航空学报 > 2021, Vol. 42 Issue (7): 124483-124483   doi: 10.7527/S1000-6893.2020.24483

着水初始条件对水陆两栖飞机着水性能的影响

卢昱锦, 肖天航, 邓双厚, 支豪林, 朱震浩, 陆召严   

  1. 南京航空航天大学 航空学院 飞行器先进设计技术国防重点学科实验室, 南京 210016
  • 收稿日期:2020-07-02 修回日期:2020-10-10 发布日期:2020-11-06
  • 通讯作者: 肖天航 E-mail:xthang@nuaa.edu.cn
  • 基金资助:
    国防预研项目;国家自然科学基金(11672133);江苏高校优势学科建设工程;江苏省普通高校研究生科研创新计划(KYLX16_0391);中央高校基本科研业务费专项资金

Effects of initial conditions on water landing performance of amphibious aircraft

LU Yujin, XIAO Tianhang, DENG Shuanghou, ZHI Haolin, ZHU Zhenhao, LU Zhaoyan   

  1. National Defense Key Laboratory of Aircraft Advanced Design Technology, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
  • Received:2020-07-02 Revised:2020-10-10 Published:2020-11-06
  • Supported by:
    National Defense Pre-Research Foundation; National Natural Science Foundation of China (11672133); Priority Academic Program Development of Jiangsu Higher Education Institutions; Jiangsu Innovation Program for Graduate Education (KYLX16_0391); The Fundamental Research Funds for the Central Universities

摘要: 针对着水初始条件对水陆两栖飞机静水面降落性能影响的问题,使用非定常雷诺平均Navier-Stokes方程和标准k-ω两方程模型求解非定常流场,耦合流体体积模型捕捉自由液面,结合改进的流场域网格划分策略,并借助任意拉格朗日欧拉方法处理机体、网格和水气交界面三者关系。基于上述方法,探讨初始姿态角、下降速度和前飞速度对着水性能的影响,其中驾驶舱与重心位置加速度、气动力与水动力、俯仰角与吃水深度等参数变化被考虑在内,逐步得到最优着水初始条件。结果表明:增大初始姿态角有利于减缓飞机各位置除初次触水过载峰值外过载峰值的变化。当飞机俯仰力矩出现极值时,驾驶舱垂向过载显著大于其他方向和位置过载。减小初始下降速度,各加速度值也随之减小,值得注意的是重心垂向加速度值与初始垂向下降速度平方值存在线性变化关系。着水前飞速度的选取应使得气动升力略大于重力,飞机才能获得更佳的着水性能。

关键词: 水陆两栖飞机, 有限体积法, 流体体积模型, 任意拉格朗日欧拉方法, 驾驶舱过载

Abstract: The influence of the initial conditions on the water landing performance of an amphibious aircraft is investigated by solving the unsteady Reynolds-averaged Navier-Stokes equations coupled with the standard k-ω turbulence model. During simulation, the relationship among the aircraft, the mesh and the air-water interface is managed by the Arbitrary Lagrangian-Eulerian method with an improved computational mesh generation strategy. Based on this, the effects of the initial conditions including the incident angle, the descent velocity and the horizontal velocity on the landing performance are explored, meanwhile considering changes in parameters such as the overloads on the cockpit and the center of gravity, aerodynamics, hydrodynamics, the pitching angle and vertical displacement for the aircraft water landing process. Numerical results show that the amphibious aircraft experiences a relatively moderated load due to the increase of the initial incident angle. The cockpit experiences a much larger vertical overload value compared with that of others when the extreme value of pitching moments occurs. Furthermore, the overload of the aircraft reduces significantly as the descent velocity decreases. A linear relationship can be clearly established between the overloads on the center of gravity and the square of the downward velocities. Moreover, to obtain better landing performance on water, the aerodynamic lift caused by the horizontal flight velocity should be slightly larger than the aircraft gravity before landing.

Key words: amphibious aircraft, finite volume method, volume of fluid models, arbitrary Lagrangian-Eulerian method, overload of cockpits

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