摘要
空空导弹的挂飞振动应力是影响其可靠性的重要因素，导弹的挂飞振动主要由导弹周围的气动扰流引起。通过分析导弹周围的气动扰流特性，并引用国内外空空导弹的挂飞振动实测数据，指出了GJB899中对整弹挂飞振动要求的不合理之处。并建议整弹可靠性试验中的挂飞振动应采用20～2000Hz的宽带随机振动．且导弹头部振动量级应比导弹尾部的振动量级低3～6dB．这样才能真实地模拟气动扰流引起的振动效应。实践表明，采用该研究成果的实验室试验结果与空中挂飞试验结果相近。
The captive flight vibration stress is an important factor which affects the air-to-air missile's reliability,the vibration mainly derives from the disturbed air flow field around the missile.Through analyzing the characteristics of the disturbed air flow field around the missile,and citing the actual vibration data obtained from the missile's outfield captive flight test at home and abroad,it is pointed out that the GJB899's regulations for the whole air-to-air missile's captive flight vibration is illogical.It is suggested that the whole missile's captive flight vibration in reliability test should be a wide range random vibration whose frequency is from 20 to 2000 Hz,and the vibration power spectrum density level of the missile's foreside should be 3～6 dB lower than that of the missile's rearward,in this way,the actual captive flight vibration caused by the disturbed air flow field is simulated.The result of the laboratory test is close to that of the captive flight test in the sky.
出处
《振动．测试与诊断》
EI
CSCD
2007年第1期36-39,共4页
Journal of Vibration,Measurement & Diagnosis
基金
国防可靠性共性技术预研基金资助项目
关键词
可靠性
振动
功率谱密度
挂飞
参考应力
reliability vibration power spectrum density captive flight reference stress
作者简介
李根成 男，1968年5月生，研究员。主要研究方向为可靠性工程。曾发表“定时截尾可靠性鉴定试验的参数选择及分析”（《航空学报》2006年第27卷第2期）等论文。E—mail：lgcl@dse．buaa．edu．cn
