基于飞行动力学特性的运输直升机外吊挂点设计研究  

Design of Slung-Load Layout Schemes for Transport Helicopter Based on Flight Dynamics

作　　者：徐明 苏小恒 李黔[1] 黄利[1] 张威[1] Xu Ming;Su Xiaoheng;Li Qian;Huang Li;Zhang Wei(China Helicopter Research and Development Institute, Jingdezhen 333001, China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《航空科学技术》2018年第4期27-31,共5页Aeronautical Science & Technology

摘　　要：首先参考国内外直升机外吊挂点的设计经验,初步确立了某型运输直升机外吊挂点的两种布置方案;然后根据直升机吊挂飞行时的飞行动力学特性,建立了涵盖吊挂物特性的直升机外吊挂飞行动力学模型,计算了某型运输直升机两个外吊挂点设计方案的配平特性、飞行品质;最后在参考国军标的基础上,对两种外吊挂点设计方案进行了对比分析,确定了机身腹部设置外吊挂点的设计方案,为直升机设计提供参考。Firstly,based on the case studies of foreign successful references,the two types of slung-load schemes were preliminary determined for a transport helicopter.Then,a helicopter mathematical model with a slung load was described,according to the characteristic of helicopter slung-load flight,and the trim character and flight quality were calculated for the different slung-load schemes by the model,Finally,the two types of slung-load schemes were compared by reference to the National Military class,and the schemes which slung load were fixed on belly haS been established,and it provided guidance for helicopter design.

关 键 词：直升机 吊挂 飞行动力学 飞行品质 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]