民用飞机试飞员空中应急离机轨迹风洞实验研究  

Investigation of flight test crew aerial emergency egress trajectory from civil aircraft in low speed wind tunnel

作　　者：刘洋[1] 周星[1] 

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《实验流体力学》2015年第6期54-58,共5页Journal of Experiments in Fluid Mechanics

摘　　要：根据民用飞机试飞员空中应急离机安全性的适航验证需要,结合某型客机的空中应急离机初步方案,在南京航空航天大学3m×2.5m低速风洞(NH-2)对试飞员空中应急离机轨迹进行了研究。实验设计了与试飞员外形、重量以及转动惯量相似的人体模型,利用高速摄影机捕捉人体模型从离机出口跳伞后的轨迹,分析轨迹安全性,研究不同参数对轨迹的影响。结果表明,某型客机空中离机初步方案存在风险,离机轨迹会与右侧主起落架和短舱发生碰撞。且飞行高度、飞行速度、离机初速度以及防气流吹袭装置对离机轨迹有显著影响。本研究可用于民用飞机空中应急离机方案的设计和适航验证。Flight test crew emergency egress trajectory experiments were conducted in 3m×2.5mlow speed wind tunnel（NH-2）at NUAA,in order to assess and validate the airworthiness of the initial emergency egress concept for certain civil aircraft.Scaled models bearing similar shape,weight and moment of inertia to real flight test crew were designed,and high speed cameras were used to capture the egress trajectories of these scaled models carrying parachutes.Consequently,the safety of the trajectory was analyzed,and effects of different parameters on the trajectory were investigated as well.Test results demonstrate that the initial emergency egress concept of certain civil aircraft is not safe,and some trajectories run into the starboard main landing gear and nacelle.In addition,the influence of the flight altitude,the flight speed,the egress speed and the anti-airflow device on the aerial emergency egress trajectory are found to be significant.This investigation could be utilized in the design of aerial emergency egress concept and airworthiness validation for civil aircraft.

关 键 词：民用飞机 适航 空中应急离机 轨迹 风洞实验 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]