战斗机阻力伞载荷计算研究  

Load Calculation of Drag Parachute for Fighter

作　　者：蔡志军 闵强[1] 余继红[1] CAI Zhi-jun;MIN Qiang;YU Ji-hong(AVIC Chengdu Aircraft Design&Research Institute,Chengdu 610091,China)

机构地区：[1]中国航空工业集团有限公司成都飞机设计研究所,成都610091

出　　处：《装备环境工程》2020年第9期122-128,共7页Equipment Environmental Engineering

摘　　要：目的通过对战斗机阻力伞载荷计算开展研究,为阻力伞安装支持结构的静强度和疲劳强度分析提供支持。方法分别运用工程计算方法、流固耦合数值模拟方法,并对比阻力伞火箭滑车试验实测数据,对阻力伞载荷计算开展研究。同时基于飞参数据,运用统计学方法对影响阻力伞载荷大小和方向的开伞速度、飞机俯仰角、侧风速度与方向等参数进行统计分析,为载荷谱编制提供数据基础。结果确定阻力伞载荷工程计算方法中动载系数k取为1.2,将一次放伞的载荷历程简化为以拉直力和张满力为峰值的两个载荷循环,且拉直力为张满力的50%。以某型飞机766架起落飞参数据为基础,运用皮尔逊Ⅲ型分布、指数分布对开伞速度、飞机俯仰角、侧风速度与方向等参数进行拟合,结合阻力伞载荷计算方法,得出阻力伞载荷大小和方向分布的统计规律。结论明确了阻力伞载荷计算方法及计算相关参数选取,同时提出一种符合战斗机实际使用环境的阻力伞载荷谱编制方法。The paper aims to provide support for the static strength and fatigue strength analysis of the installation support structure of the drag parachute through research on the load calculation of the fighter drag parachute.By using engineering calculation method,fluid structure coupling numerical simulation method,and comparing the measured data of drag parachute rocket pulley test,the load calculation of drag parachute was studied.At the same time,based on the flight data,drag parachute release velocity,aircraft pitch angle,cross-wind velocity,direction and other parameters affecting the drag parachute load were statistically analyzed,to provide data base for compilation of load spectrum.The dynamic load coefficient k was determined to be 1.2 in engineering calculation method of parachute load,and the load history of parachute releasing was simplified as two load cycles with the peak value of stretching force and tension force,and the straightening force was 50%of the full tension force.Based on 766 takeoff and landing flight data of a certain type of aircraft,the parachute release velocity,aircraft pitch angle,cross-wind velocity and direction were fitted by PearsonⅢdistribution and exponential distribution.Combined with the calculation method of drag parachute load,the statistical law of drag parachute load value and direction distribution was obtained.The calculation method of parachute load and the selection of relevant parameters are defined.At the same time,a compilation method of parachute load spectrum in accordance with the actual use environment of fighter is proposed.

关 键 词：阻力伞 流固耦合 火箭滑车试验 统计分析 载荷谱 

分 类 号：V216[航空宇航科学与技术—航空宇航推进理论与工程]