| 地效飞行器双断阶机腹着水砰击过载分析 |
| |
| 引用本文： | 陈思宇,孙建红,孙智,侯斌,刘浩.地效飞行器双断阶机腹着水砰击过载分析[J].航空工程进展,2022,13(6):134-143. |
| |
| 作者姓名： | 陈思宇 孙建红 孙智 侯斌 刘浩 |
| |
| 作者单位： | 南京航空航天大学飞行器环境控制与生命保障工业与信息化部重点实验室,南京航空航天大学民航学院,南京航空航天大学民航学院,南京航空航天大学飞行器环境控制与生命保障工业与信息化部重点实验室,南京航空航天大学飞行器环境控制与生命保障工业与信息化部重点实验室 |
| |
| 基金项目： | 江苏高校优势学科建设工程资助项目，航空科学基金项目（20200023052002），中国空气动力研究与发展中心基础和前沿技术研究基金资助项目(PJD20200210) |
| |
| 摘 要： | 地效飞行器着水过程中，断阶着水产生的冲击易导致结构表面屈曲或破坏。基于ALE 有限元法，通过罚函数法处理两相界面流固耦合问题，对地效飞行器着水过程进行数值模拟，分析不同前飞速度、下沉速度、俯仰角等参数变化对浸水深度、砰击过载等的影响。结果表明：在研究工况下，机体着水产生的压力峰值均出现在断阶处；随着俯仰角增加水平过载峰值减小，垂向过载峰值先增大后减小，俯仰角为7°时垂向过载峰值最大，是最低过载峰值（俯仰角为15°时）的1.4 倍；前飞速度增加致使水平过载峰值增大，而对垂向过载峰值影响不明显，但垂向过载峰值与垂向速度的平方近似呈线性关系，下沉速度越大，砰击过载峰值越大。
|
| 关 键 词： | 地效飞行器 断阶 砰击 过载 俯仰角 |
| 收稿时间： | 2022/1/14 0:00:00 |
| 修稿时间： | 2022/3/15 0:00:00 |
Analysis of Water Landing Overload of the Double-Stepped Wing-in-Ground Aircraft |
| |
| CHEN Siyu,SUN Jianhong,SUN Zhi,HOU Bin and LIU Hao.Analysis of Water Landing Overload of the Double-Stepped Wing-in-Ground Aircraft[J].Advances in Aeronautical Science and Engineering,2022,13(6):134-143. |
| |
| Authors: | CHEN Siyu SUN Jianhong SUN Zhi HOU Bin and LIU Hao |
| |
| Affiliation: | Nanjing University of Aeronautics and Astronautics,,,, |
| |
| Abstract: | It is important and necessary to study the water landing overload of wing-in-ground(WIG) aircraft, as the damage or buckling step is most likely occurred in body steps, especially in double-stepped cases. The Arbitrary Lagrangian-Eulerian (ALE) finite element method was utilized to simulate the water landing of a wing-in-ground aircraft, and the penalty function method was used in the two-phase interface fluid-solid interaction problem. The effect of different parameters such as horizontal flight velocity, falling velocity, pitch angle on the immersion depth, and overload was analyzed. The results showed that the pressure maxima of the aircraft landing water all occur at the step in this paper. With the increase of the pitch angle, the peak of vertical overload rises and then falls, while the peak of horizontal overload keeps reducing. When the pitch angle is 7°, the vertical overload peak reaches the highest, which is 1.4 times that of the lowest overload in the pitch angle of 15°. On the other hand, the peak of the horizontal overload rises as the horizontal component of flight velocity increases, and it is visible that there is no discernible effect on the peak of vertical overload. Meanwhile, an approximately linear relationship appeared between the peak of vertical overload and the square of falling velocity in this paper. |
| |
| Keywords: | wing-in-ground aircraft planning step water landing overload pitch angle |
|
| 点击此处可从《航空工程进展》浏览原始摘要信息 |
|
点击此处可从《航空工程进展》下载全文 |
|
