翼吊低平尾布局飞机水上迫降数值仿真分析

Numerical Simulation Analysis of Wing-hung and Low-hip Aircraft Ditching

为研究翼吊低平尾布局飞机水上迫降过程,基于欧拉-拉格朗日耦合法对某型号飞机开展水上迫降仿真计算,通过和缩比模型试验结果对比,验证仿真方法的适用性。基于仿真结果,分析飞机的运动和受载以及垂向初速度和初始俯仰角对飞机水上迫降过程的影响及其机理,提出降低翼吊低平尾布局飞机水上迫降冲击载荷的策略。结果表明:飞机先抬头后低头、平尾着水低头力矩对飞机抬头有限制作用;俯仰角变化量峰值随垂向初速度和初始俯仰角增加而降低;垂向加速度峰值随垂向初速度增加而提高,且随初始俯仰角增加而降低;应尽量减小垂向初速度,增大初始俯仰角。

In order to study the ditching of a wing-hung and low-hip aircraft,the simulation calculation of ditching was carried out for a certain type of aircraft based on Euler-Lagrange coupling method,and the applicability of the simulation method was verified by comparing with the results of the scaled model test.Based on the simulation results,the motion and load of the aircraft as well as the effects and mechanisms of the initial vertical velocity and initial pitch angle on the ditching process of the aircraft were analyzed.A strategy to reduce the ditching load of the wing-hung and low-HTP aircraft was proposed.The results show that the aircraft's looking-up first and bowing-down after,and the nose-down moment caused by the horizontal tail landing in the water limits the aircraft's head-up;the peak value of pitch angle variation decreases with the increase of vertical initial velocity and initial pitch angle;the peak vertical acceleration increases with the increase of the initial vertical velocity and decreases with the increase of the initial pitch angle;therefore,the initial vertical speed should be reduced as much as possible and the initial pitch angle should be increased.