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.
国家科技期刊平台
NSTL
维普
万方数据
