关键词: 双机身飞机, 水上迫降, URANS方法, 流体体积模型, 俯仰角度

Abstract:

Aircraft ditching is a trans-media process, namely the process of the aircraft going from air to water. The exploration of the physical phenomena and dynamic characteristics of trans-media objects can provide insights into the research on airplane ditching and water entry of trans-media vehicles. The ditching process of a twin-fuselage aircraft is studied. The unsteady Reynolds-averaged Navier-Stokes (URANS) method, VOF method, dynamic grid technique and 6DOF model are used to numerically simulate the ditching process. Based on the numerical validation of the 3D plate water-skipping experiment, the effect of pitch angle on the ditching process of the twin-fuselage aircraft is analyzed. The numerical results show that: the larger the pitch angle, the greater the peak vertical velocity of the aircraft, the greater the vertical displacement and the smaller the change in pitch deflection angle during the ditching process; the horizontal velocity of the airplane decreases faster and the horizontal displacement of the aircraft is smaller as the pitch angle decreases; when the aircraft ditches with a 6° pitch angle, it is subjected to the largest horizontal force, and therefore stops in the shortest time; when the aircraft ditches with a 14° pitch angle, the vertical force is the largest, and meanwhile the submerged displacement is the largest.

Key words: twin-fuselage aircraft, water forced landing, URANS method, VOF method, pitch angle

孙肖元, 邓枫, 刘学强. 某型双机身飞机水上迫降数值模拟[J]. 兵工学报, 2023, 44(7): 2066-2079.

SUN Xiaoyuan, DENG Feng, LIU Xueqiang. Numerical Simulation of Ditching of a Twin-Fuselage Aircraft[J]. Acta Armamentarii, 2023, 44(7): 2066-2079.

图/表 23

图1 数值模拟流程

Fig.1 Flowchart of numerical simulation

图2 相位交界面的呈现原理图

Fig.2 Schematic diagram of the phase intersection interface

图3 一般物体的空间6DOF

Fig.3 6DOF in space of objects

图4 飞机三视图

Fig.4 Three views of the aircraft

图5 边界条件

Fig.5 Boundary conditions

图6 整体网格区域和移动网格区域

Fig.6 Global grid area and mobile grid area

图7 预处理后压力云图和相位云图

Fig.7 Pressure contour and phase contour after pretreatment

表1 4种不同网格的详细信息

Table 1 Details of four different grids

网格序号	整体网格区域网格单元尺寸/m	移动网格区域网格单元尺寸/m	整体网格区域网格单元数/ 万个	移动网格区域网格单元数/ 万个	网格单元总数/ 万个
网格1	0.45	0.03	443	207	650
网格2	0.4	0.03	616	207	823
网格3	0.4	0.025	616	426	1042
网格4	0.4	0.02	616	601	1217

图8 不同网格的数值结果对比

Fig.8 Comparison of simulation results of different grids

图9 圆盘的几何特征

Fig.9 Geometrical properties of the plate

图10 圆盘水面滑跳实验和数值计算的滑跳姿态对比(Ω=65rot/s,上为实验结果,下为数值模拟结果)

Fig.10 Comparison between experimentally obtained and numerically calculated skipping attitudes of the plate over water surface (Ω=65rot/s, the top is the experimental result, and the bottom is the simulation result)

图11 圆盘水面滑跳实验和数值计算的滑跳姿态对比(Ω=0rot/s,上为实验结果,下为数值模拟结果)

Fig.11 Comparison between experimentally obtained and numerically calculated skipping attitudes of the plate over water surface (Ω=0rot/s, the top is the experimental result, and the bottom is the numerical simulation result)

图12 β=20°时不同α值的圆盘最小投掷速度对比曲线

Fig.12 When β=20°, the minimum throwing speed of the plate with different values of α

图13 俯仰角度

Fig.13 Pitch angle

表2 飞机不同俯仰角度的质量属性

Table 2 Mass attributes of the aircraft at different pitch angles

俯仰角度	质心坐标/m	质量/kg	I_xx/(kg·m²)	I_yy/(kg·m²)	I_zz/(kg·m²)	I_xy/(kg·m²)
6°	(0,0,0)	365.122	556.250	1128.107	656.731	-65.879
8°	(0,0,0)	365.122	552.351	1132.006	656.731	-45.773
10°	(0,0,0)	365.122	549.864	1134.495	656.731	-25.445
12°	(0,0,0)	365.122	548.801	1135.558	656.731	-4.992
14°	(0,0,0)	365.122	549.167	1135.192	656.731	15.486

图14 不同时刻的飞机姿态和水面变化(上为飞机姿态云图,下为水面变化云图)

Fig.14 Aircraft attitude and water surface changes at different times (the top is the aircraft attitude contour, and the bottom is the water surface change contour)

图15 不同时刻的相位云图(上为飞机侧面相位云图,下为飞机底部浸水相位云图)

Fig.15 Phase countours at different moments (the top is the aircraft side phase contour, and the bottom is the aircraft bottom water immersion phase contour)

图16 俯仰偏转角度随时间的变化

Fig.16 Pitch deflection angle varying with time

图17 不同时刻的压力云图

Fig.17 Pressure contours at different moments

图18 垂向速度和垂向位移随时间变化

Fig.18 Vertical velocity and vertical displacement varying with time

图19 水平速度和水平位移随时间变化

Fig.19 Horizontal velocity and horizontal displacement varying with time

图20 垂向作用力和垂向加速度随时间变化

Fig.20 Vertical force and vertical acceleration varying with time

图21 水平作用力和水平加速度随时间变化

Fig.21 Horizontal force and horizontal acceleration varying with time

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