带应急漂浮系统直升机水上迫降性能研究  

Research on the Performance of Helicopter with Emergency Floating System for Ditching

作　　者：陈立霞[1] 汪正中[1] 辛冀[1] 王明镇 焦俊 Chen Lixia;Wang Zhengzhong;Xin Ji;Wang Mingzhen;Jiao Jun(Science and Technology on Rotorcraft Aeromechanics Laboratory,China Helicopter Research and Development Institute,Jingdezhen 333001,China;China Special Aircraft Research and Development Institute,Jingmen 448035,China)

机构地区：[1]中国直升机设计研究所直升机旋翼动力学国家级重点实验室,江西景德镇333001 [2]中国特种飞行器研究所,湖北荆门448035

出　　处：《航空科学技术》2021年第12期35-41,共7页Aeronautical Science & Technology

基　　金：民用飞机专项科研技术研究项目(MJ-2014-F-15)。

摘　　要：针对直升机水上迫降问题,以光滑粒子动力学方法离散水域进行建模,发展了机身着水载荷的理论分析模型。以带柔性气囊直升机构型的水上迫降为算例,开展了仿真分析。仿真计算结果与试验数据的对比显示,机身过载和气囊连接带的载荷的计算误差均在18%以内,验证了仿真模型的分析精度,可用于支持民用直升机水上迫降过程的强度和结构设计。从提高直升机生存率的角度出发,开展了不同着水工况下的仿真计算,对机身姿态角、重心位置等因素对各项着水载荷的影响进行了深入分析,给出了直升机水上迫降时的建议机身姿态。研究成果可为直升机水上迫降适航取证提供技术支持。In order to solve the problem of helicopter ditching, the theoretical analysis model is developed by using the method of smooth particle dynamics in discrete water area. The simulation analysis is carried out for an example of helicopter with flexible airbags. The comparison between simulation results and test data shows that the fuselage and airbag connected with load calculation error are within 18% and verifies that the analysis precision of the simulation model can be used to support civil helicopter ditching intensity and structure design. From the perspective of improving survival rates of helicopter, the simulation calculation under different conditions is carried out. This paper makes a thorough analysis on the influence of fuselage attitude angle and center of gravity position on helicopter water loads, which proposes the fuselage attitude during helicopter ditching on water. The results can be applied to the helicopter ditching airworthiness certificate.

关 键 词：光滑粒子动力学 直升机 水上迫降 仿真 载荷 

分 类 号：V221[航空宇航科学与技术—飞行器设计]